Space Grant Consortium - University of Wisconsin - Green Bay

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B. Attenuation and Uncertainty Shock attenuates when it propagates through a material. Attenuation, the reduction of shock, is critical in calculating the peak levels of shock that a particular piece of a larger structure will be exposed to. Attenuation analysis of shock is based on the length of the dispersion path through the structure and the number and types of structural joints in that structure. According to a NASA Technical Standards for Pyro- Shock Requirements Document (RD 23) there is a reduction in shock magnitudes in the realm of 20 to 75 percent from propagation through structural joints. This percentage range depends on the material of the joint and structure, and the path of transmission through the joint. This shows the uncertainty in quantifying shock, creating large margins between acceptance and qualification SRS. C. Methods to Assess Shock There are general methods of assessing the risk of damage from shock. Coverage of shock using random vibration loads and the two methods for structural and electrical components from the ESA Shock Handbook are widely accepted. The 0.8f rule for structural components is a simple comparison of a 0.8 sloped limit line, with respect to frequency, where structures are not at risk if their SRS lie below the limit. The 6db/octave rule for electronics shares a similar concept, except it has a smaller slope of 6db/octave and tops out at 500g for 2 kHz. The other method of assessing shock allows one to compare the shock specification to random vibration. This is the most accepted method among the space community. This approach converts random vibration loads into a random response spectrum or RRS that can be compared to a SRS. This is done with the Miles formula, which is a simplified approximation of an RRS. The equation uses Q; an amplification factor which is typically 10 or 25, fo; the frequency at which the acceleration is calculated and W (fo); the value in g 2 /Hz of the Power Spectral Density (PSD or random specification) at the frequency fo in the calculations. Shock will not be an issue if the RRS covers the SRS levels. By using the formula below, the frequency values for random vibration loads and the corresponding PSD, RRS can be compared to SRS to asses shock and determine if direct testing is needed. RRSMiles (fo) = 3 x SQRT [π/2 * Q * fo * W (fo)] The James Webb Space Telescope Detectors JWST uses new detectors that are top of the line with very low noise and darkcurrent, and high quantum efficiency. These qualities measure the precision, accuracy and reliability of detectors, respectively. There are a total of 18 infrared detectors between the four instruments. Of these, 15 are HAWAII 2RG detector arrays from Teledyne Imaging Sensors and the other three are SB-375 Si:As detector arrays from Raytheon. HAWAII is an acronym for HgCdTe Astronomical Wide Area Infrared Imager and 2RG denotes the size (2048x2028 pixel), and that the array has reference and guidance pixels included. H2RG detectors are used in the Near-Infrared Camera 60
(NIRCam), Near-Infrared Spectrograph (NIRSpec) and the Fine Guidance Sensor (FGS). The Silicon Arsenic detectors are 1024x1024 pixel arrays with reference and guidance as well, that are only used in the Mid-Infrared Instrument (MIRI). The detectors on NIRCam, NIRSpec and FGS are used for imaging, spectroscopy, object tracking and narrow band imaging respectively. The detectors on MIRI are used for mid-infrared imaging and spectroscopy. The 18 detector arrays are the most impressive, however not the only part of the Focal Plane Assembly (FPA). The FPAs are positioned to capture light while being mounted on the base of their instruments, which also sit on top of the ISIM base by way of kinematic mounts. [2][6] A. FPA Structure The FPAs for each instrument consist of the Sensor Chip Assembly (SCA) along with its support structure and housing enclosure. The SCA is made up of the infrared detector material, a Silicon readout integrated circuit (ROIC), and a SCA mount connecting to a flex cable link. Microscopic Indium bumps connect the infrared material to the ROIC. The Silicon ROIC is responsible for charge to voltage conversion, signal transfer through the circuit, and digitization of the signal. The flex cable connects to the ROIC and sends out the digitized signal to be processed. The SCA mount supports the ROIC, infrared array and flex cable. Above the SCA is a stray light mask which protects the detector array from unwanted sources of light. The SCA is epoxied to an insert or interface plate below it, this provides electrical isolation as well as precision alignment for the SCA. The interface plate rests on top of the mosaic plate to provide a sturdy connection of the SCA to lower supporting structure. The mosaic plate by way of flexure struts connects to the baseplate. The baseplate is the support of the assembly housing and interface to the instrument. The FPAs in the ISIM have different configurations, some with 1 SCA and others with 2 or 4. The FPAs with 4 SCAs are set as 2x2 mosaics. [2][6] 61
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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,
Page 94 and 95: Introduction The analysis of wake v
Page 96 and 97: 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
Page 103 and 104: forces is implemented in the popula
Page 105 and 106: Figure 2. CAD representation of a t
Page 107 and 108: Results Figure 5. Assembled hydraul
Page 109: References Anitescu, M. (2006). "Op
Page 112 and 113: Multi-stage Joule-Thomson cycles ar
Page 114 and 115: significant change in total compres
Page 116 and 117: The enthalpy (h3) of the 2 nd stage
Page 118 and 119: UA m� ⎛ ε −1 ⎞ ( c nd c st
Page 120 and 121: educed, the temperature range that
Page 122 and 123: 7. Lemmon, E. W.; Huber, M. L.; McL
Page 124 and 125: Throughout each of the run cycles,
Page 126 and 127: and heater adjusted to accommodate
Page 129 and 130: Phaeton Mast Dynamics Mechanical Sy
Page 131 and 132: exposure to the FEMAP with NASTRAN
Page 133 and 134: The irregularity in the plots above
Page 135 and 136: inversion of a particular matrix, t
Page 137: clarified. Additionally, the PMD ki
Page 140 and 141: A. Abstract For hardware to be flig
Page 142 and 143: should be performed at the JWST obs
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Page 148 and 149: Detector Shock Environment The leve
Page 150 and 151: Orbiter (MRO), Moon Mineralogy Mapp
Page 152 and 153: 4. NASA JPL. MIRI FOCAL PLANE SYSTE
Page 155 and 156: Is Lake Superior a significant sour
Page 157 and 158: each grid cell at daily resolution.
Page 159 and 160: Figure 3. (a) Seasonal cycle of lak
Page 161 and 162: Figure 5. Model pCO2 at the surface
Page 163: Marshall, J., A. Adcroft, C. Hill,
Page 166 and 167: numerical weather prediction (NWP)
Page 168 and 169: High Resolution Radiometer (AVHRR)
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
Page 183: type IIn Supernova SN 1995N,” 200
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Understanding the Evolution of Supe
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Radio  measurements  of  supe
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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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