Space Grant Consortium - University of Wisconsin - Green Bay

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From some of the information Kaymont had on their website regarding balloon performance we were able to get a better idea of how our balloons should be performing. The 1200 gram balloons we purchased had an average ascent rate of 1050 feet per minute with an average bursting altitude of a little over 30 kilometers. This now gave us some ground statistics which would allow us to better predict landing locations for future launches. Command and Payload Pods The StratoSat system comes with one command pod and three payload pods. The command pod is responsible for flight data acquisition such as position, altitude, speed, and heading while the payload pods can be set up with other sensors to collect data such as temperature and pressure. The payload pods can communicate wirelessly with the command pod which sends all of the information gathered by both the command pod and the payload pod back to the tracking software. Once tracking is complete the data can be simply exported into an excel file and analyzed even without the recovery of the system. Equipment Testing Since the tracking of our balloons was to be done with StartoStar Systems StratoSat setup, we began by installing Microsoft MapPoint and the StratoStar software. The new StratoStar software conveniently interfaced with Microsoft MapPoint which allowed for easy geographical location of the balloon. Before our first launch we took all of the StratoSat equipment outside to verify it was working properly. After overcoming a few obstacles with the USB to serial converters, we were able to locate the command pod on our computers. After tracking one of our team members driving around Milwaukee we concluded that the equipment was working properly. Our team quickly noticed that the command pods transmitter needed to be directionally positioned to the antenna receiver. For example, when the transmitter was pointed away from the antenna, the GPS transmitter on the command pod could not communicate with the receiver. While this remains an issue once the balloon is on the ground, this problem is diminished when the balloon is high above the GPS receiver. High Altitude Launch Opportunity (HALO) II The Wisconsin Space Grant Balloon Launch Team began its annual duties in the 2009-2010 season by participating in the High Altitude Launch Opportunity (HALO II) this spring. The HALO II project consisted of the simultaneous launching of 15 high altitude balloons from 15 universities in 9 different states. The purpose of the HALO II launch was to set up a high altitude communications network along with collecting temperature, humidity, pressure, altitude, CO2, rate, and radiation data. By having each payload transmit a radio frequency, the different balloons could link together through the radio transmissions and share data. Taylor University in Indiana served as the mission control for the project and through the communication network created, could receive data in real time. This eliminated the need for a sometimes unsuccessful recovery of the balloon. 2
Our experience with the HALO II launch went well and was a good starting point for the rest of the season. We were able to experience some of the basic procedures such as caring for and filling the balloon along with practicing with the software and the payload unit that was sent to us from StratoStar. While the procedures of the launch and actually launching the balloon went well, tracking and recovering the balloon was a different story. Up to about half way through the balloons flight, the tracking software was working well and was transmitting GPS points back to our software. However, shortly after the balloon reached Figure 2: HALO II Network Coverage approximately 100,000ft we stopped receiving GPS and data packages. After driving around for about four hours trying to pick up a signal on the payload, our team was forced to abort the recovery mission. A few weeks ago our team contacted Jason Krueger from StratoStar to try and figure out the reason for the GPS failure. His conclusion was that the payloads aerodynamic design caused it to twist and turn, eventually becoming tangled in the cord, causing the antenna to break off. We were not the only team to have trouble with tracking and data transmission so hopefully these problems will be corrected for the next team that decides to partake in the continuing HALO project. For more information on the HALO II launch you can go to the following website http://www.nearspacenetwork.com/group/halo2project Launch Planning Balloon Choice As stated above our team chose to use 1200 gram balloons for our launches. 1200 gram balloons are relatively small so they allow us to maximize our use of helium while still providing ample lift for any payload the team may choose to send up. 1200 gram balloons also have similar maximum height and ascent rate characteristics when compared with larger balloons. Location Choice An optimal location for a launch is dependent upon 1) the ideal location of landing, 2) weather conditions, and 3) risk factors in the area. The ideal location of a landing would be in a rural location, away from power lines and heavy traffic. Further, it would be someplace that is not heavily wooded, since this makes retrieval difficult. The location for which we aimed for our first launch was near Monroe, Wisconsin. This is a rural, sparsely populated area, with less trees and hills than Western Wisconsin. 3
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Page 3 and 4: THE CASSINI ENCOUNTER WITH THE GEM
Page 5: Th he proceedinngs of our 199th Ann
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Page 10 and 11: Part 3: NASA Reduced Gravity Progra
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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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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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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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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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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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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. 4.— Light curve of SN 2008bo
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Understanding the Evolution of Supe
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Radio  measurements  of  supe
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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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eneficiation reagents. Ionic liquid
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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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The cost of a one credit graduate c
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EAA WOMEN SOAR - YOU SOAR Dr. Lee J
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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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