Space Grant Consortium - University of Wisconsin - Green Bay

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made out of fiberglass. Although, the centering ring would need to be mounted to the outer body tube and motor mount tubing with metal corner braces and appropriate hardware, in addition excessive amounts of epoxy. The fins and the tail cone however, would almost certainly need to be made from carbon fiber and would have to be a solid one piece custom design. Dart. A solution for the dart is a fairly obvious one. The use of a dual deployment tether/parachute system could have allowed the dart to fall much faster and could have likely kept it within a half mile radius of the launch. This would have added significant amounts of weight to the dart, but now knowing that Tripoli will launch under almost any wind conditions, it would obviously be worth it. A practice launch, as was attempted twice, would have also alerted the team of this. Lastly, as mentioned above, if there was not a radio transmitter in the booster, the dart could easily be tracked as it fell. If nothing else, the rough direction of its location could be known. Conclusion. Maybe the hardest part of this project is just not knowing what happened to the dart. With school now over, a more intensive and comprehensive search will be made. Using GPS, a metal detector, and all the information from this report, the team will spend one or two days attempting to locate the dart in the weeks ahead. It is the team’s hope that this report illustrates that the rocket was still designed particularly well and most of the missed objectives came—not from a lack of engineering—but due to random events out of the team’s control. Had the parachute been deployed even a few seconds after motor burnout, the booster would have likely came down intact and the team could have spent more time looking for the dart. Without the high winds and premature ejection, there is a very good chance that it would have been a very successful flight. Furthermore, a successful flight would likely have produced a maximum altitude anywhere between 50 and 100 percent higher than any other rocket launched that day. The problems that did occur, were never read about or came up in conversations with any experts. Furthermore, it would have been a poor use of resources to even try and account for such a rare occurring event. Except for the modification of the transmitter in the booster and the use of dual deployment in the dart, no other modifications would be made. Ultimately, the team still feels that that the rocket was designed extremely well. In addition to all of the work that the team put in, this project could not have been complete without the help of many people and organizations. The team would gratefully like to express out thanks to the following: The National Space Grant College and Fellowship Program and the Wisconsin Space Grand and Consortium for providing all of the funding for this project. Western Technical College for providing use to their custom prototyping machine at an extremely discounted rate. Jim Connors, a Mechanical Design Technology student from WTC, who helped with the operation of the custom prototyping machine. The University of Wisconsin-La Crosse Physics Department for providing a location to have meetings and store the rocket. References [1] Stine, G.H. 2004. Handbook of Model Rocketry. Wiley, University of Michigan. 12
[2] Public Missiles Ltd. Frequently Asked Questions. 2007. . Accessed 15 March 2009. [3] Parachute 2009. . Accessed 25 March 2009. [4] Drag Coefficient 2009. . Accessed 26 February 2009. [5] Nose Cone Design 2009. . Accessed 28 February 2009. 13
Page 1 and 2: Space Grant Consortium wisconsin UN
Page 3 and 4: THE CASSINI ENCOUNTER WITH THE GEM
Page 5: Th he proceedinngs of our 199th Ann
Page 8 and 9: Wisconsin Space Grant Consortium Un
Page 10 and 11: Part 3: NASA Reduced Gravity Progra
Page 12 and 13: EAA Women Soar - You Soar, Lee Siud
Page 15 and 16: Elijah High Altitude Balloon Projec
Page 17 and 18: Our experience with the HALO II lau
Page 19 and 20: which had been a problem in the pas
Page 21: Figure 6: 3-D GPS Generated Track o
Page 24 and 25: Results The seeds tested in the lab
Page 26 and 27: hour as we assumed the flight in th
Page 28 and 29: Experimental Results There are two
Page 30 and 31: A series of tests were done in a co
Page 32 and 33: 380 360 340 320 23.3 Temp. (Celsius
Page 35 and 36: First Place, Non-Engineering: Schmi
Page 37 and 38: of the basis for fin designs came f
Page 39 and 40: ejection charge from the motor fire
Page 41 and 42: using rip-stop nylon cloth. To atta
Page 43 and 44: Post-flight recovery. A field searc
Page 45: Thus, it is believed that the main
Page 50 and 51: Design Features The chief requireme
Page 52 and 53: The joint between the dart and the
Page 54 and 55: Area dramatically influenced by flo
Page 56 and 57: Altitude [ft] 6000 5000 4000 3000 2
Page 58 and 59: though a strong crosswind was prese
Page 60 and 61: Our Design Our rocket uses the basi
Page 62 and 63: e easily recovered. Bong recreation
Page 64 and 65: Performance Characteristics of Pred
Page 67 and 68: Background and Context: Student Roc
Page 69 and 70: The Rocky Mountain Miners’ compet
Page 71: 19th Annual Conference Part Three N
Page 74 and 75: The angle of repose of a granular m
Page 76 and 77: Experiment Design The experiment co
Page 78 and 79: on the ground and in the Weightless
Page 80 and 81: measurements for the 1 − g data.
Page 82 and 83: [ImageJ, 2008] Image Analysis Softw
Page 85 and 86: Dynamics Characterization of the El
Page 87 and 88: Figure 1 - A calibration equation f
Page 89 and 90: Wire A secondary investigation into
Page 91: [1] Taminger, K. M. B.; and Hafley,
Page 94 and 95: Introduction The analysis of wake v
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Figure 2: Screen I mage o f G UI. T
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References ¹ Burnham, D.C., and Ha
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Validation of Novel Rigid Body Fric
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forces is implemented in the popula
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Figure 2. CAD representation of a t
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Results Figure 5. Assembled hydraul
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References Anitescu, M. (2006). "Op
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Multi-stage Joule-Thomson cycles ar
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significant change in total compres
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The enthalpy (h3) of the 2 nd stage
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UA m� ⎛ ε −1 ⎞ ( c nd c st
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educed, the temperature range that
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7. Lemmon, E. W.; Huber, M. L.; McL
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Throughout each of the run cycles,
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and heater adjusted to accommodate
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Phaeton Mast Dynamics Mechanical Sy
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exposure to the FEMAP with NASTRAN
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The irregularity in the plots above
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inversion of a particular matrix, t
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clarified. Additionally, the PMD ki
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A. Abstract For hardware to be flig
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should be performed at the JWST obs
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B. Attenuation and Uncertainty Shoc
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Detector Array and ROIC SCA Mount L
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Detector Shock Environment The leve
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Orbiter (MRO), Moon Mineralogy Mapp
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4. NASA JPL. MIRI FOCAL PLANE SYSTE
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Is Lake Superior a significant sour
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each grid cell at daily resolution.
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Figure 3. (a) Seasonal cycle of lak
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Figure 5. Model pCO2 at the surface
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Marshall, J., A. Adcroft, C. Hill,
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numerical weather prediction (NWP)
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High Resolution Radiometer (AVHRR)
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On the morning of 26 May 2008, ther
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References Behnke, C., 2005: Synopt
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Figure 3 Figure 3 contains base ref
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A Comparative Study of Type IIb Sup
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Fig. 3.— Cartoon Image of SN blas
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Fig. 4.— Light curve of SN 2008bo
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type IIn Supernova SN 1995N,” 200
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and then can spiral in to the black
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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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