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Detector Shock Environment The levels of shock on the observatory are specified as the shock environment. This environment comes from the different sources of shock that affect the JWST. These levels of shock are from the launch and the internal events that affect the observatory while it’s in space. The shock from launch is from the effects of launch vehicle and fairing separation. The internal events that self-induce shock on to the observatory are from the launch restraint mechanisms (LRMs) that deploy the JWST. There are specified acceptance and qualification SRS for the Spacecraft, Optical Telescope Element (OTE), ISIM and their interfaces. The ISIM/OTE interface, referred to as the Region 1 interface is the environment that is of interest to the detectors. The shock environment will occur at approximately 200K when the observatory is in orbit. ISIM/OTE Interface shock specifications have recently been updated by Northrop Grumman in ECR 155. [14] A. Shock from Launch The shock from launch comes from the Ariane 5 interface; this includes PAF and fairing separation. Arianespace has developed a new fairing and clampband separation device that have made the shock input to the spacecraft negligible. These new developments were demonstrated by several on-ground tests. The shock levels from launch are now enveloped by the shock from the observatory internal events. [11][5] Freq (Hz) Ariane 5 Interface Shock Acceptance Qualification Acceptance Qualification Freq (Hz) SRS (g) SRS (g) SRS (g) SRS (g) 100 20 40 100 10 20 1000 111 222 3000 700 1400 10000 80 160 10000 700 1400 B. Shock from Internal Events Updated ISIM Shock Specifications (ECR 155) Launch restraint mechanisms (LRMs) used to release the observatory deployables utilize non-explosive actuators to release the appendages, allowing them to deploy to their on-orbit positions. The LRMs chosen produce a very low shock impulse into the attached hardware compared to heritage pyrotechnic devices. However, significant shock impulses occur when the stored strain energy of the restrained hardware is released. The Primary mirror wing LRMs are the closest source to ISIM. The detectors are on the Science Instrument (SI) level of the observatory, thus the shock from the LRMs is 64 [14] Observatory LRM Shock
attenuated from its source. The attenuated shock levels for the detectors are in the table below along with a graph comparing current acceptance to the previous. [11][13] Updated SI Acceptance Shock Specification Freq (Hz) A. Previous Projects Acceptance Qualification SRS (g) SRS (g) 100 10 20 1700 350 700 10000 350 700 SRS (g) 1000 100 SI Acceptance Shock Levels [1] Detector Heritage Stored Strain Release LRMs 10 100 1000 Freq (Hz) 10000 Updated Specification Previous Specification Teledyne Sensors and Raytheon are producing the deliverable FPAs for JWST. These companies are the main detector producers and have significant experience in building the assemblies. They have built FPA packages for the Spitzer Space Telescope, Deep Impact Comet mission, Hubble Space Telescope (HST), Mars Reconnaissance 65
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Space Grant Consortium wisconsin UN
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THE CASSINI ENCOUNTER WITH THE GEM
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Th he proceedinngs of our 199th Ann
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Wisconsin Space Grant Consortium Un
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Part 3: NASA Reduced Gravity Progra
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EAA Women Soar - You Soar, Lee Siud
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Elijah High Altitude Balloon Projec
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Our experience with the HALO II lau
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which had been a problem in the pas
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Figure 6: 3-D GPS Generated Track o
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Results The seeds tested in the lab
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hour as we assumed the flight in th
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Experimental Results There are two
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A series of tests were done in a co
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380 360 340 320 23.3 Temp. (Celsius
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First Place, Non-Engineering: Schmi
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of the basis for fin designs came f
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ejection charge from the motor fire
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using rip-stop nylon cloth. To atta
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Post-flight recovery. A field searc
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Thus, it is believed that the main
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[2] Public Missiles Ltd. Frequently
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Design Features The chief requireme
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The joint between the dart and the
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Area dramatically influenced by flo
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Altitude [ft] 6000 5000 4000 3000 2
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though a strong crosswind was prese
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Our Design Our rocket uses the basi
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e easily recovered. Bong recreation
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Performance Characteristics of Pred
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Background and Context: Student Roc
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The Rocky Mountain Miners’ compet
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19th Annual Conference Part Three N
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The angle of repose of a granular m
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Experiment Design The experiment co
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on the ground and in the Weightless
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measurements for the 1 − g data.
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[ImageJ, 2008] Image Analysis Softw
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Dynamics Characterization of the El
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Figure 1 - A calibration equation f
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Wire A secondary investigation into
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[1] Taminger, K. M. B.; and Hafley,
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Introduction The analysis of wake v
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Figure 2: Screen I mage o f G UI. T
Page 98 and 99: References ¹ Burnham, D.C., and Ha
Page 101 and 102: Validation of Novel Rigid Body Fric
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Page 107 and 108: Results Figure 5. Assembled hydraul
Page 109: References Anitescu, M. (2006). "Op
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Page 122 and 123: 7. Lemmon, E. W.; Huber, M. L.; McL
Page 124 and 125: Throughout each of the run cycles,
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Page 129 and 130: Phaeton Mast Dynamics Mechanical Sy
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Page 133 and 134: The irregularity in the plots above
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Page 140 and 141: A. Abstract For hardware to be flig
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Page 163: Marshall, J., A. Adcroft, C. Hill,
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Page 170 and 171: On the morning of 26 May 2008, ther
Page 172 and 173: References Behnke, C., 2005: Synopt
Page 174 and 175: Figure 3 Figure 3 contains base ref
Page 177 and 178: A Comparative Study of Type IIb Sup
Page 179 and 180: Fig. 3.— Cartoon Image of SN blas
Page 181 and 182: Fig. 4.— Light curve of SN 2008bo
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In the equations on the p
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SN 2008ax in NGC 4490 SN2008ax is a
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References Chevalier, R. A., “Int
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Computational Fluid Dynamical Model
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context of the k − ɛ model invol
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Figure 3: Experimental results (•
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direction results in the terminal s
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121 (2000). [Blue Ridge Numerics, I
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concentrated our effort specificall
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density, and Ps is a pressure tenso
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Properties of the GEM problem Recon
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Figure 1: Increase in reconnection
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Figure 3: Examples of agreement of
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Reflection and Refraction of Vortex
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Experimental Procedure The left han
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frames in the upper left corner, wh
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Vortex ring reflection. Similarly,
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References L Bernal and J Kwon. Vor
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group started in 1997 with the goal
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I conducted five semi-structured in
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In the example of the guinea pig pr
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explain t his t rend. F rom t alkin
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Research. Washington, DC: Pan Ameri
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Our team has two goals: 1. To put S
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fluctuating humidity, drying winds,
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western border of the Arkansas Rive
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adjusted to less than .4millisecond
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Cacti Experiment 18 has produced 10
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13. What N decomposer's are needed
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Abstract Toxic Offgassing Analysis
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The chambers were sealed and baked
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Tables 4 and 5 show offgassing comp
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there was no dichlorobenzene peak.
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eneficiation reagents. Ionic liquid
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Figure 3: Current versus voltage da
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Abstract New Initiatives in the Pro
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was noticed above the gel. A discol
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delicate structures (hairs). N o fu
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and A. Y. Rozanov, Eds., SPIE, Vol.
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Combining Writing Across the Curric
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But the study also reported a consi
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Educators’ Aerospace Workshop for
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2008-2009 Evaluation Educators’ A
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Some comments from participants 200
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The cost of a one credit graduate c
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EAA WOMEN SOAR - YOU SOAR Dr. Lee J
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� Incorporated the technology res
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Evaluation Results: At the conclusi
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Educational Standards: The National
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curriculum development, to provide
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and applications of GIS technology
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• A significant new outcome for t
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The design of this project and appl
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Activities at the workshop involved
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to give our students a series of PR
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In the past we have not focused on
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Providing High School Students with
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that th e current generations of s
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instruction a s pa rt o f t heir ow
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Wisconsin Space Grant Consortium &
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11:45-1:00 pm Lunch *** Concurrent
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Moderator: David B lock, A ssociate
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Second Place, E ngineering, Drew an
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Wisconsin Space Grant Consortium
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Space Grant Consortium - University of Wisconsin - Green Bay

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