PROGRAM - Agence spatiale canadienne

Life and Physical
Sciences Workshop
PROGRAM
March 3 to 5, 2008
Life and Physical Sciences
Directorate
Space Science

TABLE OF CONTENTS
1 INTRODUCTION....................................................................................................................5
2 MAP OF THE CONFERENCE CENTRE OF THE CSA....................................................... 6
3 AGENDA................................................................................................................................. 7
3.1 DAY ONE: SCIENTIFIC RESULTS (March 3, 2008).......................................................................7
3.2 DAY TWO: TECHNOLOGY DEVELOPMENT (March 4, 2008)....................................................9
3.3 DAY THREE: SCIENCE AND TECHNOLOGY (March 5, 2008) .................................................11
4 SCIENTIFIC ABSTRACTS FOR ORAL PRESENTATION IN SPACE PHYSICAL
SCIENCES .................................................................................................................................... 12
4.1 Solidification and Dissolution under Microgravity and Applied Magnetic Fields ............................12
4.2 Nonlinear Optical Properties of Schiff Base-Containing Conductive Polymer Films
Electrodeposited in Microgravity ..................................................................................................................13
4.3 Phase Field Modeling of Rapid Solidification...................................................................................13
4.4 Genèse planétaire : expériences et simulations..................................................................................14
4.5 Control of Surface Tension-Driven Convection During Evaporation of Water ................................14
4.6 Solute Diffusion in Non-Ionic Liquids – Effects of Gravity .............................................................15
4.7 Effect of small vibrations on the behaviour of a solid particle contained in a fluid cell under
microgravity ..................................................................................................................................................15
4.8 Effects of Buoyancy and Pressure on Diffusion Flame Dynamics and Structure..............................16
4.9 Flame Propagation and Quenching in Iron Dust Clouds ...................................................................17
4.10 The role of microgravity on X-ray diffractive properties of protein crystals.....................................17
5 SCIENTIFIC ABSTRACTS FOR ORAL PRESENTATION IN SPACE LIFE SCIENCES 19
5.1 Visual perception of smooth and perturbed self-motion....................................................................19
5.2 Muscle fat accumulation in space flight analogue.............................................................................19
5.3 Bodies In the Space Environment (BISE). Relative contributions of internal and external cues to
self-orientation, during and after zero gravity exposure................................................................................20
5.4 Cardiovascular responses to long-duration missions to the International Space Station...................20
5.5 Development/characterization of novel hardware for use in space to use cells cultured in 3D to
study the interaction between host immunity and tumour growth.................................................................21
5.6 Alternative Dispute Resolution (ADR) Systems Design – Conflict Resolution Concept for Extended
Space Missions..............................................................................................................................................22
5.7 APEX-CAMBIUM: Growing trees in microgravity.........................................................................22
5.8 Biomechanics on Cellular Responses to Microgravity......................................................................23
5.9 The effect of tail-suspension on energy expenditure in mice ............................................................23
5.10 Effects of simulated microgravity on the swimbladder and buoyancy regulation in the zebrafish ...24
6 SCIENTIFIC ABSTRACTS FOR POSTER PRESENTATION IN SPACE PHYSICAL
SCIENCES .................................................................................................................................... 25
6.1 Non-Equilibrium Solidification for Quantitative Microstructure Engineering of Ni And Al Alloys 25
6.2 Microgravity as an environment for growth of semiconductor nanowires ........................................25
6.3 Agrégation des poudres fines en gravité réduite................................................................................26
6.4 Propriétés optiques d'agrégats fractals à monomères nanométriques de Si .......................................26
6.5 Production d’alliages binaires par évaporation-condensation laser...................................................27
6.6 Simulation non séquentielle des procédés d’agrégation en microgravité ..........................................27
6.7 Preliminary Results of Thermal Diffusion Coefficients for Different Hydrocarbon Mixtures
Experiment Flown on Board Foton M3 Mission...........................................................................................27
6.8 The Shape of Impact Craters in Granular Media...............................................................................28
6.9 Double-helical contact processes and heat exchange ........................................................................28
2

6.10 Microgravity double-helical fluid containment .................................................................................29
6.11 Numerical Simulation of Liquid Sloshing in Microgravity...............................................................29
6.12 Modeling of thermodiffusion experiments for hydrocarbon mixtures and water-alcohol mixtures On
Board FOTON M3 ........................................................................................................................................30
6.13 Diffusion in Liquids ..........................................................................................................................31
6.14 The effect of gravity on flame shape and radiation in laminar diffusion flames ...............................31
6.15 Flame Propagation in Discrete, Heterogeneous Media......................................................................32
6.16 High-density/low-cost micro-gravity protein crystallization methodology.......................................32
6.17 Quantum Communication and SpaceQUEST....................................................................................33
6.18 Durability Enhancement and Contamination Prevention for Functional External Materials in Space
Missions .......................................................................................................................................................33
6.19 Impact of Gaseous and Temperature Environmental Conditions on Thermal Parameters of Materials
and Protective Structures of Satellites, Spacecraft and Landing and Re-Entry Space Vehicles....................34
7 SCIENTIFIC ABSTRACTS FOR POSTER PRESENTATION IN SPACE LIFE SCIENCES
............................................................................................................................................. 35
7.1 Canadian experiments in European bed rest studies, WISE-2005 and ESA-2008 ............................35
7.2 Canadian bed rest experiments – study of the NASA fluid loading protocol....................................35
7.3 Research Activities in Radiation Exposure of Space Crew ...............................................................36
8 SPACE AGENCY ABSTRACTS.......................................................................................... 37
8.1 Recent Successes in NASA’s Gravity-Dependent Physical Sciences Research Program on the ISS37
8.2 The ESA program in physical sciences in the framework of the ELIPS-ARISE program research
including applications on the ground and in space........................................................................................37
8.3 Sciences de la Matière, CNES...........................................................................................................38
8.4 On-board Experimental Study of Bubble coalescences and Bubble Oscillations in the Recoverable
Satellite .......................................................................................................................................................38
8.5 Foton-M3: Technological and Operational Constraints in Meeting Scientific Objectives ................39
9 TECHNOLOGY DEVELOPMENT ABSTRACTS FOR ORAL PRESENTATION IN
SPACE PHYSICAL SCIENCES .................................................................................................. 40
9.1 An Application of Hardware Development for Microgravity Research............................................40
9.2 System Identification and Performance Testing of the Microgravity Vibration Isolation Subsystem
(MVIS) for the European Space Agency’s Fluid Science Laboratory...........................................................40
9.3 Space-DRUMS® - Facility for the ISS .............................................................................................41
9.4 A Historical Review of Space Instrument Technologies Developed by Routes AstroEngineering and
Used to Support L&PS Scientific Mission Objectives ..................................................................................42
9.5 Canada’s Heritage and Experience with Operations and Hardware Development within the ISS
Program .......................................................................................................................................................43
9.6 Configurable Miniature Laboratory for Space Science and Materials Processing ............................43
9.7 PCS: An Example of Collaboration between Engineers and Scientists.............................................44
10 TECHNOLOGY DEVELOPMENT ABSTRACTS FOR ORAL PRESENTATIONS IN
SPACE LIFE SCIENCES .............................................................................................................45
10.1 Advanced Miniature IR Spectral Processor for Remote Astronaut Health Diagnostics....................45
10.2 Rapid microbial DNA detection on compact disc: potential applications on spaceship....................45
10.3 MOEMS-based optical micro-bench platform for the miniaturization of sensing devices for space
applications....................................................................................................................................................46
10.4 eOSTEO – Automated Closed Culture System for Study of Bone Cells in Microgravity ................47
10.5 Micropackaging technology of microbolometer FPA enabling the miniaturization of mid-IR
instruments for space exploration missions...................................................................................................47
10.6 INO’s Micro-Flow Cytometer and other Optics and Photonics Technologies for Space ..................48
11 TECHNOLOGY DEVELOPMENT ABSTRACTS FOR POSTER PRESENTATION IN
SPACE PHYSICAL SCIENCES .................................................................................................. 49
3

11.1 The Vibration Environment on Spacecraft and Development of Isolation Technology for the ISS..49
11.2 An Overview of Past, Present, and Future Canadian Microgravity Vibration Isolation Mount
Technology....................................................................................................................................................49
11.3 Diagnostics Using a Confocal Holography Microscope for Three-Dimensional Temperature and
Compositional Measurements of Fluids in Microgravity ..............................................................................50
11.4 ARTEC Technologies........................................................................................................................51
11.5 A New Multifunctional Space Simulator for Accelerated Ground-Based Testing of Spacecraft
Materials and Structures Intended for Space Exploration Missions.................................................................51
11.6 A Novel Approach for Non-Destructive Mapping of Structural and Mechanical Properties of Moon
and Mars Soils...............................................................................................................................................52
11.7 Extended Interaction Klystrons for Communications, Topographical Mapping and Remote Sensing
Applications...................................................................................................................................................52
11.8 Étude de l’influence des Perturbations Orbitales sur la Trajectoire des Satellites Défilants .............53
12 WORKSHOP PARTICIPANT LIST.................................................................................. 55
4

1 INTRODUCTION
The Canadian Space Agency (CSA) Space Life and Physical Science (LPS) Directorate is pleased to invite
Canadians to the bi-annual LPS workshop entitled "Life and Physical Sciences in Space: Scientific
Advancement and Planning for Future Missions". The workshop will be held at CSA HQ in St-Hubert on
March 3, 4, and 5, 2008. The main objectives of this year's workshop are to:
• Encourage and foster collaboration among the key groups of participants: physical scientists, life
scientists, and Canadian industry.
• Present and discuss recent scientific results in space life and physical science programs; and
• Present and identify key technological requirements to meet scientific objectives for future missions in
both scientific disciplines.
• Provide a forum for dialogue between CSA and its clients.
The objectives will be met through the active participation of Canadian industry, the academic community,
space agency representatives, and graduate students. In preparation for the workshop, Canadian scientists
were first invited to submit abstracts requested to include the following information:
• Scientific objectives
• Recent scientific progress, including results from ground-based and/or reduced-gravity (near freefall)
environments
• Identification of key technologies or advances required for implementing scientific objectives in a
future spaceflight experiment
These scientific abstracts, including many others submitted by the scientific abstract deadline date, were
published on the CSA workshop website. The next step was for Canadian industry and technology
developers to review these scientific abstracts in order to tailor their technology abstract submissions. The
technological abstracts were requested to include, as a minimum:
• Past and recent technological progress
• Results of technology from ground-based studies and/or reduced-gravity operational environments
• Identification of scientific requirements that have been (or could be) met by the technology, as
used in past, present or future spaceflight experiments
In order to develop the workshop program, a review of both scientific and technology development
abstracts was conducted. This resulted in the scientific program scheduled for the first day of the workshop,
and the technology development program organized for the second day. An important objective of the
workshop is to identify and prioritize the technology necessary to meet Canadian scientific objectives of the
Life and Physical Science Programs. This will be achieved through a series of consensus-driven
brainstorming sessions, resulting in a final report available to all. In preparation for these sessions, all
participants are invited to review all abstracts prior to the workshop.
The LPS Workshop Organizing Committee looks forward to welcoming all participants to the CSA in
March.
5

2 MAP OF THE CONFERENCE CENTRE OF THE CSA
1
2
Room
1+2
3
Room
3+4+5
4
Coffee, pauses, buffet, posters
6

3 AGENDA
3.1 DAY ONE: SCIENTIFIC RESULTS (March 3, 2008)
08:00-08:30 Registration and poster setup (with coffee, muffins, juice)
08:30-08:40 Welcome & Opening Remarks
Dr. Dave Kendall, Director General, Space Science, CSA
08:40-10:10 CSA Life and Physical Science Program
Mandate
Funding and Implementation
Space Platforms
Exploration Program
• Dr. Nicole Buckley, Director, Life & Physical Sciences, CSA
• Dr. Perry Johnson-Green, Senior Program Scientist, Life and Physical
Sciences, CSA
• Dr. Alain Berinstain, Director, Planetary Exploration and Space Astronomy,
CSA
10:10-10:15 Introduction to Workshop Objectives
Dr. Nicole Buckley, Director, Life & Physical Sciences, CSA
10:15-10:30 Question Period
10:30-10:45 NETWORKING BREAK
Scientific Presentations (Part I)-Parallel Breakout Sessions for Life and Physical
Sciences
Recent Scientific Results from the Canadian LPS programs
(Each presentation includes 15 min presentation - 10 min science, 5 min technology -
and 5 min Q&A)
10:45-10:50 Life Science- Session Chair Dr. Luchino
Cohen, Program Scientist, Space Life
Sciences
LOCATION: Room 3+4+5
10:50-11:10 Visual perception of smooth and
perturbed self-motion
Dr. Robert S. Allison, Centre for Vision
Research, York University
11:10-11:30 Muscle fat accumulation in space flight
analogue
Dr. Guy Trudel, Professor, Bone and
Joint Laboratory, University of Ottawa
11:30-11:50 Bodies In the Space Environment
(BISE) Relative contributions of
internal and external cues to self-
Physical Science-Session Chair Dr.
Marcus Dejmek, Program Scientist, Space
Physical Sciences
LOCATION: Room 1+2
Solidification and Dissolution under
Microgravity and Applied Magnetic
Fields
Dr. Sadik Dost, Professor and Canada
Research Chair, University of Victoria
Nonlinear Optical Properties of Schiff
Base-Containing Conductive Polymer
Films Electrodeposited in Microgravity
Dr. Michael Wolf, Professor, University of
British Columbia
Phase Field Modeling of Rapid
Solidification
7

orientation, during and after zero
gravity exposure
Dr. Laurence Harris, Professor, Centre
for Vision Research, York University
11:50-12:10 Cardiovascular responses to longduration
missions to the International
Space Station
Dr. Richard L Hughson, Professor,
University of Waterloo
12:10-12:30 Development/characterization of novel
hardware for use in space to use cells
cultured in 3D to study the interaction
between host immunity and tumor
growth
Dr. Reginald Gorczynski, Senior Scientist,
University Health Network
12:30-12:50 Alternative Dispute Resolution (ADR)
Systems Design – Conflict Resolution
Concept for Extended Space Missions
Captain Maryellen Cronin, Canadian
Forces, 51 Aerospace Control and
Warning Squadron
Dr. Nikolas Provatas, Professor,
McMaster University
Genèse Planétaire: Expériences et
Simulations
Dr R.J. Slobodrian, Professeur, Université
Laval
Control of Surface Tension-Driven
Convection During Evaporation of
Water
Dr. Charles Ward, Professor, University
of Toronto
Effects of Buoyancy and Pressure on
Diffusion Flame Dynamics and
Structure
Dr. Ömer L. Gülder, Professor, University
of Toronto
12:50-13:50 LUNCH (own arrangements – CSA cafeteria)
13:50-15:30 HIGH LEVEL POSTER SESSION (science, technology, and agency) – see
Sections 8, 9, 10 and 13 for Poster Abstracts. Posters: 35" H X 76" W, attached by
Velcro
15:30-15:45 NETWORKING BREAK
Scientific Presentations (Part II) -Parallel Breakout Sessions for Life and Physical
Sciences
15:45-16:05 Effects of simulated microgravity on
the swimbladder and buoyancy
regulation in the zebrafish
Dr. F. M. Smith, Professor, Dalhousie
University
Flame Propagation and Quenching in
Iron Dust Clouds
Dr. Andrew Higgins, Professor, McGill
University
16:05-16:25 APEX-CAMBIUM: Growing trees in
microgravity
Dr. Rodney Savidge, Professor,
University of New Brunswick
16:25-16:45 Biomechanics on Cellular Responses to
Microgravity
Dr. Mian Long, Institute of Mechanics,
Chinese Academy of Sciences, P. R. China
(cancelled)
16:45-17:05 The effect of tail-suspension on energy
expenditure in mice
The role of microgravity on X-ray
diffractive properties of protein crystals
Dr Jurgen Sygusch, Professeur, Université
de Montréal
Solute Diffusion in Non-Ionic Liquids –
Effects of Gravity
Dr. Paul J. Scott, Research Associate,
Queen's University
Effect of small vibrations on the
behaviour of a solid particle contained
in a fluid cell under microgravity
8

Dr. Tooru Mizuno, Professor, University
of Manitoba
Dr. Masahiro Kawaji, Professor,
University of Toronto
17:05-17:15 Concluding Remarks
17:30 Bus Departs CSA
3.2 DAY TWO: TECHNOLOGY DEVELOPMENT (March 4, 2008)
08:00-08:30 Registration (with coffee, muffins, juice)
08:30-08:40 Welcome
Guy Bujold, President, Canadian Space Agency (CSA)
08:40-08:50 Introduction to the day’s objectives
Dr. Nicole Buckley, Director, Life & Physical Sciences, CSA
08:50-09:20 ESA's Research and Payload Technologies in the ELIPS Program
Dr. Martin Zell, Head of Research Operations Department, ESA/ESTEC
09:20-09:50 International Space Station: A test bed for Exploration and Science
Dr. Fred Kohl, ISS Research Project Manager, NASA Glenn Research Center
Dr. Jacob Cohen, Program Executive, Advanced Capabilities Division, NASA HQ,
ESMD
09:50-10:20 FOTON M3: Technological and Operational Constraints in Meeting Scientific
Objectives
Mr. Antonio Verga, Technical Officer for ESA’s payload, ESTEC
10:20-10:40 NETWORKING BREAK
10:40-11:25 Multidisciplinary Approach in Science
Dr. David Needham, Professor, Duke University
Technology Presentations (Part I): Parallel Sessions For Life And Physical
Sciences
11:30-11:35 Life Science- Session Chair Dr. Luchino
Cohen, Program Scientist, Space Life
Sciences
LOCATION: Room 3+4+5
11:35-11:55 INO’s Micro-Flow Cytometer and
other Optics and Photonics
Technologies for Space
Ms. Marcia Vernon, INO
Physical Science-Session Chair Dr.Marcus
Dejmek, Program Scientist, Space Physical
Sciences
LOCATION: Room 1+2
An Application of Hardware
Development for Microgravity Research
Mr. Stephen Churchill, C-CORE
11:55-12:15 Rapid microbial DNA detection on
compact disc: potential applications on
spaceship
Dr Eric Leblanc, Chef de projets, Centre
de Recherche en Infectiologie
System Identification and Performance
Testing of the Microgravity Vibration
Isolation Subsystem (MVIS) for the Fluid
Science Laboratory
Mr. Derrick Piontek, Magellan Aerospace
Corporation / Bristol Aerospace Limited
9

12:15-12:35 MOEMS-based optical micro-bench
platform for the miniaturization of
sensing devices for space applications
Dr Sonia Garcia-Blanco, INO
Space-DRUMS® - Facility for the ISS
Dr Jacques Guigné, Guigné International
12:40-13:40 LUNCH (own arrangements – CSA cafeteria)
Technology Presentations (Part II): Parallel Sessions For Life And Physical
Sciences
13:40-14:00 eOSTEO – Automated Closed Culture
System for Study of Bone Cells in
Microgravity
Mr. Lowell Misener, Systems
Technologies
14:00-14:20 Advanced Miniature IR Spectral
Processor for Remote Astronaut
Health Diagnostics
Dr. Roman V. Kruzelecky, MPB
Communications
14:20-14:40 Micropackaging technology of
microbolometer FPA enabling the
miniaturization of mid-IR instruments
for space exploration missions
Dr Sonia Garcia-Blanco, INO
14:40-15:00 Invited Speaker: Scientific Perspective
Payload Development Experiences
Mr. Ruediger Hartwich, Astrium Space
Transportation
A Historical Review of Space Instrument
Technologies Developed by Routes
AstroEngineering and Used to Support
L&PS Scientific Mission Objectives
Mr. Blair Gordon, Routes
AstroEngineering
Canada’s Heritage and Experience with
Operations and Hardware Development
within the ISS Program
Mr. Richard Rembala, MDA
Configurable Miniature Laboratory for
Space Science and Materials Processing
Dr. Roman V. Kruzelecky, MPB
Communications
Invited Speaker: Scientific Perspective
PCS: An Example of Collaboration
between Engineers and Scientists
Dr. Arthur E. Bailey, Scitech Instruments
Inc.
15:00-15:15 NETWORKING BREAK
15:15-18:00 Brainstorming in Parallel Sessions (In sub-disciplines)
The overall objective of the brainstorming sessions is to identify the technology
development required to achieve each community's scientific objectives. A series of
general questions will be used to guide participants to identify, clarify, and rank
technologies necessary for future spaceflight experiments.
Life Science
LOCATION: Room 345
Physical Science
LOCATION: Room 12
18:00-20:00 DINER (PROVIDED BY CSA) WITH CASH BAR
20:00 Bus Departs CSA
10

3.3 DAY THREE: SCIENCE AND TECHNOLOGY (March 5, 2008)
08:00-08:30 Registration (with coffee, muffins, juice)
Space Technologies Development Program (Priority Technologies, Current
Projects and AO/RFP Description)
08:30-08:45 Jean Claude Piedboeuf, Head Technology Requirement and Planning, Technology
Management and Applications, CSA
08:45-09:00 Walter Peruzzini, Program Manager, Spacecraft Technologies, CSA
09:00-10:15 Life Sciences
LOCATION: Room 3+4+5
(Prepare presentation for plenary)
Physical Sciences
LOCATION: Room 1+2
(Prepare presentation for plenary)
10:15-10:30 NETWORKING BREAK
10:30-11:50 LPS Plenary Wrap-Up
Discipline Presentations and Interdisciplinary Discussions
11:50-12:00 Closing Remarks and Thank Everyone
12:30 Bus departs CSA
11

4 SCIENTIFIC ABSTRACTS FOR ORAL PRESENTATION IN SPACE
PHYSICAL SCIENCES
4.1 Solidification and Dissolution under Microgravity and Applied Magnetic Fields
Sadik Dost
Professor and Canada Research Chair
Crystal Growth Laboratory, University of Victoria, Victoria, BC, Canada V8W 3P6
E-mail: sdost@me.uvic.ca
This is a combined experimental/theoretical study focusing on the growth of alloy single crystals and the
associated solidification and dissolution processes under microgravity and applied magnetic fields. The
solution growth techniques of Liquid Phase Diffusion (LPD) and the Travelling Heater Method (THM) are
utilized. The materials of interest are the single crystals of SixGe1-x, and GaxIn1-xSb. Crystal growth
experiments are also being conducted under microgravity-simulated conditions using static and rotating
magnetic fields.
The objective is to determine optimum growth conditions (such as translation rates, growth rates,
temperature profiles with different gradients) for future microgravity experiments to be performed using the
MSL-LGF insert of ESA, and the ATEN furnace when it is available.
Correct values of diffusion coefficients in metallic liquids are essential for accurate crystal growth and
solidification modelling studies. In this direction, we are carrying out dissolution experiments with and
without the application of magnetic fields. The experimental results of silicon dissolution into germanium
melt will be presented. The effect of free surface is also studied experimentally. The effect of gravity is
studied by designing two dissolution systems; in one the gravitational field is in the dissolution direction
and in the other in the opposite direction.
Results show the significant contributions of gravity, free surface, and applied magnetic fields to the
dissolution process. The results of these works were disseminated in journals:
Armour, N., S. Dost, and B. Lent, “Effect of Free Surface and Gravity on Dissolution in Germanium Melt,”
J.Crystal Growth, 299, 227-233, 2007.
Armour, N., and S. Dost, “The Effect of a Static Magnetic Field on Buoyancy-Aided Silicon Dissolution
into Germanium Melt,” J. Crystal Growth, 306(1), 200-207, 2007.
and presented in conferences:
Armour, N., and S. Dost, “Effect of Free Surface and Gravity on Silicon Dissolution into Germanium
Melt,” CANCAM07, Toronto, Ont., June 3-7, 2007.
Dost, S., N. Armour, and B. Lent, “The Effects of Gravity and an Applied Magnetic Field on the
Dissolution of Silicon into Germanium Melt,” ISPS07, p. 53, Nara, Japan, November 22-26, 2007.
Experiments will be supported by 3-D numerical simulations using both commercial packages (CFX and
Fluent), and in-house codes based on the finite volume method. We are also utilizing the technique of
Smoothed Particle Hydrodynamics (SPH) to determine the evolution of the growth interface and the solid
crystal composition in the grown crystals. The use of this technique in crystal growth is new, and needs
further research to improve its computational efficiency.
Required technologies and platforms
1. All dissolution and LPD experiments (with and without the application of an applied rotating magnetic
field) can be carried out using the MSL-LGF inset of ESA. It is also possible to perform THM experiments
under certain restrictions (such as temperature and its gradient).
2. The above experiments can also be carried out (with no magnetic fields) using ATEN furnace when it
becomes available.
3. A quenching facility to solidify the samples of dissolution experiments.
12

4.2 Nonlinear Optical Properties of Schiff Base-Containing Conductive Polymer Films
Electrodeposited in Microgravity
Agostino Pietrangelo, Bryan C. Sih, Britta N. Boden, Zhenwei Wang, Qifeng Li, Keng C. Chou, Mark J.
MacLachlan, Michael O. Wolf. Department of Chemistry, University of British Columbia, 2036 Main
Mall, Vancouver, British Columbia, Canada V6T 1Z1
Materials with large nonlinear optical (NLO) responses are needed for new optical and photonic
technologies for data transmission and processing. Molecular and polymeric materials offer possible
advantages, including tuneable NLO properties and solution processability, over conventional materials.
Conjugated polymers containing metals in the backbone are one class of materials being considered for
new NLO technologies. Studies indicate that electrochemical processes are significantly influenced by the
effect of gravity, however electropolymerization, an effective method to prepare conjugated polymers
films, is essentially unexplored in microgravity. In this study, we compare the effects of pendant alkoxy
chains, metals, and gravity on the third-order susceptibilities, 3) , of the electropolymerized thin films. We
have designed and built a computer-controlled self-contained potentiostat with sealed cells to allow data
collection on the Falcon jet. The four compartment sealed cell was developed with a software (written
using Labview) and hardware package to control four sets of electrodes. Measurement of 3) demonstrates
that gravity affects the electropolymerization, and some polymers prepared under microgravity have
enhanced third-order NLO properties relative to those prepared at 1 g. A key objective for a future
spaceflight experiment will be to prepare thicker free-standing films which cannot be grown on parabolic
flights due to the short duration of microgravity under these conditions. Thicker films grown in space will
allow us to use X-ray diffraction and other analytical methods to probe the local order in the films to further
understand the origin of the enhanced NLO properties obtained from the parabolic flights. New hardware
must be developed for the spaceflight experiments to allow fully automated growth of films without the
need to reload the cells between flights. This will involve incorporating a robotic unit loaded with
sufficient substrates to maximize utilization of the time spent in zero gravity. Modification of the
electronics and software to accommodate thicker film growth and more substrates will also be needed.
4.3 Phase Field Modeling of Rapid Solidification
Sebastian Gurevich, Peter Kuchnio and Nikolas Provatas
Department of Materials Science and Engineering, McMaster University
Theoretical Solidification Modeling:
We will explore the use of phase field methodology as an emerging technique for predictive modeling of
solidification microstructure evolution in metallic alloys. We begin by introducing phase field models of
solidification and novel computational/mathematical techniques necessary to simulate dendritic growth
efficiently at experimentally relevant parameters. We discuss recent quantitative predictions of dendrite
spacing in selection in directional solidification of binary alloys, the role of surface tension anisotropy in
dendritic morphology, and non-equilibrium solute trapping effects in rapid solidification of Cu-Ni alloys.
We then move on to a recent extension of the traditional phase field paradigm, coined the phase-fieldcrystal
(PFC) method, which allows us to incorporate atomic-scale elasto-plasticity effects in solidification
and solid state transformations. Results and remaining challenges of this new technique are discussed.
Industrial Relevance:
Phase field simulations on dendritic structure can play a significant role in the design of commercial alloys
for industrial application. Our work focuses on three areas of casting: direct thin slab casting of steel, strip
casting of aluminum alloys and the solidification of aluminum-based liquid drops. The last category in
particular is industrially relevant to powder metallurgy, but also offers a unique glimpse into the
solidification physics in micro-gravity conditions. Our emerging theoretical picture on grain refinement in
rapidly solidified liquid drops is based on a competition between thermal and solute diffusion and
anisotropy in the kinetics of atomic attachment at the interface. Testing our theory will thus require microgravity
experiments, where convection is minimal and where high cooling rates can be achieved. Candidate
13

alloy systems to be investigated can include but are not limited to Al-Cu drops with a chemistry in the
range of

transport up to 60% of the energy required to evaporate water, with the remainder of the energy supplied by
thermal conduction (Phys. Rev. E 72: 056302; 056303; 056304; 2005). Also, the Marangoni number, as
defined by Pearson, provides a criterion for the onset of Marangoni convection. When the funnel is changed
to a non-conducting material, we find surface tension-driven convection is eliminated, and thermal
conduction supplies all of the energy required to evaporate water. Further, the Marangoni number does not
provide a criterion for the initiation of surface tension-driven convection.
Although buoyancy-driven convection can be eliminated during water evaporation when the water
temperature is less than 4°C, to study energy transport during water evaporation at higher temperatures
probably requires the near-free fall conditions of the space station. The apparatus required for that
environment is presently under investigation. One of the main issues is the elimination of the vacuum
pumps, used in the ground-based studies, with a condenser.
4.6 Solute Diffusion in Non-Ionic Liquids – Effects of Gravity
Reginald W. Smith, Paul J. Scott and Barbara Szpunar 1 , Department of Mechanical and Materials
Engineering, Nicol Hall, Queen's University,
Kingston,Ontario K7L 3N6
(Currently with Atomic Energy of Canada Ltd, Chalk River ON K0J 1J0)
In our QUELD II/MIM/MIR studies, in all the alloy systems studied, the solute diffusion coefficient (D)
increased linearly with temperature (T). Our recent molecular dynamics studies have confirmed the linear
variation of D with increase in T. For example, the diffusion of gold in liquid copper over the entire liquid
temperature range (1400 to 3200 o K) is best represented in a linear fashion as D = D m + C(T – T m ), where
D m is the value of D at the melting point T m (1357.5 K) and has the value 0.2233 x 10 -4 cm 2 /s ; C is a
constant of value 8.7 x 10 -8 cm 2 /sK
The objectives of our future liquid diffusion studies will be:- 1) Theoretical (a) to extend the MD
simulations to cover those of the alloy systems examined in the QUELD II/MIM/MIR campaign for which
appropriate interatomic potentials may be obtained; and (b) to determine the factors controlling the slope
of the DversusT relationship for any given alloy. 2) Experimental (a) measure ‘D’for various solutes alone,
and (b) with other solutes present, primarily in the industrial light metal solvents Al and Mg. 3) Future
Space Activities Some success has been obtained by others in 1g experiments in alloy systems in which the
solute distribution in the diffusion couple can provide stability to buoyancy convection. However, such 1g
experiments are usually subject to convective disruptions due to radial temperature gradients. Thus, in
addition to 1g studies, further space activities are desired; these would be best conducted in a microgravity
isolation mount -equiped type of laboratory or a well-characterised free-flyer with low g-disturbance levels.
The apparatus required would be either a QUELD II(with a pay-load astronaut) or ATEN- type(if required
to be fully automated) of facility in combination with a microgravity isolation mount(MIM), for operation
over a temperature range of 200 – 1000 o C, using sealed triple-containment long capillary samples,
preferably having forcing motion available of square wave-form and intensity 4x10 -3 g. All specimen
analysis would be done when the samples were returned to earth and the principal investigator. No special
atmospheres, analysis techniques would be required on orbit.
4.7 Effect of small vibrations on the behaviour of a solid particle contained in a fluid cell under
microgravity
Masahiro Kawaji and Samer Hassan
Dept. of Chemical Engineering & Applied Chemistry
University of Toronto
Toronto, ON, M5S 3E5, Canada
Diffusion-controlled material processing such as protein crystal growth in space can be adversely affected
by small vibrations called g-jitter existing aboard space platforms such as the International Space Station, if
a relative motion is induced between the particle and surrounding fluid. To better understand the vibration-
15

induced phenomena, theoretical, numerical and experimental investigations have been performed into the
behaviour of a small particle contained in a fluid cell under normal gravity and microgravity.
When a fluid cell containing a small particle such as a protein crystal in liquid is vibrated parallel to the
wall nearest to the particle, the particle oscillates with certain amplitude and a hydrodynamic force in the
direction normal to the wall is induced. Theoretical models based on an inviscid fluid assumption have
been used to predict the particle amplitude variation and drifting motion. Due to an external vibration such
as g-jitter, the oscillating particle is predicted to drift towards the wall and the particle oscillation amplitude
to decrease slightly as the distance between the particle and wall is reduced.
The reduction in particle amplitude also depends on the particle-to-fluid density ratio. The particle drifting
towards the nearest wall accelerates due to an increasing attraction force, and the drifting speed increases
with both the vibration frequency and particle diameter. Even for small protein crystals with a density close
to that of the fluid, the time required to drift from the center of the fluid cell to the wall is predicted to be
much shorter than the growth time.
The experimental verification of the theoretical and numerical model predictions can be achieved only by
conducting experiments in microgravity. Thus, a low resource experiment on the ISS is recommended in
the future. It would require a vibration apparatus such as CSA’s MIM and a small fluid cell containing a
fluid and particles mounted on a platform such as that used in FLEX experiments on the Space Shuttle
Discovery during an STS-85 mission. The results of this work can lead to the development of a new
method to separate solid particles and gas bubbles from a liquid in space systems.
4.8 Effects of Buoyancy and Pressure on Diffusion Flame Dynamics and Structure
Hyun I. Joo and Ömer L. Gülder
University of Toronto, Institute for Aerospace Studies
4925 Dufferin Street, Toronto Ontario M3H 5T6
Although most practical combustion systems are turbulent and operated at high pressures to improve
efficiency, studies of laminar diffusion flames are essential to understand the more complex nature of
turbulent diffusion flames. One of the central problems of laminar diffusion flame stability is the
mechanism that the flame stays attached near the jet exit. The conventional understanding is that at
atmospheric pressure and normal gravity, the mechanism of flame attachment might be due to the presence
of a small premixed flame region just above the burner rim that acts to prevent the flame from lift-off.
Another proposed attachment mechanism is due to the presence of a triple flame that has a stoichiometric
flame base with fuel rich and fuel lean branches on the fuel and airsides, respectively. It is stipulated that
the triple flame structure and presence guarantees the stabilization in high strain rate of jet outlet of a lifted
laminar diffusion flame. However, our current studies of laminar diffusions flames at elevated pressures,
and limited scope microgravity flame experiments, suggest that the conventional view of flame attachment
should be re-examined. Our results show that with the pressure increased to just a few bars, the blue
premixed zone disappears completely and the flame appears to be directly attached to the burner rim with
further increase in pressure. It is also known that buoyancy scales with pressure. Buoyancy-induced motion
is significant at elevated pressures and greatly affects the flame stability, whereas in micro-gravity the
effect of buoyancy is non-existent. The short-term objectives of this research are to resolve the controversy
about the flame attachment mechanism in laminar diffusion flames and investigate the effect the buoyancy
and pressure on the dynamics and structure. In the long term, our findings will have the potential to provide
tools for efficient and reliable fire safety measures for human-crew missions in space and propulsion
system design. Our current earth-based experimental findings complemented by numerical simulation
efforts are expected to help us to plan a potential micro-gravity experimental program.
An eventual flight experiment within the scope of this work would include measurement of the flame
shape, and the structure of the temperature field and soot distribution within a laminar diffusion flame
envelope under microgravity conditions. These measurements could be accomplished using a 2D CCD
camera by evaluating the spatially-resolved spectral emission from the flame. Flames would be stabilized
16

on a small burner of a few millimetres using low fuel flow rates such that the flame height would be about
10 to 20 millimetres.
4.9 Flame Propagation and Quenching in Iron Dust Clouds
François-David Tang, Samuel Goroshin, Andrew Higgins and John Lee
McGill University, Dept. of Mechanical Engineering
Laminar flames propagating in fuel-rich suspensions of iron dust in air were studied in a reduced-gravity
environment provided by a parabolic flight aircraft. Experiments were performed with four different dusts
having average particle sizes in the range 3-30 microns. Uniform fuel-rich dust suspensions were created
inside glass tubes and then ignited at the open end via an electrically heated wire. Quenching distances
were determined as the flames propagated through assemblies of equally spaced steel plates installed in the
tubes. Flame propagation speeds in the open tubes and within the quenching plates were determined from
video recordings, and emission spectra recorded by a spectrometer were used to determine flame
temperature. The obtained experimental results were in good agreement with the predictions of our onedimensional
dust flame model with conductive heat loss. Experiments that are planned in the near future
will expend to larger particle sizes, different gas mixtures and fuels. Experimentation with fuel-lean
mixtures in space will require development of a novel dust dispersion technique and non-contact optical
diagnostics permitting precise control of the suspension concentration and uniformity. Thus, an acoustic
dispersion system and a laser attenuation probe in combination with a micro-imaging system will have to
be developed to fully attain the experimental objectives.
4.10 The role of microgravity on X-ray diffractive properties of protein crystals
Jurgen SYGUSCH 1 and Yves TRUDEAU 2 ,
Université de Montréal, CP 6128, Stn Centre ville, Montréal,
QC, H3C 3J7 ; 1 Département de biochimie ; 2 ANIQ R&D Inc
Protein crystallization is the main bottleneck in the determination of protein structures by diffraction
techniques. Protein structures are essential to our fundamental understanding of how biological processes
function and to structure assisted drug design with many applications in academic, pharmaceutical, and
industrial research. Protein crystallization dictates high levels of supersaturation, which is required for
nucleation but detrimental for crystal growth. Microgravity crystallization has been proposed as a solution
because a stable protein depletion zone (PDZ), of reduced supersaturation that is dependant on the
crystallization conditions, can form in the absence of gravity-driven convection and sedimentation. The
premise that reduced supersaturation improves X-ray diffraction properties of protein crystals is the
motivation for growing protein crystals in space. A priori selection of proteins for microgravity
crystallization whose growth conditions are compatible with significant reduction in supersaturation at the
crystal face was not made in the past. As not all protein crystallization conditions yield reduced
supersaturation zones, protein crystallization experiments were flown whose growth kinetics in all
likelihood would not have been sensitive to exposure to a microgravity environment.
We propose to investigate PDZ formation and resultant incorporation of homologous impurities in protein
crystal growth that may determine the outcome of microgravity on the X-ray diffraction properties of
protein crystals. Characterization of these phenomena is intended to prioritize use of limited flight
opportunities by selecting which proteins would benefit the most. To attain this goal, a ground based
experimental platform has been built to characterize PDZ formation during crystal growth using
Michaelson interferometry and recent results will be presented. Concomitantly, a proteomics based
approach will be outlined using two-dimensional gel electrophoresis to measure homologous impurities in
protein crystals and their mother liquor. The preferential inclusion or exclusion of homologous impurities
by the crystal depends on the existence of a stable PDZ allowing for their depletion (favourable) or their
accumulation (unfavourable), respectively, at the growing crystal face.
17

Microgravity science mission(s) is proposed using the PROSPECT platform to crystallize carefully selected
candidate proteins in liquid-liquid diffusion hardware. Spaceflight monitoring of crystal growth by
interferometry could assess PDZ formation compared to ground controls. The missions’ objective would be
to determine whether differences in gravitational environment influences X-ray diffractive properties of the
crystallized proteins and to what extend.
18

5 SCIENTIFIC ABSTRACTS FOR ORAL PRESENTATION IN SPACE LIFE
SCIENCES
5.1 Visual perception of smooth and perturbed self-motion
Robert S. Allison, Jim Zacher, Centre for Vision Research,
York University Stephen A. Palmisano, School of Psychology, University of Wollongong
Successful adaptation to the microgravity environment of space and re-adaptation to gravity on earth
requires recalibration of visual and vestibular signals. Despite decades of experimentation, motion sickness,
spatial disorientation, reorientation illusions and degraded visuomotor performance continue to impact the
availability and effectiveness of astronauts. We have found that incorporating jitter of the vantage point
into visual displays produces more compelling illusions of self-motion (vection), despite generating greater
sensory conflicts. We will discuss a series of ground-based experiments that examine a range of possible
explanations for this phenomenon. Recent neuroimaging and neurophysiological data suggests that
accelerating optic flow stimuli—such the jittering optic flow used in our research—may result in
suppression of signals in vestibular cortex. Such visual modulation of vestibular signals is potentially
important to understanding the initial response and adaptation to microgravity. Currently it is unclear what
role gravity plays in the potentiation of vection with jittering optic flow. Ground and space based
experiments will provide a unique opportunity to explore the jitter effect during periods of adaptation to
altered gravity and to complement other research looking at vection on ISS. Our goals are to understand the
role of gravity in jitter-enhanced vection, to develop the theory of how vestibular and visual signals are
recalibrated in altered gravity and to study the time course of this adaptation
5.2 Muscle fat accumulation in space flight analogue
Guy Trudel, Bone and Joint Laboratory, University of Ottawa;
Martin Lecompte, CHVO; Hans Uhthoff, Bone and Joint Laboratory, University of Ottawa.
Introduction: Fat accumulation in muscle following inactivity and limb injury has been demonstrated.
The contribution of altered fat tissue metabolism to muscle function in microgravity has so far received
little attention
Objectives: To measure the cross-sectional area and fat content of gastrosoleus and tibialis muscles in 24
women bedridden for 60 days.
Methods: Using magnetic resonance imaging, we scanned the gastrosoleus and tibialis anterior muscles on
axial sections using T1W1 spin echo and measured the cross-sectional area and T1 signal intensity.
Results: The gastrosoleus cross-sectional area decreased from baseline 3632±654mm 2 to 3082±564mm 2
(15%) and 2904±584mm 2 (20%) respectively after 1month and 2 months bedrest (p

5.3 Bodies In the Space Environment (BISE). Relative contributions of internal and external cues
to self-orientation, during and after zero gravity exposure
L. R. Harris, R. T. Dyde, M. R. Jenkin, H. L. Jenkin and J. E. Zacher
Centre for Vision Research
York University, Toronto, Ontario, Canada
The Bodies In the Space Environment (BISE) project’s objective is to understand how unusual gravity
conditions, and in particular microgravity, affects the perception of self-orientation. Understanding how
humans construct a perceptual up direction is crucial to treating subjects on earth who through age or
disease are unable to correctly transduce sensory information that underlies the perception of up. It is also
crucial to the development of countermeasures to microgravity related illusions such as visual reorientation
illusions that have been reported on orbit. The specific objective of the BISE study is to conduct
experiments during long-duration microgravity conditions to better understand how humans first adapt to
microgravity and then re-adapt to normal gravity conditions upon return to earth. Our ongoing terrestrial
research has developed a unique set of perceptual tests that investigate the perceived up direction and these
results have lead to a weighted vector sum model of the ‘perceptual up’. We propose to utilize these tests,
coupled with the standard ‘luminous line’ test from the literature, to investigate how astronauts’ perceptual
up adapts from pre-flight to microgravity, and then re-adapts from prolonged microgravity to return to
earth-normal conditions. This information will make it possible to provide countermeasure strategies
tailored to individual astronauts.
The BISE project is currently slated to place its first experimental subject on-station in spring 2009. This
presentation will describe the BISE project, preparations to date in terms of the expected launch date, and
the basic scientific rationale underlying the project.
5.4 Cardiovascular responses to long-duration missions to the International Space Station
Richard L Hughson 1 , J. Kevin Shoemaker 2 , Philippe Arbeille 3 , Andrew Blaber 4 , Danielle K. Greaves 1
Universities of Waterloo 1 , Western Ontario 2 , Simon Fraser 4 , and Tours 3 (France)
The project Cardiovascular and cerebrovascular Control on return from the International Space Station
(CCISS) is designed to study an integrated view of blood flow control to establish the weak links that make
astronauts more susceptible to fainting on return from space. To date, we have collected complete data on
one astronaut with one more due to return to Earth soon. We are examining with non-invasive ultrasound
the factors that regulate the ability of the veins to return blood to the heart, the contractile properties of the
heart and the ability of the arteries to constrict to maintain blood pressure, as well as the ability of the blood
vessels of the brain to respond appropriately so that delivery of oxygen is well maintained. In addition, we
use 24-hour monitoring of the heart rate and physical activity patterns to understand the changes in heart
rate control during the long-duration space flight. Data will be presented for the heart rate as we now have
enough data that we can show responses without compromising astronaut confidentiality.
In the near future, we will initiate a project on Cardiovascular Health Consequences of Long-Duration
Space Flight (VASCULAR). This project will examine blood vessel changes after flight and will explore
the possible role of blood inflammation processes in these changes. Blood samples will be returned from
space and measured for a range of inflammatory markers.
The technologies required for space flight experiments must be simple yet highly reliable. We will soon
switch to a new generation of 24-hour heart rate monitor that provides greater resolution and potential for
longer periods of data collection. Ground-based experiments are highly dependent on the non-invasive
imaging technologies. Our planned space flight studies will use standard laboratory-based techniques but
future studies could benefit from micro-technologies for rapid analyses in-flight.
20

5.5 Development/characterization of novel hardware for use in space to use cells cultured in 3D to
study the interaction between host immunity and tumour growth
Reginald M. Gorczynski, Chris Adamson, Olha Kos, Lowell Misener and Dennis Sindrey
University of Toronto (Toronto) and Systems Technologies Inc. (Kingston, Canada)
The utilization of 3D structures for targeted biological tests has increased in popularity in many fields of
research, in part at least because the 3D environment of dense cell contact more closely mimics the
physiological biologic environment than does traditional 2D culture in cell monolayers. This is particularly
evident when studying the interaction between biologic systems. One example of the latter is seen in the
interaction between host resistance mechanism(s) (the immune system) and tumors growing in a stromal
bed. Pharmaceutical companies interested in drug development research have frequently reported that
promising new drugs testing positive in 2D cultures are often inactive in vivo. Research & development in
2D cultures is likely inadequate to model events and mechanisms of action for in vivo (3D) effects. This
can be especially critical in microgravity conditions.
We propose to target the development of a new dedicated 3D bioreactor that would build upon a previously
described eOSTEO hardware for reflight in space. The current eOSTEO bioreactor was designed and
optimized for use with a 2D bone substrate (Osteologic) limiting the science utility to basic bone research.
A basic insert was created to fit within the bioreactor that allowed for the inclusion of small 3D bone
scaffolds. While not optimally configured for 3D scaffolds, the fidelity of the science on the 3D scaffolds
was found by our group to be substantially improved in comparison to the 2D substrates. The science focus
we have targeted for development of this hardware involves exploration of growth of tumor cells in space
in 3D cultures in the presence of a viable host immune system.
Data to date confirms that immune responsiveness is decreased during and following spaceflight, which
may have considerable impact on surveillance against autologous tumors. The Gorczynski lab has
documented that the novel ligand:counter-receptor interaction between CD200:CD200R, members of the
TREM family, can modulate immunity in general, and tumor immunity in particular. Overexpression of
CD200 suppresses immunity and enhances tumor growth. Independent observations by several other
groups have confirmed that CD200 expression is associated with poor prognosis in human lymphoma,
myeloma, leukemia, and, more recently, breast, lung and melanoma cancer cells. The Gorczynski lab
described increased expression of CD200 on thymoma cells under microgravity conditions. In bone
cultures, increased CD200 expression promotes osteoblastogenesis vs osteoclastogenesis, and in recently
completed studies in eOSTEO, cells transfected to overexpress CD200 showed an attenuated bone loss
during spaceflight. These opposing effects of CD200 in suppression of bone loss and enhanced tumor
growth may be controlled by CD200 signaling to different CD200Rs. CD200:CD200R2 activates
osteoclastogenesis, while CD200:CD200R1 signals suppression of anti-tumor immunity.
The “proof-of-principle” science proposed for these studies is to explore whether tumor growth in a
physiologic-type 3-dimensional matrix embedded with host splenocytes in vitro is attenuated by
suppression of CD200 expression on tumor cells using mAbs or CD200-specific silencer (si) RNAs, or
using splenocytes from CD200R1 “knock-out” mice, and conversely is enhanced using splenocytes from
mice overexpressing CD200. These studies will make use of a CD200R1 KO mice and a CD200-transgenic
mouse showing increased expression of CD200 when induced by doxycycline. The latter model was used
in eOSTEO. Our overall goal is to identify pathways which stimulate the desired CD200 effect on
osteoblastogenesis, without simultaneously blocking tumor immunity.
21

5.6 Alternative Dispute Resolution (ADR) Systems Design – Conflict Resolution Concept for
Extended Space Missions
By Captain Maryellen Cronin, Canadian Forces, 51 Aerospace Control and Warning Squadron, 22 Wing
North Bay, UND Space Studies Department, Distant Program
Vadim Y. Rygalov, Ph.D., Human Factors & Environmental Design (HF & ED)
UND Space Studies Department, USA
Alternative Dispute Resolution (ADR) systems design was performed in late 1990/early 2000’s and
concept was developed and applied within the Department of National Defence (DND) for conflict
resolution using Interest-Based Communication (IBC) models. The DND ADR policy applies to all
personnel, both military and civilian, and is flexible to allow for cultural differences between elements
(army, navy, air force) under variable stress conditions. This methodology continues to be successfully
applied for conflict resolution and effective human operations and is versatile to allow for fluctuations in
operational tempo (i.e low operational tempo environments to conflict experienced under extreme stress
conditions.) Future plans for space mission to Mars and beyond will present even more stressful
environments for a small group of space crew and nature of stressors is expected to be, in certain aspects,
different compared to what astronauts have experienced until now. Effective interpersonal relations and
communication amongst space crew and between space crew and Mission Control is imperative for mission
success. ADR systems design methodology could be performed in the interest of developing an
appropriate conflict resolution system for extended duration space missions. There are
suggested/considered potential difficulties provided by specifics of space environment for this concept
development. As well, theoretical predictions will be done on the basis of experiences accumulated within
DND and the Conflict Management Program (CMP).
5.7 APEX-CAMBIUM: Growing trees in microgravity
Rodney Savidge, PhD,
Professor, Tree Physiology / Biochemistry
Faculty of Forestry & Environmental Management
University of New Brunswick
Fredericton, NB, Canada
The objective of this life sciences study is to grow willow trees in an Advanced Biological Research
System (ABRS, comprising two independently controlled environmental growth chambers) on the
International Space Station (ISS) in order to gain information about the role of gravity in the
regulation of plant growth and development. A compact method for growing trees within root
tubes was developed, and experiments to date have confirmed that 1) healthy trees can be
successfully grown in ABRS at elevated CO2 under environmentally defined conditions without
mortality over >5 weeks; 2) the trees undergo both primary and secondary growth; 3) in addition
to normal cambial growth, gravitationally sensitive reaction wood formation can be induced at
predictable locations; 4) in principle, plant tissues can be returned to earth alive, frozen or in
liquid fixative for further investigation. These advances set the stage for gaining anatomical,
biochemical and molecular biology insight into gravity perception within plants grown on the ISS.
However, there remains a major need for an ISS-based micro-dissection / cryo-fixation (plunge-freezing)
/ cryo-substitution system to enable the fine structure of living cells as they exist in microgravity to be
permanently fixed before the specimens are subjected to earth gravity. In addition, there is scope
for mass spectroscopy technology enabling sensitive, accurate, continual monitoring of individual
concentrations of all volatile organic compounds (VOCs) within the ABRS chamber.
22

5.8 Biomechanics on Cellular Responses to Microgravity
Mian Long , Shujin Sun, Yuxin Gao, and Zulai Tao
National Microgravity Laboratory, Institute of Mechanics,
Chinese Academy of Sciences, Beijing 100080, P. R. China ( mlong@imech.ac.cn)
Scientific objectives Cell growth in space is pre-requisite to understand cellular responses under
microgravity. How the driven flow of culture medium in a space cell bioreactor affects biological responses
of mammalian cells to microgravity, however, have been poorly understood. The goal of the current study
is to understand the impact of mechanical stimuli on cellular responses using a dual approach that
coordinates biological functionality, mechanical measurements, and numerical calculations, and to develop
the novel assays and technologies for both ground-based measurements and space payload experiments.
Research progresses Absence of gravity or microgravity influences molecular and cellular functions of
bone forming osteoblasts. A novel ground-based assay was developed to quantify the effects of vectordirectional
gravity on cellular responses of osteoblasts where Ros 17/2.8 or MC3T3-E1 cells were grown
up on upward-, downward- and edge-on- oriented substrate, respectively. It was found that Ros 17/2.8 cells
were shrunk with a reduced cell area in downward- and edge-on-orientated substrates. Cell-type specific
differences in cell cycle were observed in S and G2/M phases for both types of Ros 17/2.8 or MC3T3-E1
cells on the three orientated substrates. F-actin expression was reinforced, and perinuclear network of
vimentin was well organized in downward-orientated substrate. These results provide a new insight into
understanding how cultured osteoblasts response to vector-directional gravity.
Advanced technologies Driven flow is required to provide sufficient mass transportation and nutrient
supply for mammalian cells. Here a customer-made counter sheet-flow sandwich cell culture (CSSCC)
device was developed upon a biomechanical concept from fish gill breathing. The sandwich culture unit
consists of two side chambers where the medium flow is counter-directional, a central chamber where the
cells are cultured, and two porous polycarbonate (PC) membranes between side and central chambers. Flow
dynamics analysis revealed the symmetrical velocity profile and uniform low shear rate distribution of
flowing medium inside the central culture chamber, which promotes sufficient mass transport and nutrient
supply for mammalian cell growth. A payload measurement using CSSCC device was conducted in
recoverable satellite, which validated the accessibility of the CSSCC device and provided new clues in
glucose consumption of mammalian cells.
5.9 The effect of tail-suspension on energy expenditure in mice
Tooru M. Mizuno, Peisan Lew, Davie Wong
Department of Physiology, University of Manitoba
Space travelers experience an anorexia and body weight loss while in a microgravity environment.
Microgravity-like situation produced by an antiorthostatic tail-suspension model causes changes in the
hypothalamic activity. These observations suggest the hypothesis that microgravity-induced weight loss is
due to not only reduced energy intake but also increased energy expenditure. Furthermore, the effect of
microgravity on metabolic function is mediated through specific signaling pathways in the hypothalamus.
To address these possibilities, the effect of microgravity on metabolic rates and hypothalamic gene
expression was assessed. Male C57BL/6J mice were placed in the metabolic cage system and the tail was
suspended for 3 hours to mimic the microgravity environment. Hypothalamic tissue was collected at the
end of the experiment and hypothalamic gene expression was assessed by PCR array which can screen 84
genes at once. Metabolic rates (oxygen consumption and carbon dioxide production) were significantly
increased in tail-suspended mice compared to control mice. The PCR array analysis demonstrated that tailsuspension
increased expression of several hypothalamic genes including brain derived neurotrophic factor.
These data are consistent with the hypothesis that microgravity increases energy expenditure and this effect
is mediated through hypothalamic signaling pathways. Obesity is a significant risk factor for several
serious medical problems including diabetes and cardiovascular diseases. Because obesity has reached
23

epidemic proportions in the world, there is tremendous need to better understanding of mechanisms for the
regulation of energy balance. The microgravity environment may constitute a unique and valuable
experimental system for the study of metabolic regulation and metabolic disorders.
5.10 Effects of simulated microgravity on the swimbladder and buoyancy regulation in the
zebrafish
F. M. Smith 1 , B. Lindsey 1 , T. Dumbarton 2 and R. P. Croll 2 .
Departments of Anatomy & Neurobiology 1 , and Physiology & Biophysics 2 ,
Dalhousie University, Halifax, NS
Aquatic organisms such as fishes are partially supported against the pull of gravity by a factor equal to the
volume of water their bodies displace. Many fishes also use an internal gas-filled organ, the swimbladder,
to actively regulate buoyancy to finely adjust their position in the water column. However, the effects of
reduced gravity on the swimbladder and the consequences of such effects for survival in space, where
"buoyancy" does not apply, are not understood. In the zebrafish, an extensively studied model vertebrate,
we have investigated the structure, neural control, development and function of the swimbladder in animals
raised at 1G (control group) and in animals exposed for 96 hr as embryos and young larvae to a net 0
gravitational vector in a bioreactor (experimental group). After exposure, the experimental group was
removed from the bioreactor and raised under the same conditions as the control group. Within 2-3 days
posthatch, larval zebrafish in the control group swam to the surface to inflate the swimbladder, but in the
experimental group this initial inflation was delayed by 24 hr. Swimbladders from experimental animals
examined 2 wk or longer posthatch showed no differences in anatomy, morphology, innervation, or
developmental pattern from those of the control group, nor was the behaviour of experimental animals
different from that of controls. Our results suggest that, while there may be an early effect of simulated
microgravity on timing of swimbladder inflation, this effect is transient and is not accompanied by
permanent developmental or anatomical changes in the zebrafish swimbladder.
24

6 SCIENTIFIC ABSTRACTS FOR POSTER PRESENTATION IN SPACE
PHYSICAL SCIENCES
6.1 Non-Equilibrium Solidification for Quantitative Microstructure Engineering of Ni And Al
Alloys
Hani Henein,1 Dieter M. Herlach2, Charles-André Gandin3, Asuncion Garcia-Escorial4,
1University of Alberta, Edmonton, Canada
2Institut für Materialphysik im Weltraum, Deutsches Zentrum für Luft- und Raumfahrt (DLR)
Köln, Germany, dieter.herlach@dlr.de
2Institut für Festkörperphysik, Ruhr-Universität Bochum, Germany
3Ecole des Mines de Paris, CEMEF UMR CNRS 7635, Sophia Antipolis, France
4Dept. Metalurgia Fisica, CENIM-CSIC, Madrid, Spain
Solidification is initiated by nucleation and completed by subsequent growth. In particular the growth
conditions control the microstructure evolution. If the melt is undercooled prior to solidification a system of
enhanced free energy is created that enables various solidification pathways into different metastable
solids, termed rapid solidification. Containerless processing such as gas atomization is one of the most
efficient methods to undercool metallic melts. In order to engineer the microstructure of rapidly solidified
alloys some fundamental data is necessary. In the present project electromagnetic levitation is applied both
under terrestrial conditions and in reduced gravity using TEMPUS-EML. The non-equilibrium
solidification during recalescence and segregation during post-recalescence phase is investigated and
modeled. TEMPUS-EML is equipped with Video cameras for observation of sample position and a highspeed
pyrometer for contactless temperature measurements. As an option for the future, a high-speed
camera system is considered for EML on board the ISS for measurements of dendrite growth velocities.
Levitation experiments enable the measurement of undercooling and the corresponding dendrite growth
velocity as a function of undercooling. The comparison of experimental investigations on Earth and in
reduced gravity allows for the determination of the effect of forced convection to the growth dynamics. To
solidify a spray of droplets a drop tube of 8m is used. A dedicated Impulse Atomization facility is
employed to produce powders, which are solidifying in containerless state during free fall. Non-equilibrium
effects during rapid solidification as solute trapping in alloys are investigated and analyzed within current
theories of dendrite growth.
6.2 Microgravity as an environment for growth of semiconductor nanowires
H. Ruda et al.
Centre for Advanced Nanotechnology
University of Toronto
Semiconductor nanostructures are increasingly being seen as a possible route that can take electronics
beyond the limitations of Moore's Law, with the potential for new types of devices and phenomena. Of key
importance is the ability to access regimes in which the confining dimension of the nanostructures lie
within the quantum limit. We will report on a series of terrestrial experiments that were performed showing
how high quality nanostructures of relatively large size were fabricated. We also report on a parabolic flight
campaign where our first preliminary data indicates conditions for unprecedented thin nanostructures were
achieved.
The apparatus employed for the terrestrial/parabolic flights experiments consists of a Lindberg 55035
furnace operating at 900 °C, with an inert carrier gas (argon) delivered at atmospheric pressure (nominal)
and 40 sccm (nominal), used to grow the nanostructures on silicon substrates. Analysis of the
nanostructures were done using scanning electron microscopy and transmission electron microscopy.
25

6.3 Agrégation des poudres fines en gravité réduite
C. Rioux, L. Potvin et R.J. Slobodrian
Département de physique, de génie physique et d’optique,
Université Laval, Québec (QC), Canada G1V 0A6
La formation des planètes à partir d’un nuage de poussière interstellaire est encore mal comprise. Afin de
jeter un peu de lumière sur ce phénomène, il nous apparaît pertinent d’en étudier la première étape c’est-àdire
la formation d’agrégats à partir de poudres fines. Ces agrégats formés dans un environnement de
gravité réduite sont en général de type fractal. Dans le cadre de notre étude visant à produire et à étudier les
agrégats fractals, nous avons mis au point un appareil permettant l’étude de l’agrégation des poudres fines
en microgravité. Cet appareil a été conçu dans nos ateliers et permet d’observer l’agrégation en
microgravité. Deux lentilles différentes ont permis d’afficher respectivement, avec l’aide d’une caméra
vidéo, 4 et 2 mm à plein écran. Une nouvelle version de l’appareil permet de combiner deux vues
perpendiculaires en une seule image et ainsi une reconstruction de l’événement en trois dimensions est
possible. De plus, une nouvelle caméra vidéo permet d’afficher 1 et 0.5 mm à plein écran. Les détails de
l’appareil seront présentés ainsi que les résultats d’une étude de l’agrégation d’une poudre de carbonate de
calcium en gravité réduite. Les résultats de cette étude ont mis en lumière l’importance des charges
électriques lors de l’agrégation. Nous prévoyons que l’utilisation de la version améliorée de l’appareil avec
d’autres matériaux permettra d’approfondir notre connaissance des processus en cause. De plus des
expériences sous différentes pressions allant jusqu’au vide seront nécessaire pour compléter l’étude. Une
façon de disperser des particules, dans une enceinte sous vide et en apesanteur, sera donc nécessaire et
devra être mise au point.
6.4 Propriétés optiques d'agrégats fractals à monomères nanométriques de Si
Yvanho Romanesky, Jean-Claude Leclerc, Michel Piché, Claude Rioux et R. J. Slobodrian
Département de physique, de génie physique et d’optique
Université Laval
À l’ère des communications, l’augmentation du rendement de couplage optoélectronique est un des défis
les plus importants de la physique et de l’ingénierie contemporaine. Notre groupe se penche depuis
quelques années sur l’étude de la matière fractale produite par évaporation condensation effectuée en
microgravité réelle ou simulée. Il s'agit plus précisément d’agrégats à monomères sphéroïdaux ou
microcristaux connectés à topologie fractale. Les propriétés physiques de cette matière diffèrent de la
matière ordinaire. Dans un solide cristallin, on appelle phonons les quanta de vibrations du réseau. Dans un
agrégat à monomères fractals, il existe un régime vibration où le phonon devient plutôt fracton. Le but
précis de notre recherche est de démontrer de façon théorique et expérimentale que l’interaction fractonphonon
peut être utilisée pour augmenter le rendement de photoluminescence des semi-conducteurs à
transition de bande indirecte comme le Si et le Ge. Nous avons, en outre, mis au point un modèle théorique
complet et élaboré un protocole expérimental qui nous permet de démontrer l’efficacité de cette théorie.
Notre protocole est constitué de la production de nos nanostructures, de l’observation et de l’étude
topologique des agrégats, de l’observation de la photoluminescence et de l’analyse de la composition
atomique.Le défi technique charnière dans cette étude est la production de nos agrégats. La seule façon
pour nous d’obtenir des agrégats de grandes tailles et de morphologies intéressantes pour toutes les étapes
de notre protocole est la production en impesanteur.
26

6.5 Production d’alliages binaires par évaporation-condensation laser
Jean-Claude Leclerc, Yvanho Romanesky, C. Rioux, M. Piché, R J. Slobodrian, Département de
physique,de génie physique et d’optique, Université Laval,Québec, QC
Plusieurs alliages sont difficiles, voir impossible à réaliser en phase liquide. La température de fusion d’un
élément est parfois de l’ordre de grandeur de la température d’évaporation de l’autre élément, comme c’est
le cas pour l’aluminium et le tungstène. Cela amène des problèmes d’homogénéité de la composition de
l’alliage ou bien tout simplement l’impossibilité d’obtenir un alliage entre des éléments. L’objectif final de
ce projet est de produire des alliages macroscopiques d’aluminium-tungstène en phase vapeur par la
méthode d’évaporation-condensation par laser. Le rapport des masses atomiques Al:W étant de 1:6.8, une
bonne compréhension du comportement des atomes évaporés est requise afin d’obtenir une distribution
d’énergie permettant une interaction entre les atomes Al et W. Pour la phase initiale du projet, les
expériences se sont déroulées au sol et en utilisant un laser excimer KrF à 248nm. Des alliages binaires
microcristallins d’Al-W ont été produits déjà par notre groupe en superposant les zones de condensation
des éléments. Des expériences en gravité réduites permettraient d’obtenir des cristaux de plus grandes
dimensions rendant possible l’étude de la distribution des éléments à l’intérieur des cristaux. De plus, il
serait possible d’étudier l’ajout d’éléments d’alliage à divers stade de la croissance cristalline et ainsi de
mieux comprendre l’interaction des éléments lors de la formation des alliages à partir de la phase vapeur.
L’élaboration d’un évaporateur utilisant un laser plus compact serait alors requise afin de mener à bien ces
expériences en gravité réduite.
6.6 Simulation non séquentielle des procédés d’agrégation en microgravité
Karl-Alexandre Jahjah et R. J.Slobodrian
Département de physique, de génie physique et d’optique,
Université Laval
Notre groupe de recherche se penche depuis plusieurs années sur l’étude de la matière fractale produite par
évaporation condensation effectuée en microgravité réelle ou simulée. Nous produisons plus précisément
des agrégats à monomères sphéroïdaux et des microcristaux connectés selon une topologie fractale. Les
propriétés physiques de cette matière diffèrent de la matière ordinaire à plusieurs niveaux. La plupart des
modèles de simulation d’agrégation utilisent une technique séquentielle pour créer les agrégats, ce qui n’est
probablement pas représentatif des interactions entre les différents agrégats durant l’agglomération. Nous
avons donc développé un nouveau programme de simulation basé sur un modèle balistique et qui permet
d’utiliser la force brute pour simuler l’agrégation simultanée de plusieurs milliers de monomères à
l’intérieur d’une enceinte. Le but de cette recherche est de mesurer l’impact des agrégations agglomérats à
agglomérat sur la dimension fractale et donc sur les propriétés des agrégats obtenus expérimentalement. La
nouvelle simulation permet également de tenir compte de l’inertie angulaire des particules afin de mesurer
l’impact de la rotation des agrégats sur la croissance directionnelle. Finalement, la simulation permet de
mesurer l’effet de la présence dans l’enceinte d’un gaz neutre.
6.7 Preliminary Results of Thermal Diffusion Coefficients for Different Hydrocarbon Mixtures
Experiment Flown on Board Foton M3 Mission
M. Z. Saghir*, T.J. Jaber, and Y. Yan
Ryerson University, Department of Mech and Ind Engineering, Toronto, Canada
*Corresponding author E-mail: zsaghir@ryerson.ca
Flow due to thermodiffusion may change direction in fluid mixtures with the variation of composition and
temperature. This occurrence remains an unraveled phenomenon in petroleum research. Using a modified
theoretical approach developed by Pan et al [J. of Chemical physics, Vol 126, No 1, 2007], this paper
evaluates the thermal diffusion factor in hydrocarbon mixtures (mixtures 1 and 2) and for alkanol water
mixtures, ( mixture 3). The thermal diffusion factor is compared with available ground base experimental
data and flight data. Results revealed an excellent agreement with the ground base experiment and excellent
27

accuracy of the model. In addition, the theory detected the sign change for mixture 3 when the
concentration of water is higher then the alcohol component in the mixture. TOTAL Oil Company is still
analyzing our results and it is the intention of the authors to present a preliminary results as it becomes
available. The mixtures, which will be discussed, are;
Mixture 1 Dodecane (C12), Isobutylbenzene (IBB), Tetrahydronaphtalene (THN)
Mixture 2 Dodecane(C12), n-Butane(C4), Methane(C1)
Mixture 3 Water-Isopropanol
Mixture 4 Dodecane (C12), Isobutylbenzene (IBB), Tetrahydronaphtalene (THN), Decane
All the analysis is performed at a pressure ranging from 1 bar to 350 bars with a temperature variation from
328 to 338 K. Results revealed the importance of measuring those coefficients in a convection free
environment as the one available on board FOTON M3. On the hardware aspect special discussion
focusing on the hardware development and the challenges facing the industry in achieving a successful
experiment will be discussed. In particular technological challenge such as better sealed valve to operate at
high pressure, accurate temperature sensors, efficient thermal system are some of the issue which will be
discussed in details.
6.8 The Shape of Impact Craters in Granular Media
Simon de Vet, Dr. John de Bruyn
University of Western Ontario,
Physics and Astronomy
Craters are ubiquitous on solid bodies in our solar system, but we rarely observe the formation of these
craters. We study the formation low energy impact craters in granular media, both as a model for high
energy craters on the geologic scale, and to better understand the formation of secondary craters formed
when the ejecta from a larger crater returns to the surface. We've used laser profilometry to investigate the
shape of our impact craters, and relate this to the impact parameters. We find that the shape of the resultant
crater is mostly determined by the collapse of an unstable, transient crater. To investigate these dynamics,
we sandwich a granular layer between two vertical glass plates which allows the direct observation of
subsurface flows normally hidden in 3-D. Particle image velocimetry is used to accurately visualize these
flow dynamics.
6.9 Double-helical contact processes and heat exchange
Heather-Jean May, Brian J. Lowry (presenting)
Department of Chemical Engineering, University of New Brunswick
Our theoretical and experimental results demonstrate that double-helical boundaries have broad utility in
containment of open, drainable filaments of liquid. In microgravity, loosely twisted double-helical
boundaries, such as paired springs, can support a stable liquid filament of infinite length; this contrasts well
with cylindrical liquid bridges, where a maximum length to diameter ratio of 6.28 severely limits their
utility. Unfortunately, our terrestrial experiments have necessarily been limited to liquid-liquid systems in
a Plateau tank, where it is impossible to investigate either gas-liquid interfaces or potential vibration issues
that would exist in open environments. Certain evident gas-liquid applications of double-helical
containment are open-contact processes and heat exchange, and further investigation of these will require
spaceflight experiments. The fundamentals of double-helical containment will be presented alongside two
potential spaceflight experiments that would further our understanding of the fundamentals: humidification
and liquid-metal heat exchange. As double-helical supports can be stored as compressed springs weighing
no more than a few grams, experiments on humidification would be especially straightforward. This would
clarify the long-term stability and drainability of long, supported liquid filaments (both over slow
evaporation of water) as well as the sensitivity of the filaments to flow rate (through the filament) and the
28

dependence of evaporation rate on flow and volume.
Both the humidification and liquid-metal experiments would require precision-machined helical supports,
constructed from a light spring material to permit compact storage. Humidification can be freely
investigated in open, ambient conditions, but liquid metal would require a sealed enclosure (mercury) or
300 -- 800 deg C oven (e.g. silver-copper or gold-tin alloys). The experiments are largely scaleindependent,
but the extended supports will require a space approximately 100 times the diameter in length
(20 cm by 2 mm, for example). The experiments will also require simple machinery for
expanding/collapsing the supports while simultaneously filling/emptying them from a syringe-type source.
The filling of the supports can be monitored by changes in resistance across the two helical supports, so
that no visual observation of liquid metal experiments would be required.
6.10 Microgravity double-helical fluid containment
Heather-Jean May (presenting), Brian J. Lowry
Department of Mechanical Engineering, University of New Brunswick
Double-helical containment is a novel approach to open containment in microgravity. In contrast to
axisymmetric containers there is no length restriction on properly designed double-helical containers. Use
of a double helix permits drainage to zero volume, an uncommon feature in microgravity; near-complete
drainage is a key feature for any practically useful container. That double-helical containers are open and
tubular makes possible a broad range of applications that rely on accessible fluids. Helical supports permit
filamentary containers of infinite extent, but only double-helical containers are stable down to zero volume.
The base case of symmetric supports (separation angle 180 degrees) is considered in terms of symmetric
volumes as well as asymmetric helicatenoid volumes. The distinct symmetric and asymmetric cases are
then related by perturbing the angle of separation between the supports. Helicatenoid volumes may
combine to form a dual helicatenoid volume, which is interesting in that it permits multiphase tube-like
geometries. Double-helical behaviours such as drainability are found to vanish beyond a critical separation
angle of about 246.5 degrees. A secondary shift in behaviour occurs at 209 degrees, where separate regions
of stability become more connected. The common structures of DNA coincide with the limiting geometry
at 209 degrees. Experimental results roughly verify the volume maximum for near-symmetry, and more
importantly verify stability to zero volume. Future spaceflight experiments would permit the stability of
arbitrarily long supported liquid filaments to be measured in a true microgravity environment.
6.11 Numerical Simulation of Liquid Sloshing in Microgravity
Hamideh B. Parizi 1 , Javad Mostaghimi 2
1 Simulent Inc., Toronto, Canada, parizi@simulent.com
2 University of Toronto, Toronto, Canada, mostag@mie.utoronto.ca
Sloshing occurs when a partially-filled container of liquid goes through transient or steady external forces.
Under such conditions, the free surface of the liquid may move and the liquid may impact on the walls of
the container, exchanging forces. Since every satellite or spacecraft carries liquid in form of fuel or water,
the knowledge of the behavior of liquid under such conditions is very important to help understand how
sloshing affects the attitude control of launchers and space vehicles as well as the commercial or scientific
satellites.
Sloshing is a free surface flow problem and under microgravity conditions fluid behavior is more
complicated than under terrestrial conditions, because capillary forces at the free surface could dominate
the fluid flow.
A computational fluid dynamic (CFD) code called SimSlosh has been developed in Simulent Inc., to
investigate the liquid sloshing under normal gravity as well as the microgravity conditions. The numerical
29

esults from the code have be used for optimizing the tank design and studying the different aspects of the
liquid slosh, from effects of the physical properties of liquids to the different operational conditions and
tank geometrical shapes. The code has the ability to be coupled to any dynamic code to model the results of
the forces and their effect on satellite attitude. Capillary effects are characterized by surface tension at the
liquid/gas interface and contact angle at the liquid/wall contact line. Both static and dynamic contact angle
concepts can be applied in SimSlosh code.
Although the code has been used to model liquid sloshing under microgravity conditions, the results must
be further validated using experimental results obtained through spaceflight experiments. In 2005,
European Space Agency launched a mini satellite to measure the effects of liquid sloshing under
microgravity conditions. The results of that experiment, SloshSat Flevo, are now available and have been
used by European researchers to validate their model. In addition to using those results for validating our
code, which is more accurate in terms of free surface tracking of the liquid and implementation of the
contact angle, we will propose to design and coordinate a Canadian experimental initiative for future
spaceflight experiments.
6.12 Modeling of thermodiffusion experiments for hydrocarbon mixtures and water-alcohol
mixtures On Board FOTON M3
C. Y. Yan, P. Ezzatian, T. J. Jaber, M. Z. Saghir*
Ryerson University, Dept of Mechanical and Industrial Engineering
Thermodiffusion experiments have been conducted on board FOTON Soyuz rocket in September 2007.
The space hardware used is developed by the European Space Agency. And the TOTAL Oil Company in
France is currently in the progress of data analysis. On the numerical side, we have modeled the
thermodiffusion experiments for hydrocarbon mixtures containing methane, n-butane and dodecane in
6mm experimental cells and a water-isopropanol mixture in 12mm experimental cells. Two types of
scenarios have been considered in the numerical modeling: (1) static 10 -6 g 0 ; and (2) FOTON-12 TRAMP.
Scenario (1) may be regarded as a “perfect” condition that a space experiment can possibly achieve.
Scenario (2) may be regarded as a “real” condition. Numerical results, e.g., thermodiffusion coefficient,
temperature, concentration etc., under both scenarios will be presented and discussed in detail. Based on the
numerical results, average thermodiffusion coefficients at both hot and cold side of the experimental cell
can be derived. These results may be compared with the space experimental data in the near future upon the
availability.
*Corresponding Author
Table 1: Mixtures measured and modeled onboard FOTON Satellite
Hydrocarbon mixtures (in mole fraction)
Label C1 (C 12 H 26 ) C2 (nC 4 H 10 ) C3 (CH 4 )
Mix1 0.7 0.1 0.2
Mix4 0.4 0.4 0.2
Mix5 0.3 0.5 0.2
Water-alcohol mixture (in mass fraction)
Label Water Isopropanol
W-2P 0.9 0.1
30

6.13 Diffusion in Liquids
Bjarni Tryggvason
Visiting Professor, University of Western Ontario
Canadian Space Agency
Diffusion is fundamental in heat and mass transfer and become in many experiments the dominant term in
the free-fall condition of space. While diffusion has been taken as well understood, experiments conducted
on the space shuttle and on the Russian space station in the late 1990’s demonstrate quite clear departures
from what would be predicted on the basis of ground based work. These basic results will be reviewed
along with results from ground-based work done under conditions of suppressed convection. The current
effort to replicate the results will be outlined along with some of the challenges.
6.14 The effect of gravity on flame shape and radiation in laminar diffusion flames
Marc R.J. Charest, Clinton P.T. Groth, and Ömer L. Gülder
University of Toronto, Institute for Aerospace Studies
4925 Dufferin Street, Toronto Ontario M3H 5T6
Combustion phenomena display significant changes under microgravity conditions as compared to normal
gravity flames. The major cause of these changes is the suppression of buoyancy-induced effects. At
elevated pressures on earth, the influence of buoyancy increases sharply with pressure. Therefore,
microgravity and high pressure on earth are the limiting cases for the influence of buoyancy. The findings
of the current research activity have the potential to provide tools for efficient and reliable fire safety
measures for human-crew missions in space and propulsion system design.
The main focus of this effort is the numerical simulation of laminar diffusion flames, which is complicated
by complex processes such as chemistry, diffusion, radiation, and soot formation/destruction. While several
detailed studies of laminar flames exist at atmospheric conditions, those at elevated pressures or
microgravity are limited or nonexistent. Currently, a code capable of solving laminar reacting flows with
detailed chemistry and radiation has been developed. The code makes use of a Godunov-type finite volume
scheme and a parallel block-based adaptive mesh refinement algorithm. Radiation is modelled using the
optically thin approximation, the discrete ordinates method, and the finite volume method. The statistical
narrow band correlated-k method is used to quantify gas band absorption. At present, models capable of
predicting the nucleation, growth, and oxidation of soot are being developed.
As a first step, a 2D laminar co-flow methane diffusion flame was simulated neglecting soot. Gravity was
varied from 1g to various levels of reduced gravity using several radiation models. The effects of gravity
on radiation and flame shape are reported as well as the effect of choice of radiation model. The findings
of this work and future accomplishments aim to improve our fundamental understanding of laminar
diffusion flame stability and help to formulate a potential microgravity experimental program.
An eventual flight experiment within the scope of this work would include measurement of the flame
shape, and the structure of the temperature field and soot distribution within a laminar diffusion flame
envelope under microgravity conditions. These measurements could be accomplished using a 2D CCD
camera by evaluating the spatially-resolved spectral emission from the flame. Flames would be stabilized
on a small burner of a few millimeters using low fuel flow rates such that the flame height would be about
10 to 20 millimeters.
31

6.15 Flame Propagation in Discrete, Heterogeneous Media
François-David Tang, Andrew Higgins and Sam Goroshin
McGill University, Dept. of Mechanical Engineering
A novel theoretical approach for the description of reactive waves in discrete systems has been recently
developed at McGill University. The theory predicts the existence of two asymptotic regimes of flames in
discrete media. When the flame thickness is much greater than the inter-particle spacing, the flame can be
modeled as a continuum wave in accordance to the classical flame theory. In the other extreme, a system
with rapidly reacting particles, the heterogeneous flame can no longer be treated as a continuum and
discrete effects become dominant. The effects of discreteness are characterized by a strong dependence of
flame speed on the spatial distribution of the sources (i.e., density fluctuations) and results in a flame
propagation limit that is not dictated by heat losses from the system. The theory predicts a complex
dynamics near the propagation limits manifested by a transition to chaos. Numerical simulations of the
systems with randomly distributed particles show a strong dependence of the propagation limit on the size
of the domain, characteristic of percolation-type phenomenon. Experimental observation of the flame near
the propagation limit and verification of percolation is challenging even in the reduced gravity onboard
parabolic flight aircraft due to sensitivity of the near-limit flames to g-jitters. An analysis of candidate
systems for the observation of percolating flames necessitates a long-duration, high-quality weightless
environment achievable only on orbital platforms. The proposed experimental set-up is envisioned as an
insert into the ISS Combustion Rack supplemented with a video registration complex and laser illumination
system.
6.16 High-density/low-cost micro-gravity protein crystallization methodology
Bart Hazes (Assistant Professor)
Dept. of Medical Microbiology & Immunology University of Alberta
1-15 Medical Sciences Building
Edmonton, Alberta
Micro-gravity has a theoretically well-defined benefit on crystallization by minimizing convective currents
around a growing crystal. The resulting diffusion-limited mass transport of molecules to the crystal surface
leads to crystal growth at a preferred lower level of supersaturation. Unfortunately, experiments to
demonstrate the benefit of micro-gravity for protein crystallization have had mixed results and, in general,
have failed to meet expectations. The mixed success could indicate that i) micro-gravity improves crystal
quality for some but not all proteins, ii) the technical challenges to execute experiments in a space
environment may have negated any real benefits, iii) the small number of micro-gravity experiments,
combined with inherent variability in crystal quality, is inadequate to detect systematic differences.
In the past decade, high-throughput methodologies have implemented efficient high-density, low-volume
crystallization experiments. This makes it nearly impossible for complex and costly micro-gravity
crystallization instruments to compete, unless we can transform the same high-throughput methods to a
micro-gravity-compatible format. The objective of the CSA-funded study is to develop high-density
crystallization plates that allow state-of-the-art high-throughput crystallization methods to be performed in
a micro-gravity environment. Sub-microliter crystallization drops will be kept in a frozen state until stable
orbit is reached. Crystallization is than initiated by thawing of the drops and, if desired, the experiment can
be terminated by re-freezing if required. This technology has the potential to carry out orders of magnitude
more experiments at a greatly reduced cost. In addition it avoids past problems in creating accurate ground
controls.
The current first phase research aims to find and test suitable crystallization plates, determine if freezing
itself affects crystal formation, and how cooling-rate, presence of cryo-protectants and other experimental
conditions influence the process. If successful, a second phase project, in collaboration with CSA
32

engineers, would focus on building a compact piezo-electric cooling device to advance the project to a
spaceflight experiment. This second stage would also look at vibration-isolation and, possibly, in-flight
monitoring of experiments.
6.17 Quantum Communication and SpaceQUEST
Authors: Chris Erven 1 , Raymond Laflamme 1,2 , and Gregor Weihs 1
Affiliations:
1 Institute for Quantum Computing and Department of Physics and Astronomy, University
of Waterloo, 200 University Ave W, Waterloo, Ontario, N2L 3G1
2 Perimeter Institute for Theoretical Physics, 31 Caroline St, Waterloo, Ontario, N2L 2Y5
While the origins of quantum physics are more than one hundred years old, we have only recently begun to
understand its power in information processing. Feynman was among the first to suggest that quantum
systems may go beyond those based on classical physics in a way that fundamentally changes the
representation of information. While full-scale quantum computers are still out of reach, secure
communication based on quantum physical laws is starting to become a commercial product. Yet, such
ground-based quantum key distribution (QKD) systems will not be able to go any further than 200 km,
because of the intrinsic propagation loss in optical fibers.
We have designed and built a QKD system that uses free-space optical (FSO) transmission to connect three
buildings in Waterloo. Near the ground an FSO system won’t outperform fiber-based ones due to the strong
scattering and turbulence in the troposphere. Space based systems, for example on LEO satellites may be
the only solution.
To this end and for experiments that test the very foundations of quantum physics, the SpaceQUEST
mission has been proposed to ESA by a consortium of physicists, led by Anton Zeilinger (Vienna, Austria).
ESA has funded some preliminary studies and is currently sponsoring a Topical Team that supports the
SpaceQUEST proposal. SpaceQUEST aims to put a source of entangled photon pairs into orbit, such that
two ground stations can simultaneously see the source for some time and create a secret random encryption
key. We will present our own ground-based results and how they relate to the SpaceQUEST proposal.
6.18 Durability Enhancement and Contamination Prevention for Functional External Materials in
Space Missions
Z. Iskanderova, J. Kleiman, V. Issoupov, R. Ng
Integrity Testing Laboratory Inc., 80 Esna Park Drive, Units #7-9,
Markham, ON, L3R 2R7, e-mail: ziskanderova@itlinc.com
A program was initiated at ITL to further improve the space durability and radiation resistance of
conductive and non-conductive polymer-based thermal control paints and other external space materials.
The main goal was to evaluate the enhancement of space durability and space environment resistance of the
thermal control paints and other functional external materials by innovative patented ITL technologies.
The results of surface modification of some advanced Russian conductive paints, USA and European space
paints, including their ground-based testing and performance evaluation, are presented. Results of radiation
testing are also presented for the Russian conductive paints. Functional properties and performance
characteristics, such as erosion resistance, thermal optical properties, surface resistivity characteristics of
pristine and treated materials were verified using independent testing facilities. Test results revealed that
the successfully treated materials exhibit strongly reduced mass loss or full stabilization and no surface
morphology change, thus indicating good protection from the severe oxidative environment. It was
demonstrated that the developed surface modification treatment could be applied successfully to not only
non-conductive but also to charge dissipative and conductive paints.
33

Contaminating films on spacecraft sensitive materials surfaces in many cases consist primarily of products
resulting from the interaction of atomic oxygen with silicones. Necessity of a drastic reduction of the
outgassing of volatiles and the reduction or prevention of the following contamination of the sensitive
spacecraft structures, such as containing optical and thermal control materials, has thus become a
challenging problem. The effective surface conversion of space-related silicone thermal control paints to
oxide-based protective sub-surface layers under ground-based air plasma at specific conditions, or surface
modification of various thermal control materials by specially developed ITL patented pre-treatment
technology has been researched. Complementary surface analysis techniques have been used to assess the
surface composition, bounding states re-arrangements, and atomic oxygen resistance during oxygen plasma
asher and fast atomic oxygen (FAO) testing of the treated materials.
It was shown that the application of this approach may provide the essential pre-flight surface conversion
of space materials and structures that are coated with silicone-based coatings and/or other advanced thermal
control paints to oxide(s)-based protective surface structures. Since the air plasma treatment is performed at
atmospheric pressure, this proposed surface modification technique is easy and cost-effective to apply to
three-dimensional complex shapes.
The preliminary results indicate at potential opportunities of the proposed ground-based pre-treatment
technologies to substantially reduce or prevent the contamination of spacecraft sensitive structures and
advanced thermal control conductive and non-conductive coatings by silicone-coated space materials and
drastically enhance their durability in space flights.
6.19 Impact of Gaseous and Temperature Environmental Conditions on Thermal Parameters of
Materials and Protective Structures of Satellites, Spacecraft and Landing and Re-Entry Space
Vehicles
E. Litovsky, V. Issoupov, S. Horodetsky, J. Kleiman
Integrity Testing Laboratory Inc., 80 Esna Park Drive, Units 7-9, Markham, ON,
Canada, L3R 2R7, E-mail: elitovsky@itlinc.com, Phone: 905 4152207, FAX: 905 4153633
Thermophysical properties of protective spacecraft materials determine the heat transfer, temperature, rate
of ablation, weight and safety of re-entry and planetary-landing of space vehicles.
Generally, temperature affecting the spacecraft materials can be from -200°C up to materials’ melting point
(>2000°C), the gas pressure ranges from 10 -6 Pa to 10 7 Pa. Extensive experimental data have shown that
high vacuum conditions, gas pressure and temperature changes in space and during the landing and re-entry
phase of spacecraft can dramatically influence (5-10 times) the materials thermal conductivity. These
variations are explained using the classical (conduction, radiation, gas convection) and novel heat transfer
mechanisms in the materials.
The first group of heat transfer mechanisms includes the heterogeneous heat and mass transfer process in
pores and cracks, including the phenomenon of gas transport (gases are produced due to gas emission,
evaporation and sublimation). The grain boundary segregation and diffusion of impurities can influence the
thermal conductivity of dense oxide materials and metals.
The second group of mechanisms deals with phenomena that involve a mismatch between the thermal
expansion coefficients of different materials.
Experimental methods and analytical technique are being developed for measurement of the materials
thermal conductivity and diffusivity. The experimental technique applied to studying the thermal physical
properties employs either monotonous heating of samples or steady-state analysis of the involved heat
transfer mechanisms.
In this paper, a review and analysis of the described above problems will be made, with an emphasis on
description and explanation of typical experimental results.
34

7 SCIENTIFIC ABSTRACTS FOR POSTER PRESENTATION IN SPACE
LIFE SCIENCES
7.1 Canadian experiments in European bed rest studies, WISE-2005 and ESA-2008
Richard L Hughson 1 , J. Kevin Shoemaker 2 , Philippe Arbeille 3 , Danielle K. Greaves 1 ,
Marc-Antoine Custaud 4 , Reginald Gorczynski 5 and David Hart 6
Universities of Waterloo 1 , Western Ontario 2 , Toronto 5 , Calgary 6 and Tours 3 and Angers 4 (France)
The Women’s International space Simulation for Exploration (WISE) was a 60-day head down bed rest
completed in 2005 by 24 women with or without countermeasures of exercise or nutrition. The objectives
of the Canadian research team were to examine structural and functional changes in the cardiovascular
system that might contribute to the deconditioning responses noted with long-duration space travel. We
used non-invasive technologies including ultrasound and blood pressure measurements to characterize the
changes in cardiovascular properties. To date 4 full journal papers have been published along with many
conference presentations. We observed poor tolerance of the upright posture after bed rest but with benefits
of countermeasures that consisted of supine treadmill running inside a negative pressure box and heavy
resistance exercise. We did note however a very wide range of individual responses that suggest genetic
variants. The data from this study can be applied to astronauts but also to the aging population of Canada
who are also at greater risk for fainting and falling.
The ESA-2008 studies will examine the role of inflammatory processes in the progression of
cardiovascular, bone and muscle changes with short-duration (5-days) bed rest in men. Countermeasures
are planned to be artificial gravity with a short-radius centrifuge.
The inflammatory process plays a key role in disease states including development of atherosclerosis and
osteoporosis. The planned experiments will utilize existing techniques to monitor blood markers of these
processes. Future space flight studies cannot use these laboratory-based techniques but could benefit from
micro-technologies for rapid analyses. Our work also depends on non-invasive cardiovascular monitoring
with ultrasound or other imaging techniques.
7.2 Canadian bed rest experiments – study of the NASA fluid loading protocol
Richard L Hughson 1 , J. Kevin Shoemaker 2 , Danielle K. Greaves 1
Universities of Waterloo 1 and Western Ontario 2
NASA currently recommends that astronauts consume water and salt tablets immediately prior to return
from space in an attempt to increase blood volume. It is proposed that this will support the cardiovascular
system on return to Earth and that it will reduce the chances of fainting. We are currently investigating this
hypothesis using models of 28-hours or 4-hours of bed rest. Previous research in our lab has shown that
there is a marked reduction in tolerance of the upright posture or application of lower body negative
pressure after only 4-hours of head down bed rest. We are further investigating the mechanisms responsible
for poor cardiovascular responses by examining the changes in cardiac output by different non-invasive
methods including ultrasound. Blood measurements of hormones involved in fluid regulation will be
completed.
The results of this study can have important implications for the elderly population as they frequently spend
both short and long periods of time in bed and often suffer from dizziness and fainting on rising from their
beds.
References
Butler, G.C., H.C. Xing, D.R. Northey and R.L. Hughson. Reduced orthostatic tolerance following 4 h 6°
head-down tilt. Eur. J. Appl. Physiol. 62: 26-31, 1991.
35

Fischer D, P Arbeille, JK Shoemaker, DD O’Leary, RL Hughson. Altered hormonal regulation and blood
flow distribution with cardiovascular deconditioning after short-duration head down bed rest. J. Appl.
Physiol. 103: 2018-2025, 2007.
7.3 Research Activities in Radiation Exposure of Space Crew
B.J. Lewis and L.G.I. Bennett
Royal Military College of Canada,
Kingston, Ontario K7K 7B4
K. Garrow and H. Ing
Bubble Technology Industries
Chalk River, Ontario K0J 1J0
The complex space radiation environment offers significant challenges for the dosimetry of space crew
workers. Research activities will be discussed including the calibration of radiation instruments based
on ground-based accelerator studies. This calibration work has focused on neutron dosimetry and
spectrometry for space field application. In particular, ground-based accelerator studies have been
carried out with the nuclear fragmentation separation experiment (NFSE) (with a capability for
charged particle discrimination), a bubble detector spectrometer (BDS) and neutron-sensitive bubble
detectors at the CERN, HIMAC and TRIUMF facilities. Additional work at the PTB and iThemba
laboratories has involved the calibration of the Canadian High Energy Neutron Spectrometry System
(CHENSS) for space application. Various equipments have also been tested at aircraft altitudes.
The development of a novel, biologically-based, device for mixed-field measurement will also be
described. This device may enable personal dosimetry through the recognition of DNA damage (i.e.
single and double strand breaks). A polymeric biosensor is employed to detect all types of radiation of
varying quality and linear energy transfer. Such a device may find particular application on long
duration space missions.
36

8 SPACE AGENCY ABSTRACTS
8.1 Recent Successes in NASA’s Gravity-Dependent Physical Sciences Research Program on the
ISS
Fred J. Kohl 1 , Francis P. Chiarmonte 2 , and Thomas H. St. Onge 1
1
NASA Glenn Research Center, Cleveland, OH, USA
2 NASA Headquarters, Washington, DC, USA
Physical sciences research conducted on the International Space Station (ISS), free flyers or the ground in
the recent past, currently, and planned for the future supports NASA programs in both “Exploration
Research” and “Non-Exploration Research.” The Exploration Research Program aims to fill identified
knowledge gaps required to enable new technologies necessary to support NASA’s planned exploration
missions. The Non-Exploration Research Program is a continuation of the heritage Microgravity Science
Research Program that utilizes the uniqueness of the microgravity and space environment to unmask
phenomena that cannot be observed or studied in the normal Earth environment. The goal of these current
programs is generate research data from science and technology experiments and advance the broader
NASA Exploration Program capabilities by supporting a core group of principal investigators, providing
ground-based facilities and space flight hardware. The “Physical Sciences” referred to herein that comprise
Exploration and Non-Exploration research are derived from the main gravity-dependent aspects of the
traditional disciplines of fluid physics, combustion science and materials science.
Summaries of significant results will be presented from several instruments and experiments conducted
over the past six years of ISS operations. Descriptions will be presented of the capabilities of the major
NASA–developed facilities utilized on the ISS: currently, the ExPRESS Racks, the Microgravity Science
Glovebox (MSG), and the Maintenance Work Area; soon to be utilized, the Combustion Integrated Rack
(CIR), the Fluids Integrated Rack (FIR) and the Materials Science Research Rack (MSRR).
The ISS Traffic Model for physical science experiments and plans for future ISS-based experiments for
both Exploration and Non-Exploration research will be discussed.
8.2 The ESA program in physical sciences in the framework of the ELIPS-ARISE program
research including applications on the ground and in space
O. Minster*, L. Cacciapuoti, D. Jarvis, N. Lavery, S. Mazzoni, O. Minster,
K. Norfolk, A. Orr, A. Pacros, S. Vincent-Bonnieu, D. Voss
Olivier.Minster@esa.int
Physical Sciences Unit
Directorate of Human Spaceflight, Microgravity and Exploration Directorate,
ESA-ESTEC
Keywords: programme in physical sciences, space environment, basic research,
industry relevant research, exploration preparation
ESA has developed a broad set of research activities in physical sciences activities in the framework of the
European Life and Physical sciences in Space (ELIPS) programme of ESA.
Research projects incubated and consolidated in the context of Topical Teams supported by ESA and
eventually submitted to regular Announcements of Opportunity have been selected on the occasion of 3
consecutive Announcements of Opportunity between 1999 and 2004.
These projects that involve team of European, Canadian scientists span over several years and make an
optimal use of the various platforms available to ESA. A large number of these projects will eventually
have dedicated instruments flown on the International Space Station as of early 2008, right after the launch
of the Columbus laboratory.
37

The programme is organised in rather classical research cornerstones, namely
• Fundamental physics (quantum sensors, complex plasmas, dust particles physics and space-atmosphere
interactions),
• Fluid physics (structure and dynamics of fluids, multi-phase systems and interfaces, combustion),
• Materials sciences (materials designed from fluids, thermo-physical properties of fluids to support
advanced processes)
The projects covered by this research plan span basic and applied research, with in a number of cases,
industries associated to the teams running these projects. This industry support has been sustained through
significant delays incurred with the building of the ISS thanks to the alternative opportunities that ESA
could secure on other platforms.
In developing this programme, ESA has maintained high the cooperative spirit that prevailed in the
development of the ISS project. Beyond the “institutionalised” cooperation with Canada through a direct
participation in the ELIPS programme, cooperative projects with NASA could be pursued, as well as with
Russia. The close collaboration with JAXA also enabled the promotion of a number of International
Topical Teams that, we jointly trust, will demonstrate the full potential of cooperation between ISS partners
in maximising the return on investments in scientific instrumentation.
An additional element of the programme is progressively developing, that capitalises on the experience and
knowledge of the scientific community currently active in the programme. As any new technology
development requires a solid scientific basis, initiatives are taken to incubate projects that address more
particularly the science at the basis of the future technologies that are anticipated to be required to support
any manned space exploration programme.
This element of the programme should not be seen as a dramatic change of emphasis in the current ESA
programme, but as the development of a knowledge-based technology maturation activity anticipating on
the future of human spaceflight programmes.
8.3 Sciences de la Matière, CNES
B. Zappoli
Scientifique de programme
CNES, Toulouse, France
Contenu du poster:
-Les enjeux et besoins associés
-Les missions en cours; programmées; probables
-Le positionnement potentiel CNES, Français (labos, industriels), Européen
-Les exigences critiques futures et les Infrastructures clés
-Les compétences indispensables
-Représentation graphique
8.4 On-board Experimental Study of Bubble coalescences and Bubble Oscillations in the
Recoverable Satellite
Q. KANG H.L. CUI L. HU L. DUAN
National Microgravity Laboratory/CAS; Institute of Mechanics,
Chinese Academy of Sciences, Beijing 100080, China ( kq@imech.ac.cn )
Some results on bubble interaction in microgravity are presented in the paper. The microgravity experiment
was performed on board the Chinese 22nd recoverable satellite. In the space experiment, Bubble
coalescences are observed through the bubbles staying at the upper side of the test cell in the experiment.
Reduced gravity is the only way to observe the coalescences of large spherical bubbles without deformation
38

of shape. It is the first time to obtain the detail results of coalescences of large size bubbles in reduced
gravity. The relationship between coalescence time and size of bubbles is analyzed. The bubble oscillations
due to bubble coalescence were researched. The periodicity of bubble oscillation was proved with two
dimension cross correlation to images; the period of bubble deformation was obtained with Fourier analysis
to correlation coefficient, and the period is compared with the theory predicted by Longuet-Higgins(1989).
It was displayed that the part of high frequency in the surface wave during bubble oscillation increased with
the bubble size. But there was still some deviation between the experimental data and the predictions.
8.5 Foton-M3: Technological and Operational Constraints in Meeting Scientific Objectives
A. Verga 1 , J. Winter, R. Demets, P. De Gieter,
European Space Agency (ESA)
European Space Technology and Research Centre (ESTEC)
Directorate of Human Spaceflight, Microgravity and Exploration
Microgravity Payloads and Platforms Division
Noordwijk, The Netherlands
ESA’s scientific programme of microgravity experiments was hit by two significant setbacks, the FOTON-
M1 launch accident on October 15 th , 2002 and the loss of the Columbia Space Shuttle, minutes before its
scheduled landing on February 1 st , 2003. ESA wanted to adhere to established practice, i.e. to re-fly
missions or experiments, which are not successful due to system failures. Immediately after these
accidents, ESA began to study the possibility of re-flying most of the experiments, explored the availability
of spare or qualification models of the lost payloads, and assessed with the industrial partners the effort
necessary to upgrade any existing model to flight standard or to re-build new flight H/W, as appropriate.
The survey was extended to other national agencies like CSA, CNES and DLR, ESA’s partners in previous
FOTON missions.
The tragic loss of the U.S. Shuttle Columbia pressed ESA to look for re-flight possibilities of the STS-107
experiments. The main conclusion was that, in view of the nature and the size of the payloads, a FOTON reflight
was the best option. Driven by these facts, the negotiations with Russian partners led to a commonly
accepted understanding for the contractual and utilisation details of two FOTON missions, their payload
complement and their launch schedule. An agreement was then reached in October 2003, and subsequently
amended in November 2005, for an overall ESA payload mass of about 700 kg, lately increased to 800 kg,
distributed over two flights, FOTON-M2 and FOTON-M3, with launch dates on May 31 st 2005 and
September 14 th 2007, respectively.
ESA has been using FOTON and BION since 1987 for its physical science and life science experiments.
Several ESA instruments, specifically designed for FOTON/BION, had flown aboard these spacecraft.
FOTON-M2 lifted-off from Baikonur for the first time in the FOTON history. FOTON-M3, also launched
from Baikonur was the twelfth such missions that ESA has been involved in, with a total payload mass of
almost 400 kg, and brought back a substantial deal of scientific and technological results. The Russian
FOTON and BION spacecraft, conceived to conduct mainly experiments in weightlessness, have been
designed and built by the Central Specialised Design Bureau of the State Research and Production Space
Rocket Centre (TsSKB-PROGRESS), in Samara (Russia) and made the first flight in 1985.
This talk presents the main features and the preliminary results of the FOTON-M3 mission, and addresses
the challenge of developing and operating payloads to meet a wide range of scientific objectives in both life
and physical sciences within the given technical and logistical constraints. Thanks to the long-standing
experience with these missions, to their unique flexibility and typical features, and to their educational
value, ESA is drawing plans to continue the exploitation of FOTON and/or BION for an even larger breadth
of users, where highly ranked experiments benefit of the excellent microgravity conditions that such
platforms guarantee.
1 Tel. +31-71-565-3098; Fax. +31-71-565-3141; e-mail antonio.verga@esa.int
39

9 TECHNOLOGY DEVELOPMENT ABSTRACTS FOR ORAL
PRESENTATION IN SPACE PHYSICAL SCIENCES
9.1 An Application of Hardware Development for Microgravity Research
Stephen Churchill, C-CORE, St. John’s, NL, Canada, stephen.churchill@c-core.ca
Gerald Piercey, C-CORE, St. John’s, NL, Canada, gerald.piercey@c-core.ca
The Soret Coefficients of Crude Oil (SCCO) experiment is multi-flight set of fluid physics microgravity
experiments representing a series of collaborations between the Canadian Space Agency and the European
Space Agency.
The scientific objective of the experiments is to increase our understanding of the transport of fluids within
oil reservoirs which will lead to improving methods for enhanced oil recovery. Specifically, the SCCO
experiment attempts to determine the Soret Coefficient of specific samples, including hydrocarbons.
C-CORE (St. John’s, NL) designed and constructed the control electronics and software which then
combined with fluid sample containers constructed by Verhaert Aerospace of Belgium. This and similar
configurations were flown on the Russian Foton M1, M2, and M3 scientific research satellites. These
experiments and the research program which they represent are strongly supported by academia and
industry, including Ryerson Polytechnic University and the Microgravity Research Center in Belgium.
The latest successful flight of the SCCO experiment was completed in September of 2007. The sample
mixtures were placed under a thermal differential for 200 hours, returned to earth and recovered. Each of
the seventeen samples was divided by a valve while in flight and all are currently being analyzed to
determine the results of diffusion.
Technical challenges included the storage of samples under high pressure, the establishment and
maintaining of steady state temperature differentials for long periods via control algorithms, heater control,
bidirectional thermoelectric cooler and motor control, accurate measurement and monitoring of
temperatures and power consumption, as well as autonomous and interactive telemetric experiment control.
This presentation details scientific requirements, how these were met for the Foton M3 flight of the SCCO
experiment, the operational results of the flight and a summary of the scientific results to date.
9.2 System Identification and Performance Testing of the Microgravity Vibration Isolation
Subsystem (MVIS) for the European Space Agency’s Fluid Science Laboratory
Authors: Derrick Piontek 1 , Jean de Carufel 1 , Michael Labib 1 , Nicolas Valsecchi 2
1 Bristol Aerospace Limited / Magellan Aerospace Corporation, Ottawa, Ontario, Canada
2 Canadian Space Agency, St-Hubert, Québec, Canada
Building on the successes of the Canadian Space Agency’s Microgravity Vibration Isolation Mount (MIM)
technology aboard both the US Space Shuttle and the Russian MIR space station, the Microgravity
Vibration Isolation Subsystem (MVIS) is the third generation of the MIM technology. Integrated within
the European Space Agency’s (ESA) Fluid Science Laboratory (FSL), which was successfully delivered to
the International Space Station (ISS) during the US Space Shuttle flight STS-122, the MVIS is designed to
actively isolate the FSL’s Facility Core Element (FCE) from vibrations in the ISS. The system is based on
a six degree of freedom (6DOF) magnetic levitation (MAGLEV) scheme using wide gap actuators whose
magnets and coils are located on the FCE and the FSL respectively.
40

The FSL facility is designed to study the dynamics of fluids in the absence of gravitational forces and
houses individually developed Experiment Containers (EC). The ECs can utilize the standard FSL utilities
and diagnostics along with the MVIS for a reduction in the vibratory environment. This isolation from the
surrounding vibrations is important for many experiments including the study of multi-phase flows and
diffusion-controlled heat/mass transfer in crystallization processes. CIMEX-1, part of the ESA CIMEX
Migrogravity Application Promotion (MAP) project to study dynamics of evaporating liquids, is the first
EC slated to utilize the isolation capabilities of MVIS.
MVIS has been designed to isolate experiments from vibratory accelerations greater than 0.01 Hz.
However the isolation performance of the MVIS is directly related to the FSL umbilical stiffness, the bias
forces required to maintain the FCE in a centered position, the level of disturbances on the FCE, and the
presence of umbilical dynamics that are difficult to characterize. The FSL umbilicals, the electrical
harnesses and air/fluidic cooling lines connecting the isolated FCE to the FSL, are the primary points of
concern for the analysis. An extensive effort has been undertaken to identify the FSL umbilical stiffness
and bias. This includes the creation of a simulated umbilical model using FSL design data, the creation of
numerical models, 6DOF ground based testing of the FSL flight model and simulated umbilical model
using custom designed balancing beams and test rigs, along with parabolic flight testing of the simulated
umbilical model on the ESA Zero-G Airbus A300. The MVIS performance is then estimated using the
results of the testing paired with a high fidelity simulation of the MVIS system.
Bristol Aerospace Limited, a division of Magellan Aerospace Corporation, is responsible for development
of elements of the MVIS including system integration and performance testing. This paper will give an
introduction to the MVIS system, present the findings of the system identification and performance testing,
summarize the activities undertaken and recommended to reduce the FSL umbilical stiffness and improve
isolation performance, and provide an overview of the on-orbit activities used in the identification and
commissioning of MVIS.
9.3 Space-DRUMS® - Facility for the ISS
Guigné International Ltd (GIL)
Dr. Jacques Guigné
Colorado School of Mines
Dr. John Moore
Sponsor: NASA Innovation Partnership Program.
Scheduled operation for ISS late 2009 to 2014. Space-DRUMS is a full rack facility occupying an
EXPRESS rack and uses acoustics to position objects inside its processing chamber.
Designed to operate on the ISS over long periods with minimum astronaut support using TREK
commanding and making functional changes by simple ground-based software commands. Materials for
processing transported in carousels.
Availability to ground-based equipment to universities and laboratories GIL Stairwell approach for ground
studies to space
Ground based chambers
COSYM facility: Parabolic Aircraft
Single Axis Levitator: Ground based, parabolic flights
Space-DRUMS® on ISS
Possible future facility on the Moon
Instrumentation includes:
Temperature measurement up to 2500°C
Video data in visible (CCD) and thermal infrared
Triple containment for safety
41

Independent modular construction with standard connectors; each unit can be shared by other ISS payloads.
Designed to produce lighter, stronger, harder and higher temperature resistant materials, either dense or
porous
Develop processes that reduce spacecraft weight and power consumption and for using in-situ resources
Perform experiments with high scientific merit
Involve students and industry to participate
List of possible candidates- both process and advanced materials in space, focus has been on the use of
Moon regolith
•Glass, IR Glasses, Glass ceramics
•Ceramic foams, Metal-Ceramic foams for structures
•Filters
•Acoustic abatement in high temperature applications
•Bone replacement
•Drug delivery systems. (Diabetes, schizophrenia, osteoporosis)
•Cutting tools
•Wear resistant parts
•Armor
•Farm machinery (related to cutting and wear)
•Automotive (Brakes, ball joints, hubs, coatings, weight reduction program)
•Crack repair
•Brazing
•Coatings
•Fire extinguishing
9.4 A Historical Review of Space Instrument Technologies Developed by Routes
AstroEngineering and Used to Support L&PS Scientific Mission Objectives
B. Gordon, W.F (Tory) Payne, K. Smith, L. Piché, G. Barnes
Routes AstroEngineering
303 Legget Drive, Ottawa, Ontario, Canada K2K 2B1
Since our inception in 1988, Routes AstroEngineering has supported Canadian Scientists in achieving their
scientific research objectives in Life & Physical Sciences research by developing space science
instrumentation ‘from Concept to Flight”. Routes AstroEngineering has been involved in the development
of L&PS instruments designed to be flown on parabolic, shuttle, and ISS/MIR platforms. Some of the
L&PS programs supported by Routes include: ARF-II, MIM-II, ATEN Furnace, Insect Habitat, Advanced
Animal Habitat (Orbitec/NASA-Ames), PMDIS-TRAC, and IML-SPE. Each instrument, designed to
operate in a microgravity environment, was tailored to meet the unique requirements of the science being
investigated. Technologies employed included: Wide field-of-view optics, high-resolution/high-speed
video imaging systems, near-lossless science data compression, environmental control systems
(temperature, humidity, illumination, food exchange), fluid containment systems, programmable
centrifuges, microgravity isolation mount design, high temperature furnace conceptual design, and adding
touch-screen capability to the official ISS laptop.
42

9.5 Canada’s Heritage and Experience with Operations and Hardware Development within the
ISS Program
Richard Rembala, Mike Daly, Nadeem Ghafoor
MDA, 9445 Airport Road, Brampton, Ontario, Canada, L6S 4J3
Tel: 905-790-2800 x4908, Fax: 905-790-4420
E-mail: richard.rembala@mdacorporation.com
Canada’s long-awaited 3 rd and final infrastructural contribution to the International Space Station (ISS) will
be delivered in Spring 2008 with the launch of the Special Purpose Dextrous Manipulator (SPDM).
Canadian participation on ISS will increasingly now include a utilization component, with opportunities for
life and physical sciences research as well as technology demonstration and validation. The development,
delivery and operation of hardware and experiments for the ISS however carries specific challenges unique
to a manned spaceflight program. Fortunately this is an area of particular Canadian experience, and a clear
opportunity exists to now combine the expertise gained from decades of infrastructure provision with the
life and physical sciences research now being proposed for ISS utilization.
Together with the Canadian Space Agency and the National Research Council of Canada, MDA has over
twenty-five years of experience in space flight hardware production and real-time flight operations support
to Shuttle (Canadarm) and ISS (Canadarm2) robotic operations, beginning with the second shuttle flight
STS-2 back in 1981. In this capacity, Canadian engineering and management teams have become familiar
with the challenges, hurdles and gates involved in designing, testing, and delivering hardware for flight
onboard the International Space Station that satisfies NASA’s strict safety, reliability, material, and
environmental requirements.
From environmental testing at the David Florida Labs in Ottawa, to certifying hardware with the NASA
Safety Panel at the Johnson Space Center, this paper will address the challenges Canada and MDA have
faced and the experiences gained in developing space qualified hardware for both utilization within the
habitable interior and on the unpressurized exterior of the ISS. Furthermore, the infrastructure and skills
necessary for transitioning from the production phase to the operational/sustaining engineering phase of a
hardware’s life-cycle will be discussed.
9.6 Configurable Miniature Laboratory for Space Science and Materials Processing
Roman V. Kruzelecky, Brian Wong, Jing Zou, Emile Haddad, and Wes Jamroz
MPB Communications Inc., 151 Hymus Blvd., Pointe Claire, Quebec, Roman.Kruzelecky@mpbc.ca
Space-based physical sciences generally require a suite of complementary measurements to study the
evolution of the experiment or physical process. However, space-based instrumentation must also consider
the mass and power penalties associated with launch costs. MPBC’s innovative approach to meeting the
science measurement requirements while also minimizing the instrumentation mass and power is to employ
advanced guided-wave and fiber-optic sensor technologies. This allows a suite of complementary miniature
instruments to be accommodated within a typical international space station (ISS) mid-deck locker that can
be configured to meet the monitoring requirements of a specific physical experiment.
The MPBC suite of complementary miniaturized measurement technologies include MPBC’s patented
IOSPEC technologies for high-performance guided-wave spectrometers and an array of leading-edge fiberoptic
sensors and lasers. The optical sensing has the benefits of being immune to EMI and requires minimal
consumables. The instrument suite can be configured to meet specific measurement requirements in the
vapour, solid or gas phases.
The core infrared (IR) spectral processor is based on MPBC’s IOSPEC technology for guided-wave
spectrometers. This has been advanced to provide high performance comparable to large laboratory
spectrometers but in a compact footprint weighing under 2.0 kg. The integration of the spectrometer optics
using a low-loss IR waveguide structure provides robust optical alignment and facilitates optimization of
the output focal plane and detector array coupling with minimal optomechanical components. The
43

spectrometer employs a precision master grating micromachined in thin silicon that provides atomically
smooth grading elements to provide a background signal scattering below 0.05% while affording a 4000
nm broad spectral range of operation in first order diffraction with achievable spectral resolutions to below
4 nm. Additional optical signal filtering can provide spectral resolutions below 0.05 nm FWHM for gasphase
applications. Smart multichannel optical signal processing and dark signal compensation have been
developed by MPBC for IR linear arrays that can provide over 60 dB of dynamic signal range to enable
trace detection. Multiple spectrometers can be accommodated within a single ISS mid-deck locker,
optimized for specific measurement tasks and spectral resolution requirements to provide substantial data
synergy.
The guided-wave spectrometer is being integrated with a bore-sight CMOS micro-imager as part of the
development of a miniature instrument suite for planetary exploration and the requirements of the potential
Inukshuk landed Mars mission. This provides the added capabilities of visual inspection of the sample, or
process, in addition to the IR spectral analysis and the fiber-optic process-specific sensors.
A low-power multichannel fiber-optic sensor system, Fiber Sensor Demonstrator (FSD), has been
developed and ground-qualified towards a flight demonstration on ESA’s Proba-2. This provided the
development and ground qualification of a tuneable fiber-laser and various fiber-optic sensors for
distributed temperature and process pressure measurement. Sensor parallel and WDM serial multiplexing
allows a large number of fiber-optic sensors to be operated from a single compact interrogation system. A
low-power (< 3 W) microprocessor and 16 bit multichannel data acquisition system has also been
developed for the FSD that has already undergone substantial ground qualification; including random
vibration to 16.2 g rms and TVAC operation from –40 to +60 o C. This is currently being adapted to operate
MPBC’s miniature IR spectrometer system and upgraded to include 4 Gigabytes of flash memory data
storage with fault-tolerant management.
Acknowledgements
The authors would like to gratefully acknowledge the financial assistance of the Canadian Space Agency
for aspects of this work.
9.7 PCS: An Example of Collaboration between Engineers and Scientists
Dr. Arthur E. Bailey
Scitech Instruments Inc.
North Vancouver, BC, Canada.
Technology and engineering enable successful space science. The Physics of Colloids in Space (PCS)
experiment operated successfully for eight months on the International Space Station. Although similar
experiments flew several previous missions, PCS was the most successful. PCS benefited from the previous
generations, but the final generation was significantly more sophisticated and flexible. Not only did the
system require integration of a wide variety of technologies, but it yielded high quality scientific results
because of the communication and cooperation of the engineering team with the science team. Clear
examples of the technology, good design choices and teamwork during this project will be discussed.
44

10 TECHNOLOGY DEVELOPMENT ABSTRACTS FOR ORAL
PRESENTATIONS IN SPACE LIFE SCIENCES
10.1 Advanced Miniature IR Spectral Processor for Remote Astronaut Health Diagnostics
Roman V. Kruzelecky, Brian Wong, Jing Zou, and Wes Jamroz
MPB Communications Inc., 151 Hymus Blvd., Pointe Claire, Quebec
The detection and identification of molecular structures is a vital component of space exploration for
atmospheric studies, planetary geology, and astrobiology. It is also an important requirement for manned
missions in space for the monitoring of vital life-support systems (such as the air and recirculating water
systems), detection of potential biohazards, as well as remote diagnosis of the astronaut’s health. The
significant advantage of the Infrared (IR) spectral technique is that it can be used with minimal
consumables to simultaneously detect a large variety of different chemical and biochemical species with
high chemical specificity. IR-based analysis is founded upon the spectrum of IR absorption bands that are
characteristic of the analyte itself. It is being increasingly used for clinical analysis of human serum and
tissue. This has allowed quantization of glucose levels, cholesterol, total protein and other components of
biological fluids. For remote astronaut health monitoring; a liquid analysis system can be used to monitor
saliva and urine relatively unobtrusively to provide comprehensive medical diagnostics that are capable of
detecting a wide range of potential medical problems. The science objectives are to validate a miniaturized
suite of complementary spectral instruments with associated sample interface for biological fluids for
remote uninvasive health monitoring and to use these capabilities to provide in situ studies of the effects of
space and low gravity on human metabolisms.
For space-based systems, the important drivers are reliability, power consumption, mass and simplicity of
operation. A monolithically-integrated suite of miniature instruments is currently being developed for the
Canadian Space Agency based on MPBC’s patented IOSPEC technologies for high-performance guidedwave
spectrometers to enable laboratory-quality remote chemical and biochemical analysis. The
application of this technology to provide a compact integrated lab of complimentary instruments for
comprehensive biomedical analysis is discussed. As part of the experimental predevelopment of the
miniature chemical analysis instrument suite, a laboratory test set up was prepared focusing on spectral
measurements of a set of reference powdered and liquid samples. The complete system entails a miniature
light source, signal collection optics, data processing electronics, and a fluid handling system.
Microphotonic and MEMS technologies can play a role in the miniaturization of the various subsystems
using microfluidic channels, optical waveguides and integrated-optic sensors. The diagnostic capabilities
can be extended by combining IR spectroscopy with complementary IR Raman detection of C-C bonding
and other IR inactive biomolecular vibrational modes.
10.2 Rapid microbial DNA detection on compact disc: potential applications on spaceship
Michel G. Bergeron
Presented by Eric Leblanc
The National Aeronautics and Space Administration (NASA) aims at establishing a presence on the moon
as early as 2015 and sending humans to Mars by 2025. As astronauts begin to venture beyond low Earth
orbit, the effective detection and treatment of infection in space will become a challenge which demands
collaboration between multiple fields such as microbiology, pharmacology, chemistry and physics. Culturebased
methods are not suitable for the detection of microbial cells onboard a spaceship. Current molecular
assays run on bulky apparatus not compatible with limited space environments. Thus it would be desirable
to develop a rapid and automated method that could detect infections directly from a biological specimen
onboard a spaceship. Microfluidics technologies offer the possibility of detecting nucleic acids released by
microorganisms on small compact devices.
45

The Centre de Recherche en Infectiologie (CRI) of Université Laval in Québec City is developing an
integrated, fully automated, affordable, and single-step portable microfluidic laboratory-on-a-compact disc
(lab-CD) device for the rapid (

10.4 eOSTEO – Automated Closed Culture System for Study of Bone Cells in Microgravity
Author: Lowell Misener, Chris Adamson, Dennis Sindrey
Affiliation: Systems Technologies, Kingston Ontario
The original OSTEO system was a turnkey cell culture and support system for use in terrestrial and
microgravity experiments involving bone cell activity. The system was designed for short-term Shuttle
experiments lasting approximately 10 days. The OSTEO system was successfully operated on STS-95 and
STS-107 in which Canadian and European investigators used a synthetic bone substrate to study and
quantify bone cell activity and evaluate potential anti-osteoporosis treatments.
As a result of the tragic loss of the Shuttle Columbia and the desire to continue the support for the OSTEO
science, the eOSTEO system was created as a fully automated version with specific customization for the
unmanned Russion Foton satellite.
The goal of this presentation will be the review and discussion of the system and system capabilities to
conduct cell culture science in microgravity and on the bench. In addition, efforts responsible for the
hardware development considering the interactive design and testing of the cell culture fluid pathway will
be presented (OSTEO fluid pathway design “Grandfathered” for eOSTEO). This will also include a review
of the recent performance on the Foton M3 satellite (Launched September 2007) and future considerations
for more advanced science.
10.5 Micropackaging technology of microbolometer FPA enabling the miniaturization of mid-IR
instruments for space exploration missions
S. Garcia-Blanco, P. Topart, L. Marchese, T. Pope, C. Alain, H. Jerominek
INO, 2740 Einstein Street, Québec, Canada G1P 4S4
INO has a large experience in the development of microbolometer FPA arrays for various types of space
exploration missions. Under the current sponsorship of CSA, INO has developed a custom 512x3 pixel
microbolometer detector array for satellite-based thermal imaging applications, including cloud and earth
surface temperature monitoring and forest fire detection and monitoring. The detector array has been
selected for the NIRST instrument on the SAC-D satellite. In addition, INO is currently developing a
compact low-cost Earth horizon sensor based on their 256x1 pixel microbolometer detector array. The
design has been optimized for use on small (nano) satellites in low Earth orbits.
Reduced footprint, weight and power consumption are essential requirements for instruments to be
incorporated in nano-satellites or exploration rovers. Those requirements are also important for instruments
to be used in the ISS since the availability of space is limited.
INO has recently developed a hermetic vacuum micropackaging technology for its microbolometer FPA
that allows reducing the size of the package from 26x30x4 mm 3 to 10x10x2.5 mm 3 with the consequent
reduction in weight from 12.8 g to 0.53 g. Combined with INO’s recent developments in micro-assembly of
miniaturized optical and micro-optical components as well as its large experience in radiometric packaging,
the micropackaging technology will enable the development of miniaturized instruments for multiple space
applications for which footprint and weight are issues. Such applications include mid-IR spectral analyses
both for health monitoring and physical exploration, thermal imaging and radiometric measurements.
Acknowledgements: INO would like to thank ESA for initiating the 512x3 pixel microbolometer detector
array development and CSA for its continuous support leading to space prototype.
47

10.6 INO’s Micro-Flow Cytometer and other Optics and Photonics Technologies for Space
Marcia L. Vernon, Biophotonics Program Manager
INO
2740, rue Einstein, Québec, Qc
Canada G1T 1P4
Tel:418-657-7006; Fax:418-657-7009
marcia.vernon@ino.ca
INO is a world-class R&D centre specialising in optics and photonics solutions for Canadian industry.
INO’s expertise covers the full spectrum of optics and photonics technologies including lasers, fibre optic
sensors, microfabrication, specialty fibre optics, LIDAR and biophotonics. These have been developed into
components, subsystems and systems for space applications, for example, micromachined infrared
detectors for earth and planetary observation, a radiation-hardened optical fibre and a fibre amplifier for
integration into an OISL. In addition to an overview of INO’s technological offer, this presentation will
discuss our proposed development of a miniaturised flow cytometer combining micro-optics and our fibrebased
flow cytometer.
The development of a micro-flow cytometer with the characteristics needed for space flight (low power
consumption, small footprint) combined with the low cost of optical fibres and microfabrication will have
great impact in point-of-care diagnostics, diagnostics facilities in remote areas and resource-poor countries
and in-situ environmental monitoring.
INO’s fibre optic flow cytometer uses an optical fibre that has been micro-machined to permit counting of
particles and has been demonstrated for counting live bacteria in a mixture of live and dead bacteria.
The flow cytometer platform will be miniaturized by being brought onto a micromachined bench—an
integration platform for passive and active components in much the same way that an optical table is but on
the millimetric scale. The developmental work will be based on the micromachining processes developed at
INO for miniaturized systems with an overall device dimension on the order of tens of millimetres.
48

11 TECHNOLOGY DEVELOPMENT ABSTRACTS FOR POSTER
PRESENTATION IN SPACE PHYSICAL SCIENCES
11.1 The Vibration Environment on Spacecraft and Development of Isolation Technology for the
ISS
Bjarni Tryggvason
Visiting Professor, University of Western Ontario
Canadian Space Agency
Space offers the potential for a disturbance free nearly free-fall environment. However, conditions on
spacecraft in low Earth orbit are not completely ideal. At low frequencies several sources lead to quasistatic
departure that leave residual acceleration of the order of micro-g. While this seems a very small
disturbance level, it acts over long time periods and can and does generate flows in liquids and gases that
are noticeable at the time and spatial scales of many experiments done on spacecraft. At higher frequencies
the vibration environment is of the order of milli-g, not micro-g. This again can represent significant
disturbances for many experiments, particularly those where small scales are important, such as in
diffusion. The vibration isolation technology developed through the CSA can mitigate the effect of these
higher frequency disturbances. Some of the previous effort here will be summarized and current effort
under way at the University of Western Ontario will be described.
11.2 An Overview of Past, Present, and Future Canadian Microgravity Vibration Isolation Mount
Technology
Authors: Derrick Piontek 1 , Jean de Carufel 1 , Melanie Mailloux 2
1 Bristol Aerospace Limited / Magellan Aerospace Corporation, Ottawa, Ontario, Canada
2 Canadian Space Agency, St-Hubert, Québec, Canada
The Canadian Space Agency’s (CSA) Microgravity Vibration Isolation Mount (MIM) technology,
designed to actively isolate experiments from the high frequency (

payloads under consideration including ATEN, a materials science furnace and PROSPECT, a protein
crystal growth facility.
This poster will highlight the past and current MIM technologies, as well as future generations of the
technology currently under consideration by the CSA.
11.3 Diagnostics Using a Confocal Holography Microscope for Three-Dimensional Temperature
and Compositional Measurements of Fluids in Microgravity
P. Jacquemin, P. Marthandam, B. Sawicki and R.A. Herring
University of Victoria, Department of Mechanical Engineering,
PO Box 3055 STN CSC, Victoria, British Columbia, V8W-3P6
A Confocal Scanning Laser Holography (CSLH) microscope has been developed for the studies of fluids in
microgravity. This microscope generates a hologram for each three-dimensional point describing an object,
or fluid in a cell, and offers a new, non-intrusive means to determine the three-dimensional temperature and
composition, which is useful information for heat and mass transfer studies. The holograms are created
from the interference of a “known” reference beam to an “unknown” object beam, which contains the phase
information from which the object’s index of refraction is determined. The key feature of the microscope
for microgravity experimentation is that the object remains stationary as the beam is rastered through the
object ensuring a quiescent environment. Additionally, only one observation window that provides a
limited view of the fluid cell is necessary to obtain a three-dimensional measurement, whereas, other
comparable methods such as tomography and laminography require a large angular field of view. Vibration
disturbances due to the motion of optical components are minimized by applying counter balances and by
using the Motion-vibration Isolation System (MIM).
Many designs of a CSLH microscope are possible and are typically experiment specific. Possible designs
can be found in the publications provided below [1, 2]. Retrieval of the specimen information is made
possible by the modern computer, which has enabled large data files representing the holograms to be
processed rapidly for their reconstruction and proper three-dimensional registry. As well, specific hologram
reconstruction methods for CSLH have been developed to reduce reconstruction error and maximize
information of the specimen [3, 4].
Jacquemin, P., R. McLeod, S. Lai, D. Laurin, and R.A. Herring, “Non-Intrusive, Three-Dimensonal
Temperature and Composition Measurements inside Fluid-Cells in Microgravity using a Confocal
Holography Microscope,” Asta Astronautica 60 (2007) pp. 723 – 727.
Jacquemin, P., R. McLeod, D. Laurin, S. Lai, and R.A. Herring, “Design of a Confocal Holography
Microscope for Three-Dimensional Temperature and Compositional Measurements of Fluids in
Microgravity,” J. of Microgravity Sciences & Technology Vol XVII-4 (2006) pp. 36-40.
Lai, S., R.A. McLeod, P. Jacquemin, S. Atalick, and R.A. Herring, “An Algorithm for 3-D Refractive Index
Measurement in Holographic Confocal Microscopy,” Ultramicroscopy 107 (2007) pp. 196-201.
Jacquemin, P., and R.A. Herring, “A Low Error Reconstruction Method for Confocal Holography and
Limited View Tomography to Determine 3-Dimensional Properties,” Microsc Microanalysis 13 (2007)
Suppl 2, 1228 CD.
50

11.4 ARTEC Technologies
Jean-Paul Thiéblot
Project manager/Structural dynamics
Artec Technologies
535, Curé Boivin, Boisbriand (Québec) Canada,
Composite structures like thin and thick composite shells are now commonly used on satellite structures.
Such components are lightweight, stiff and resistant, but do not provide adequate sound isolation or
vibration damping. High vibration levels are reduced in conformity with incoming vibration requirements
during launch. However, present knowledge in vibration damping does not adequately address the question
of composite material damping.
Discrete damping visco-elastic elements can be:
Embedded at the honeycomb level within standard composite panels (thick shell) to produce damping.
Added at the level of structure stiffeners.
Such treatments have proved to be efficient for damping of metallic structures, and this know-how has
been adapted to composite structures.
This technology developed by ARTEC Technologies allows:
reducing vibration levels in composite materials
reducing the structural fatigue
saving mass and costs.
Present contract: CSA/ESA contract “Damping of RLV composite structure”
Results of technology: attenuation 10 dB
11.5 A New Multifunctional Space Simulator for Accelerated Ground-Based Testing of Spacecraft
Materials and Structures Intended for Space Exploration Missions
J. Kleiman, S. Horodetsky, V. Issoupov, Z. Iskanderova
Integrity Testing Laboratory Inc., 80 Esna Park Drive, Units #7-9,
Markham, ON, L3R 2R7, e-mail: jkleiman@itlinc.com
A new ground-based facility concept is introduced to provide for reliable, accelerated multi-environmental
laboratory testing of spacecraft materials, systems and components in the simulated LEO, GEO and HEO
space environments, as well as environmental conditions of other planets. The proposed concept of the
multifunctional simulator facility is based on the successfully manufactured Multifunctional Variable
Energy Environmental Simulator (VEMES TM ) [1] and includes three stainless steel ultra-high vacuum
chambers interconnected via a sample-transfer system and an air lock chamber. Each simulation chamber is
manufactured in the form of a hemisphere with individual vacuum pumping system, with the chambers
being separated by swing gates.
The first chamber is used to expose the test samples to combined or individual influence of ultra-high
vacuum conditions, variable-energy neutral atomic beams, variable-wavelength UV radiation, thermal
conditioning and thermal cycling in a wide range of temperatures. The simulated space environmental
conditions are controlled in-situ using a quadruple mass-spectrometer, time-of-flight spectrometer, quartz
crystal microbalance, atomic (optical) emission spectrometer and IR pyrometer.
There GEO and HEO space environments, the interplanetary environment and planetary conditions of
Moon, Mars, Venus and/or other planetary bodies can be simulated in the second chamber equipped with
variable-energy charged particle sources simulating the equivalent space radiation effects, as well as with
sources of rocket’s exhaust contaminations and accelerated dust particles.
51

The third analytical chamber implements modern analytical equipment (SEM, AES/XPS, IR/Visible/UV
spectrophotometers and mechanical properties analyzer) for comprehensive in-situ characterization of the
test samples after simulation exposure. The proposed unique multifunctional space simulator is fully
computer-controlled and is operated by powerful computer software implementing the physical models of
various space environments.
1. J. Kleiman, S. Horodetsky, V. Sergeyev, V. Issoupov, “CO 2 -laser assisted atomic oxygen beam sources:
research, development and optimization of operational parameters”, in proceedings of: 8 th International
Space Conference ICPMSE-8, 19-23 June, 2006, Colliuore, France, CD format, Publisher European Space
Agency, 2006
11.6 A Novel Approach for Non-Destructive Mapping of Structural and Mechanical Properties of
Moon and Mars Soils
E. Litovsky, V. Issoupov, Z. Iskanderova, J. Kleiman
Integrity Testing Laboratory Inc., 80 Esna Park Drive, Units #7-9,
Markham, ON, L3R 2R7, e-mail: elitovsky@itlinc.com
The major objective of the suggested approach is to develop and demonstrate in a relevant planetary
environment a new methodology and instrumentation for non-destructive thermal diagnostics of the
structure (porosity, particle’s contact area) and mechanical properties (strength, modulus of elasticity) of
the subsurface layers of planetary soils on planets with rarefied atmospheres, first of all, those of Moon and
Mars. The methodology is based on specially tailored temperature measurements using specific thermal
sensors mounted on the planetary rovers or located on orbiting satellites or spacecraft.
Using a similar methodology and radio-astronomical temperature measurements, properties of selected
regions on the Moon were predicted and later confirmed during unmanned and manned expeditions in
USSR and USA. The structure forecasting method provided good results when the lunar surface was
studied with the purpose to design the first lunar soft-landing rover.
The main innovations of the suggested work could be summarized as follows:
A non-destructive thermal diagnostics approach for mapping of thermo-physical and mechanical properties,
as well as porous structure of Moon and Mars soils within a depth of 0.03-3 m;
Advanced mathematical models for evaluation of thermal response and thermal conductivity based on
contact or remote elaborated measurements of the daily and seasonal surface temperature variations of the
planets;
New instrumentation for non-destructive diagnostics of thermophysical properties, porous structure and
mechanical properties of layers. The sensors will use both natural (passive sensor) and heating source
induced (active sensor) temperature changes.
The suggested approach will include laboratory testing, building and validation of the mathematical models
and basic correlations, as well as verification of the developed instrumentation in the relevant planetary
environments.
11.7 Extended Interaction Klystrons for Communications, Topographical Mapping and Remote
Sensing Applications
Brian Steer
Communications and Power Industries Canada
Georgetown, Ontario, Canada
Brian.Steer@cmp.cpii.com
Various space missions require state-of-the art sensor and communications systems that enable accurate
measurements of Earth precipitation, precision mapping of the planets and moons, and remote sensing of an
atmospheric aerosols and then to return the information back to Earth. These sensors and systems operate at
52

millimeter and sub-millimeter wavelengths and require pulse or CW power from a few watts to several
hundred watts.
Starting in 1990 CPI Canada developed an Extended Interaction Klystron for space-borne radar systems.
The first W-band (94 GHz) space qualified EIK was developed for NASA’s CloudSat mission. The
CloudSat mission provides cross-sectional view of clouds with information on their thickness, altitude,
optical properties, water and ice content. The EIK provides RF signals with peak power of 2 kW and has
been operating in orbit since 2 June 2006.
Recently CPI had completed first phase development of the EIK that will be used as a high power Radio
Frequency transmitter for the High Capability Instruments for Planetary Exploration Topo-mapper Radar.
This EIK will operate at 35 GHz and provide peak power of 3 kW with the duty cycle up to 30%.
Another area of interest is the development of the high power sub-millimeter sources for remote sensing of
atmospheric particles. High radar resolution is achieved by operation at 220-280 GHz with output power of
hundred Watts. Table below summarizes EIK developments for space-borne applications.
Mission
ACE
EGPM
JIMO
Mission
Phase
Proposed/
Feasibility
On hold
Feasibility
Instrument EIK specification Agency EIK Development Status
Dual frequency
doppler crosstrack
scanning
Radar
Precipitation
Radar
Topo-Mapping
Radar
WatER Proposed Radar Altimeter
ATOMS
COREH20
WAVE
Feasibility
Proposed/
Feasibility
Proposed/
Feasibility
Active
Atmospheric
Sounder
Dual frequency
SAR
Snow & Ice
Satcom
Downlink
35.5 / 94 GHz
Pulsed amplifiers
35.5 GHz 1 kW
Pulsed amplifier
35.5 GHz 3 kW
Pulsed amplifier
35 GHz 1.5 kW
Pulsed amplifier
183 GHz 5 W CW
oscillator
9.6 / 17.2 GHz
Pulsed amplifiers
72 / 73 GHz
13W CW
amplifier
NASA
ESA
NASA
NASA/ESA
NASA
ESA
ESA
Requirements Review
EM1 development complete
Development of high power
compact collector complete
Development proposed to
CSA under STDP program
EM1 developed and
delivered to JPL
17.2 GHz device study
EM Proposal for
Italian Space Agency
This poster will explore the capability of CPI’s EIK technology in relation to the applications described
above.
11.8 Étude de l’influence des Perturbations Orbitales sur la Trajectoire des Satellites Défilants
Wassila Leila RAHAL – Noureddine BENABADJI – Ahmed Hafid BELBACHIR
Université de Sciences et de la Technologie d’Oran U.S.T.O.M.B
Laboratoire d’Analyse et d’Application du Rayonnement – LAAR
Afin de réaliser une poursuite automatique des satellites, il est nécessaire de faire au préalable une
prévision de passage dés que le satellite est visible depuis la station (ce qu’on appelle AOS : Acquisition of
Signal) et de pouvoir suivre en temps réel sa trajectoire ( en site et en azimut), jusqu’à la disparition du
signal (LOS) pour une réception optimale des images satellitales.
La prévision est régit par la loi gravitationnelle et en particulier les lois de Kepler. Cependant, le champ de
gravité terrestre n’est pas idéalement de symétrie sphérique, il existe donc des déviations générées pas les
perturbations suivantes :
53

• Forces d’attraction dues aux irrégularités de la distribution de la masse terrestre (aplatissement aux
pôles, masse de l’hémisphère sud plus importante que celle de l’hémisphère nord).
• Forces d’attractions de la lune et du soleil.
• Forces de freinage dues au frottement atmosphérique, surtout pour les satellites à basse orbite
comme les satellites NOAA.
• Pression des radiations solaires.
Nous avons modélisé et pris en compte toutes ces perturbations lors de l’élaboration d’un logiciel de
prévision, qui nous permettra de connaître à l’avance l’heure et la position à laquelle n’importe quel
satellite défilant sera visible à partir d’un point fixe au sol.
54

12 WORKSHOP PARTICIPANT LIST
Title Given name Surname Job title Company or institution E-mail
Universities
Dr. Robert Allison Associate York University allison@cse.yorku.ca
Professor
Dr. Albert Berghuis Professor McGill University albert.berghuis@mcgill.ca
Dr. Anne Camirand Senior Lady Davis Institute, anne.camirand@mail.mcgill.ca
Research McGill University
Mr. Marc Charest PhD University of Toronto charest@utias.utoronto.ca
Candidate
Dr. Sadik Dost Professor University of Victoria sdost@me.uvic.ca
Dr Robert Dumaine Directeur Université de Sherbrooke robert.dumaine@usherbrooke.ca
Mr. Ian Dunkley Ph.D. Student Queen's University dunkley@me.queensu.ca
Dr. Richard Dyde Post Doctoral York University dyde@hpl.cvr.yorku.ca
Fellow
Mr. Chris Erven PhD Graduate University of Waterloo cerven@iqc.ca
Student
Dr. Carlos Fernandes Research University of Toronto carl@ecf.utoronto.ca
Associate
Dr. Clinton Groth Associate University of Toronto groth@utias.utoronto.ca
Professor
Dr. Omer Gulder Professor University of Toronto ogulder@utias.utoronto.ca
Dr. Laurence Harris Professor York University harris@yorku.ca
Dr. Bart Hazes Assistant University of Alberta Bart.Hazes@Ualberta.ca
Professor
Dr. Hani Henein Professor University of Alberta hani.henein@ualberta.ca
Dr. Andrew Higgins Associate McGill University andrew.higgins@mcgill.ca
Professor
M Bruno Hogue étudiant M.Sc. Université de Sherbrooke bruno.hogue@usherbrooke.ca
physiologie
Dr. Richard Hughson Professor University of Waterloo hughson@uwaterloo.ca
M
Karl-
Alexandre
Jahjah
Étudiant à la
maîtrise en
physique
Université Laval
karlalexandre.jahjah.1@ulaval.ca
Dr. Michael Jenkin Professor York University jenkin@cse.yorku.ca
Dr. Heather Jenkin Associate York University hjenkin@yorku.ca
Professor
(Sessional)
M Abd Elhakim Kara Student University of 20 August kara_kim72@hotmail.com
Skikda
Dr. Masahiro Kawaji Professor University of Toronto kawaji@ecf.utoronto.ca
Dr. Olha Kos Postdoc
Fellow,
Transplant
research
Dr Daniel Labrie Associate
Professor
Toronto General
Hospital
Dalhousie University
olhakos@web.de
daniel.labrie@dal.ca
55

Dr Éric Leblanc Chef de Centre de Recherche en eric.leblanc@crchul.ulaval.ca
Projets Infectiologie
M. Jean-Claude Leclerc Étudiant Université Laval jean-claude.leclerc.1@ulaval.ca
Dr. Sheng-Xiang Lin Professor Laval University and sxlin@crchul.ulaval.ca
CHUL research Center
Dr. Brian Lowry Professor University of New bjl@unb.ca
Brunswick
Dr Jean- Joyal Intensive Care Hopital Sainte-Justine js.joyal@umontreal.ca
Sébastien
Physician &
Researcher
Dr. Mark MacLachlan Professor University of British mmaclach@chem.ubc.ca
Columbia
Ms. Heather-Jean May MScE student University of New h-j.may@unb.ca
Brunswick
Mr. Tooru Mizuno Assistant University of Manitoba mizunot@cc.umanitoba.ca
Professor
Dr. David Needham Professor Duke University d.needham@duke.edu
Mr. Agostino Pietrangelo Graduate University of Britsh apietran@chem.ubc.ca
Student Columbia
Dr. Nikolas Provatas Professor McMaster University provata@mcmaster.ca
Dr Claude Rioux Professionnel Université Laval Claude.Rioux@phy.ulaval.ca
de recherche
Dr. Ziad Saghir Professeur Ryerson University zsaghir@ryerson.ca
Dr. Rodney Savidge Professor University of New savi@unb.ca
Brunswick
Dr. Paul Scott Research Queen's University pjs7@queensu.ca
Associate
Dr R J Slobodrian Professeur Université Laval rjslobod@phy.ulaval.ca
Dr. Frank Smith Associate
Professor
Dept of Anatomy and
Neurobiology, Dalhousie
University
University of Victoria
fsmith@tupdean2.med.dal.ca
Dr. Henning Struchtrup Associate
struchtr@uvic.ca
Professor
Dr. Jurgen Sygusch Professor Université de Montréal jurgen.sygusch@umontreal.ca
M. Francois-
David
Tang Étudiant Université McGill,
département de génie
mécanique
francoisdavid.tang@mail.mcgill.ca
Dr. Guy Trudel Professor Ottawa University gtrudel@Ottawahospital.on.ca
Dr. Bjarni Tryggvason Visiting University of Western btryggvason@eng.uwo.ca
Professor Ontario
Dr. Charles Ward Professor University of Toronto ward@mie.utoronto.ca
Dr. Gregor Weihs Associate University of Waterloo weihs@iqc.ca
Professor
Dr. Michael Wolf Professor University of British mwolf@chem.ubc.ca
Columbia
M. Romanesky Yvanho Université Laval yvanho.romanesky@cgocable.ca
Mr. James Zacher Research
Associate
York University
zacher@cvr.yorku.ca
56

Companies
Mr. Nicolae Alecu VP Aerospace & Parallel Geometry Inc. nicolae.alecu@llgeometry.com
Defense
Programs
Dr. Arthur Bailey Senior Scientist Scitech Instruments, abailey@scitechinstruments.ca
Inc.
Mr. William Payne Director of Routes
t_payne@routes.com
Engineering AstroEngineering
Mr. Stephen Churchill Senior Manager C-CORE stephen.churchill@c-core.ca
Ms. Maryellen Cronin Deputy
Commanding
Officer
Mr. Ron Davidson Director Space
Operations
Dr. Jean De Carufel Senior Control
Systems
Engineer
51 Aerospace Control
and Warning Sqn, 22
Wing North Bay
Guigne International
Ltd
Magellan Aerospace
Corporation / Bristol
Aerospace Limited
Cronin.M2@forces.gc.ca
rdavidson@airtab.com
jean.decarufel@magellan.aero
Dr. My Ali EL KHAKANI Professor INRS-EMT elkhakani@emt.inrs.ca
Mr. Jeremie Farret CTO Parallel Geometry Inc. jeremie.farret@llgeometry.com
Dr Martin Gagnon Chiropraticien Centre chiropratique drgagnondc@sympatico.ca
Chambly
Dr Sonia Garcia Blanco Chercheur INO sonia.garcia.blanco@ino.ca
Mr. Terry Girard Business
Development
Manager
COM DEV Ltd terry.girard@comdev.ca
Mr. Blair Gordon Director - Routes
b_gordon@routes.com
Programs AstroEngineering
Dr. Emile Haddad Project Manager MPB Communications emile.haddad@mpbc.ca
Dr. D'Arcy Hart Senior Scientist C-CORE darcy.hart@c-core.ca
Mr. Ruediger Hartwich Project Manager
Life Science
Facilities
Astrium Space
Transportation
Dr. Vitali Issoupov Research
Scientist
Integrity Testing
Laboratory Inc.
Dr. Qi KANG Professor National Microgravity
Laboratory, Institute of
Mechanics, Chinese
Academy of Sciences
ruediger.hartwich@astrium.eads.
net
vissoupov@itlinc.com
kq@imech.ac.cn
Dr. Alexandre Khananian Research PHB/Lasermap alexandrek@groupphb.com
Scientist
Dr. Jacob Kleiman President and Integrity Testing jkleiman@itlinc.com
R&D Director Laboratory, Inc.
Dr. Roman Kruzelecky Senior Research MPB Communications roman.kruzelecky@mpbc.ca
Scientist
Dr. Efim Litovsky Head of Integrity Testing elitovsky@itlinc.com
Thermophysical Laboratory Inc.
Division
Mr. Michael Labib ADCS Engineer Bristol Aerospace
Limited/Magellan
Mr. Joel May System Atlantic Nuclear
Specialist Services Ltd.
michael.labib@magellan.aero
jmay@ansl.ca
57

Mr. David McCabe Manager,
Ottawa Office
Magellan Aerospace
Corporation / Bristol
Aerospace Limited
david.mccabe@magellan.aero
Mr. Lowell Misener President Systems Technologies lowell@systemstechnologies.ca
M Bruno Murray President Narhval Systems Inc. bmurray.narhval@qc.aira.com
Dr. Gunnar K. A. NJALSSON CEO SPACEPOL njalsson@spacepol.ca
Government Policy
Consulting
Dr. Hamideh Parizi Vice President Simulent Inc. parizi@simulent.com
Mr. Derrick Piontek Systems
Engineer
Magellan Aerospace
Corporation / Bristol
Aerospace Limited
derrick.piontek@magellan.aero
Dr. Richard Rembala MDA Corporation richard.rembala@mdacorporatio
n.com
Mme Raymonde Rondeau retraitée Bac philosophie rayriopel@distributel.net
Riopel
Université de Montréal
Dr. Jean-Francois Rotge President &
CSO
Parallel Geometry Inc. jeanfrancois.rotge@llgeometry.com
Mr. Dennis Sindrey Director
Biology,
Consulting to System
Technologies
d.sindrey@sympatico.ca
Scientific Lead
Mr. Brian Steer Business
Development
Manager
M. Jean-Paul Tiéblot Project
manager/
Structural
dynamics
M Daniel Tremblay Recherche et
Développement
technologique
Ms. Marcia Vernon Program
Manager,
Biophotonics
Agency
Dr. Jacob Cohen Program
Executive,
Advanced
Capabilities
Dr. Jitendra Joshi Chief
Technology
Advisor,
Advanced
Capabilities Div
Dr. Fred Kohl ISS Research
Dr. Olivier Minster Head of
Physical
Sciences Unit
Mr. Antonio Verga Technical
Officer for
ESA’s payload
ESTEC
CPI Canada
Artec Technologies
TéléMédic, Relab
INO
NASA
ESMD, NASA HQ
brian.steer@cmp.cpii.com
jp.thieblot@artec-spadd.com
danielt@telemedic.ca
marcia.vernon@ino.ca
jacob.cohen-1@nasa.gov
jitendra.a.joshi@nasa.gov
NASA Glenn Research Fred.J.Kohl@grc.nasa.gov
Project Manager Center
European Space Olivier.Minster@esa.int
Agency
FOTON Office ESA
antonio.verga@esa.int
58

Mr. Martin Zell Head of
Research
Operations
Department
CSA-LPS workshop
Dr. Nicole Buckley Director, Life
and Physical
Sciences
Dr. Luchino Cohen Program
Scientist
Ms. St-Jean Danièle Life and
Physical
Sciences
Dr Marcus DEJMEK Scientifique de
Programme
ESA
CSA
CSA
CSA
ASC
martin.zell@esa.int
nicole.buckley@space.ca
Luchino.cohen@space.ca
Daniele.saint-jean@space.gc.ca
marcus.dejmek@space.gc.ca
Ms. Perron Diane Life and CSA
Diane.perron@space.gc.ca
Physical
Sciences
Mrs. Minodora Iordan Life and CSA
minodora.iordan@space.ca
Physical
Sciences
Dr. Perry Johnson-Green Senior Program CSA
perry.johnson-green@space.ca
Scientist
CSA participants
M. Louis-Paul Bédard Ingénieurphysicien
Agence Spatiale Louis-Paul.Bedard@space.gc.ca
(Planificateur de
mission)
Canadienne
M. Claude Brunet Ingénieur ASC claude.brunet@space.gc.ca
Mme Joanie Carrier Étudiante ASC joanie.carrier@space.gc.ca
Mme Sylvie Desmarais Analyste ASC
sylvie.desmarais@space.gc.ca
principale
M Bastien Dufour Program Lead, ASC
bastien.dufour@space.gc.ca
Physical
Sciences
Dr Stéphane Gendron Ingénieur en ASC
stephane.gendron@space.gc.ca
matériaux et
thermique
Dr. Leo Hartman Research Canadian Space leo.hartman@space.gc.ca
scientist
Mrs. Isabelle Jean Payloads
operation and
integration
Agency
CSA
Ms. Angela Johnson Student CSA (University of
Victoria)
Dr. Pierre Langlois MSS SW CSA
Engineer
M Steve Lauwaet Étudiant / École Polytechnique de
Stagiaire Montréal / Agence
M Frédérick Mathieu Étudiant
stagiaire
Spatiale Canadienne
Agence spatiale
canadienne
isabelle.jean@space.gc.ca
angela.johnson@space.gc.ca
pierre.langlois@space.gc.ca
Steve.Lauwaet@space.gc.ca
frederick.mathieu@space.gc.ca
59

Dr Benoit Palmieri Checheur
postdoctoral
M Walter Peruzzini Gestionnaire de
Programme
Dr. Jean-Claude Piedboeuf Head
Technology
Requirement
and Planning
M. Daniel Provencal Mission
Manager
M José Miguel RAMIREZ SCT satellite
control
technician
M Marla Smithwick Logistics
Officer/Project
Manager
Ms. Taryn Tomlinson Robotics
Engineer
Dr. George Vukovich Director
Spacecraft
Engineering
Agence Spatiale
Canadienne
Agence spatiale
canadienne
Canadian Space
Agency
CSA
SED Systems
CSA
Canadian Space
Agency
CSA
benoit.palmieri@space.gc.ca
walter.peruzzini@space.gc.ca
jeanclaude.piedboeuf@space.gc.ca
daniel.provencal@space.gc.ca
josemiguel.ramirez@space.gc.ca
marla.smithwick@space.gc.ca
taryn.tomlinson@space.gc.ca
george.vukovich@space.gc.ca
60