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Team Magnaritaville Final Presentation

Team Magnaritaville Final Presentation. Zachary Cuseo, Andrew Fruge ’, Tyler Knappe , Christopher Nie , Sydni Smith, and Shweta Maurya December 1, 2009. Mission Overview.

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Team Magnaritaville Final Presentation

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  1. Team MagnaritavilleFinal Presentation Zachary Cuseo, Andrew Fruge’, Tyler Knappe, Christopher Nie, Sydni Smith, and ShwetaMaurya December 1, 2009

  2. Mission Overview • The twofold purpose of this BalloonSat mission will be to show that the Earth's magnetic field varies and to show that magnetometers can be used to determine the attitude of a BalloonSat.

  3. Mission Overview Continued • Hypothesis • Fluctuation in the Earth’s magnetic field • Finding a vector which will facilitate in determining in which direction the camera is pointed • Satellite attitude • To better understand the magnetic field

  4. Mission Specific Components • 1 AVR Microcontroller • 2 Magnetometers • 2 Analog Proto Board Connectors • 5 9V Batteries • 1 Canon Camera • 1 Heater • 1 HOBO

  5. Functional Block Diagram

  6. Functionality Switch Batteries HOBO External Heater AVR Temperature Probe Magnetometers Accelerometer Camera Internal Temperature Probe Pressure Sensors

  7. Design Differences Proposed Actual The Heater and Batteries were placed in a corner to maximize heating efficiency, while the AVR was attached to a wall. The two magnetometers extended from adjacent sides for more accurate readings No photo of a cheeseburger was used. No Faraday Cage was necessary. • Staggering the Heater, Batteries and AVR for balance. • The two magnetometers will extend from opposite sides of the Satellite. • There will be a photo of a cheeseburger to truly be C.A.T.E.O.S. • Utilizing a Faraday Cage

  8. Results and Analysis Mag X Strength (nT) Time Mag Y Strength (nT) Time

  9. Results and Analysis Accel X Accel Y Internal Temp (°C) Pressure (psi)

  10. Results and Analysis • Vertical Mag Y Strength (nT) Time Voltage Time

  11. Results and Analysis • Vertical field trends – • Overall decrease of 4,219 nT • Expected change due to altitude of 1,694 nT • Rolling into x-direction would explain this extra variation

  12. Results and Analysis • Magnetometer Data X-Magnetometer Variation

  13. Results and Analysis • Picture 771 – 8:08 a.m. • Data point (28,039,1.94339)  East

  14. Results and Analysis • Picture 705 – 7:45 a.m. • Data point (21,379, 2.2266)  North

  15. Lessons Learned • Orient vertical magnetometer pointing down • Add a third magnetometer in the horizontal plane for definitive attitude determination • Prototype structure • Keep it simple • Test different designs for an efficient use of space

  16. Ready to Fly • Store payload in standard conditions upright to protect magnetometers • Perform launch checklist

  17. Failure Analysis • No in-flight failures • On functional test, y magnetometer was discovered to be inoperative • Thought to be connection problem • Found faulty connection to the proto board • Soldered and verified to be working • Magnetometer Structural Failure • End cap lost during transport to launch site • Wax paper taped onto end at launch site

  18. Conclusion • Discovered a change in the vertical component of the magnetic field with respect to altitude • Confirmed a spin in the satellite, as seen through the sinusoidal data • Discovered attitude determination is possible with the use of a horizontal magnetometer

  19. RFP Compliance

  20. Mass Budget Budgets Monetary Budget

  21. Message to Next Semester • Keep the experiment simple, but make sure everyone is interested in it. • Find a way to sufficiently secure the camera and to cover/insulate it. • Establish a consistent time to meet on a weekly basis. Do this as early as possible. • Utilize your resources (Space grant, your professors, etc.) • Start video taping early • Prepare for this project to be a major time commitment • Dedicate at least one all-nighter to the satellite

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