Issue 10 Volume 41 May 16, 2003

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SPACECRAFT DESIGN, TESTING AND PERFORMANCE
Includes satellites; space platforms; space stations; spacecraft systems and components such as thermal and environmental controls;
and spacecraft control and stability characteristics. For life support systems see 54 Man/System Technology and Life Support. For
related information see also 05 Aircraft Design, Testing and Performance; 39 Structural Mechanics; and 16 Space Transportation and
Safety.
20030032295 NASA Goddard Space Flight Center, Greenbelt, MD, USA
Initialization of Formation Flying Using Primer Vector Theory
Mailhe, Laurie; Schiff, Conrad; Folta, David; January 2002; 8 pp.; In English; International Symposium on Formation Flying
Missions and Technology, 29-31 Oct. 2002, Toulouse, France; Copyright; Avail: CASI; A02, Hardcopy
In this paper, we extend primer vector analysis to formation flying. Optimization of the classical rendezvous or free-time
transfer problem between two orbits using primer vector theory has been extensively studied for one spacecraft. However, an
increasing number of missions are now considering flying a set of spacecraft in close formation. Missions such as the
Magnetospheric MultiScale (MMS) and Leonardo-BRDF (Bidirectional Reflectance Distribution Function) need to determine
strategies to transfer each spacecraft from the common launch orbit to their respective operational orbit. In addition, all the
spacecraft must synchronize their states so that they achieve the same desired formation geometry over each orbit. This
periodicity requirement imposes constraints on the boundary conditions that can be used for the primer vector algorithm. In
this work we explore the impact of the periodicity requirement in optimizing each spacecraft transfer trajectory using primer
vector theory. We first present our adaptation of primer vector theory to formation flying. Using this method, we then compute
the AV budget for each spacecraft subject to different formation endpoint constraints.
Author
Formation Flying; Vectors (Mathematics); Trajectory Optimization; Spacecraft Trajectories; Transfer Orbits
20030032361 NASA Goddard Space Flight Center, Greenbelt, MD, USA
The LISA Integrated Model
Merkowitz, Stephen M.; [2002]; 7 pp.; In English; LISA Symposium, 19-24 Jul. 2002, PA, USA; Original contains black and
white illustrations; No Copyright; Avail: CASI; A02, Hardcopy
The Laser Interferometer Space Antenna (LISA) space mission has unique needs that argue for an aggressive modeling
effort. These models ultimately need to forecast and interrelate the behavior of the science input, structure, optics, control
systems, and many other factors that affect the performance of the flight hardware. In addition, many components of these
integrated models will also be used separately for the evaluation and investigation of design choices, technology development
and integration and test. This article presents an overview of the LISA integrated modeling effort.
Author
Dynamic Models; Lisa (Observatory); Spacecraft Instruments; Performance Prediction; Systems Engineering; Systems
Integration; Systems Simulation; Aerospace Engineering
20030032967 Instituto de Pesquisas Espaciais, Sao Jose dos Campos, Brazil
Development of an Electrostatic Energy Analyzer (ESA) for EQUARS Scientific Satellite
Dallaqua, RenatoSegio; Tan, IngHwie; Alves, MariaVirginia; delBosco, Edson; [2003]; 37 pp.; In English; Original contains
black and white illustrations
Report No.(s): INPE-9603-NTC/352; Copyright; Avail: CASI; A03, Hardcopy
We present in this report the development of an electrostatic energy analyzer to be launched onboard the EQUARS
Scientific Satellite. The instrument will be capable to detect electron beams with energies in the 0.1 - 40 keV range. This
document concerns mainly with the scientific objectives and the mass and power requirements of the instrument.
Author
Electron Beams; Satellite Instruments; Charged Particles; Wave Propagation; Data Processing; Design Analysis; Structural
Design
20030036954 NASA Goddard Space Flight Center, Greenbelt, MD, USA
JASON-1 Precise Orbit Determination (POD) Through the Combination and Comparison of GPS, SLR, DORIS and
Altimeter Crossover Data
Luthcke, S. B.; Zelensky, N. P.; Lemoine, Frank G.; Chinn, D. S.; Williams, T. A.; [2002]; 1 pp.; In English; American
Geophysical Union Meeting, 6-10 Dec. 2002, San Francisco, CA, USA; Copyright; Avail: Other Sources; Abstract Only
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