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

2.  lpha  mega

3.  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.  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  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  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 Objectives

5.  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.  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.  lpha  mega Requirements

6.  lpha  mega Design Discussion

7.  lpha  mega 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 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 Design Discussion

8.  lpha  mega

9. Schedule

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

11.  lpha  mega The following tests will be conducted: Test Plan  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 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. 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. Expected Results