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Team Ramrod Critical Design Review

Team Ramrod Critical Design Review. Dan Armel, Michaela Cui, Andrew Grimaldi, Kyle Kemble, Silvia Peckham, Chris Sawyer, & Kelsey Whitesell 2007 October 18 TH.  lpha mega.  lpha mega. Mission:

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Team Ramrod Critical Design Review

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  1. Team RamrodCritical Design Review Dan Armel, Michaela Cui, Andrew Grimaldi, Kyle Kemble, Silvia Peckham, Chris Sawyer, & Kelsey Whitesell 2007 October 18TH

  2. lpha mega

  3. lpha mega • Mission: • Travel to 30km on a high altitude weather balloon provided by Edge of Space Sciences (E.O.S.S.). • During ascent photodiodes mounted at the extremities of the balloon will quantitatively measure the levels of light in the Infrared and Visible spectrums.

  4. lpha mega Objectives • O1- The spacecraft shall be a BalloonSat with mass at or below 800 grams and total financial costs at or below $200 in compliance with the RFP. • O2 -The spacecraft shall be launched from Windsor, Colorado and recovered on November 10, 2007. • O3 -The spacecraft shall be configured to attach to a variable position on a string, with 10 other satellites, connected to the balloon launch vehicle. • O4 - The instruments of the spacecraft shall remain intact and functional during a 90 minute ascent to an altitude of 30 km and a 45 minute descent including landing. • Additionally Alpha Omega will be fully functional within one week of recovery • O5 - The spacecraft and design document shall meet all requirements stated in the RFP template • S1 - The payload shall record the number of infrared light particles during a 90 minute ascent within an altitude range of 0 and 30 km

  5. lpha mega Requirements • O1.1-The mass and financial budget shall be divided proportionally among the structural, circuit and science components. • O2.1-The team shall provide a vehicle to travel to the launch and landing site and recover the spacecraft after launch. • O3.1- The spacecraft shall be secured to a string provided by the balloon launch vehicle over the entire 135 minute flight without severing the string at any point. • O4.1- The BalloonSat components will have sufficient power to last for the duration of the flight, also components must be secured to withstand a maximum of 15 times the force of gravity. • S1.1- The photodiodes will measure light in the wavelengths ranging from 1nm to 750nm.

  6. lpha mega Design Discussion

  7. lpha mega Design Discussion Parts: • Aluminum (30cm x 76.2cm x 0.3cm): • Western Aluminum Recycling: Ordered, arrive: Oct 19th • Basic Stamp II module: • Parallax: Ordered, arrived Oct 16th • Mylar Thermal Blanket: • R.E.I: Ordered, arrived Oct 12th

  8. lpha mega

  9. lpha mega Schedule

  10. lpha mega • Financial Budget: • Mass Budget:

  11. lpha mega Test Plan The following tests will be conducted: • Circuitry: • Ensure circuitry is integrated and batteries are functional. • Photometer Circuit: • Check functionality of photometer circuit. • Photometer Calibration: • Check focal length of lens. • Dark Current Calibration: • To account for amount of dark current in circuit. • Cold Test: • Check thermal systems. • Whip Test: • Check structural systems. • Swing Angle: • Determine angle at which sun will interfere with photodiodes. • Drop Test: • Check structural systems.

  12. lpha mega Expected Results The balloon satellite shall return two sets of data; infrared and visible light levels, both as a function of altitude: • First set of data, infrared: Altitude ought to relate to the infrared light levels inverse proportionally; • Second et of data, visible: Light levels should have a directly proportional relationship to altitude; With this information it can be determined whether or not high resolution telescopic images are feasible with a lighter than air vehicle.

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