1. Ryan Olin, Austin Granger, R.J. Kakach, Seth Frick, Joey Senkyr AEM 1905 11/24/09

2. Objectives  Launch and recover payload  Use weather station to track temperature, pressure and relative humidity in near space  Track location, altitude and trajectory of payload  Test what wavelengths of light are visible at different altitudes using a diffraction grating with a low-light filter tube  Monitor internal conditions of payload using HOBO temperature probe  Attempt to generate electrical current with Peltier cell exploiting temperature difference  Analyze data after flight to qualify our predicted results

3.  For our camera experiment, we will use diffraction grating to measure the wavelengths of light in Near Space.  This picture is the control for our camera experiment, it was taken on the ground through our diffraction grating with a light filter tube.  After the flight, we will compare this picture with the ones from various altitudes.

4. Peltier Cell  We want to show how much electricity the Peltier cell will generate as the difference in temperature increases

5.  Since the HOBO cannot take voltages over 2.5 volts, we needed to make a voltage limiter circuit.  The Peltier Cell is the power supply, and the HOBO is the voltmeter.

6. Ryan Olin Team Lead, PowerPoint development Seth Frick Flight Computer Build and Peltier cell experiment Joey Senkyr Payload box build and HOBO programmer Austin Granger Photographer and Camera Experiment R.J. Kakach Weather Station Build and Programmer

7. List of Parts  Camera  Hobo  Flight Computer  Weather Station  Weather Station Shade  Batteries 4x  Heater  Peltier Cell  Epoxy  Diffraction Grating  Diffraction Grating Tube  Styrofoam  Wires  Cable Ties  Duct Tape  Hot Glue  Heat Shrink Cover  Voltage Limiter Circuit

8. Conceptual Design Sketch

10. Exterior Payload Design 7” 1” 5” Top View (without lid) Side View (without lid) 7” 1.5” 3” 6” 1” Payload Box Design

11. Payload Design (Detailed)

12. Payload Construction

13.  Team Building and Experiment Planning – 9/20/09 – 9/27/09  Weather Station build – Completed 10/4/09  Heater Circuit build – Completed 10/4/09  Flight Computer build – Completed 10/4/09  CDR Presentation – 10/6/09  Payload Construction – Began 10/11/09, Completed 10/23/09  Test and Program Flight Computer/HOBO – Completed 10/20/09  FRR Presentation – 10/27/09  Weather Station Testing and Cold Soak – Completed 10/28/09  Payload rigging – Completed 10/28/09  Final Weigh-in, Payload Turn-in, and yank test – Completed 10/29/09  Halloween Launch – 10/31/09  Data analysis - Began 11/3/09  Final project presentation – 11/24/09

14. ObjectMass (kg) Pink Styrofoam0.150 Tubing, rigging, zip ties, glue, etc.0.075 Heater circuit0.027 3-pack 9-volt battery for heater0.150 Weather station0.015 BalloonSat Easy flight computer0.033 9-volt battery for flight computer0.046 Canon Powershot still camera0.223 HOBO data logger0.048 HOBO voltage probe0.010 Peltier cell0.020 Diffraction grating0.005 Voltage Limiter Circuit0.015 Cardboard Tubing0.02 Total0.837

15. ObjectCost ($) Pink Styrofoam 8.00 Tubing, rigging, zip ties, glue, etc. 5.00 Heater circuit 5.00 3-pack 9-volt battery for heater 6.00 Weather station 40.00 BalloonSat Easy flight computer 30.00 9-volt battery for flight computer 2.00 Canon Powershot still camera 166.00 HOBO data logger 130.00 HOBO voltage probe 9.00 Peltier cell 5.00 Diffraction grating 7.00 Voltage Limiter Circuit 1.00 Cardboard Tubing Free Total 414.00

16.  Camera Experiment: We set our camera to take non-flash pictures every 30 seconds through our diffraction grating.  Flight Computer: The flight computer takes readings from the weather station every 5 seconds.  HOBO: The HOBO measures the internal temperature and the voltage of the Peltier cell every 2-5 seconds.  ;

17.  Drop Test – Result: Payload survived  Flight Computer Test – Result: Flight computer functional  HOBO Test – Result: HOBO functional and responding to program  Weather Station Test – Result: Sensors functional and communication with flight computer established  Cold Soak – Result: All components still functional after 20 minute soak  Yank Test – Result: Rigging held and all components stayed in place  Weigh-in – Result: Final payload mass 0.880 kg

18.  Camera Experiment: We expect to see fewer wavelengths of visible light because there are fewer gases in the atmosphere.  Peltier Cell Experiment: As the temperature difference between the interior and exterior of the payload increases, we expect the voltage to increase.  Weather Station: We think the weather station will detect lower pressure, humidity and temperatures at higher altitudes (except in the Ozone layer).

19. We expect the temperature to follow a pattern similar to that in the graph as the altitude increases. Our maximum altitude will be somewhere near the middle of the stratosphere. Graph courtesy of the University of Colorado, www.colorado.edu

20. Balloon filling and pre-launch activity Stack just after launch Tracking (via ham radio APRS) and chase

21. Payload interior after recovery – camera dislodged, but everything still functional Recovery was difficult … …but not impossible

22. The launch went well, although the weather was very cold with flurries. Tracking of the payload went smoothly (for the most part), and our stack reached a maximum altitude of about 112,000 feet and landed near the Chippewa Moraine State Recreation Area in west-central Wisconsin. Upon recovering the payload, we observed no physical damage to any components or the payload structure itself. Everything was still functioning, but the camera had been dislodged.

23. Note: launch occurred at t = 0 s, burst occurred around t = 5500 s, and landing occurred around t = 8000 s

24. Note: launch occurred at t = 0 s, burst occurred around t = 5500 s, and landing occurred around t = 8000 s

25. Note: launch occurred at t = 0 s, burst occurred around t = 5500 s, and landing occurred around t = 8000 s

26. Note: launch occurred at t = 0 s, burst occurred around t = 5500 s, and landing occurred around t = 8000 s Graph 2: courtesy of Team Icarus

27. Note: launch occurred at t = 0 s, burst occurred around t = 5500 s, and landing occurred around t = 8000 s

28. Note: launch occurred at t = 0 s, burst occurred around t = 5500 s, and landing occurred around t = 8000 s

29. Note: launch occurred at t = 0 s, burst occurred around t = 5500 s, and landing occurred around t = 8000 s

30. We were unable to pinpoint any specific wavelengths that drop from the spectrum at higher altitudes, but we noticed that the high- frequency end of the spectrum (near-ultraviolet light) became more intense as the altitude increased. This makes sense, since the atmosphere filters ultraviolet light from the Sun, resulting in less ultraviolet light at lower altitudes.

31. 3,376 feet Note: altitudes are in feet above sea level, not above the ground. Launch altitude was approximately 1000 feet above sea level. 84,160 feet 59,608 feet Pictures courtesy of University of Minnesota – Morris flight on 11/14/09

32. The Peltier cell responded as we expected and produced more current as the outside temperature got lower. The Peltier cell could be a reasonable alternative to batteries for powering a second heater. The color spectrum did appear (in our data) to change at higher altitudes, but we would need a more sensitive camera to detect it properly. Not everything in life or ballooning will go exactly how you want it. Ballooning is hard…but a lot of fun!