1. Critical Design Review Riley Pack, Sebastian Seeds, Greg Stahl, Paul Loeb, Nic Zinner, Pierce Edwards October 17, 2006 Project Frankenfine: A Near Space Mission

2. Mission Overview Objectives: –Take still pictures of the earth and horizon –Record digital video of the satellite and its surroundings –Measure forces acting upon the satellite Expectations: –View of Earth’s horizon from upper atmosphere. –Visual and analytical data about the forces and stresses acting on a satellite.

3. Design Parts: –Aluminum Tape Lightweight, durable adhesive agent for construction. –HOBO data logger (plus accessories) Small computer data logger and additional equipment to sense, record and later upload to a PC temperature information gathered during flight. –Electric Switches (and wires) Electronic components to link the various systems to each other and power. –Still Camera (modified) Portable still image recording device for obtaining visual data during the flight. –Glue gun (and sticks) Adhesive agent and tool for construction.

4. Parts (Continued) –Heating Unit Electronic circuitry to allow data devices to operate at low temperatures. –Foam Core Foam based construction material for satellite frame. –POCKETek Digital Video Recorder Micro digital video recording unit to record video data during flight. –Sandisk 2GB Memory Card 2GB SD flash memory unit for storing video data. –HOBO Pendant G-logger package Data logger and equipment for measuring angular displacement. –Batteries Common power cells for electronics use during flight.

5. Interior Design Drawing

6. Exterior Design Drawing

7. Functional Block Diagram Switch Power Source Heater (Sat 1) Switch Power Source Heater (Sat 2) Switch Power Source Timing Circuit Camera 1 4 Channel HOBO Internal Temperature External TemperatureRelative Humidity Video Camera HOBO Accelerometer (HOBO Pendent G-Data Logger)

8. Schedule Complete Design – 9/21/2006 Submit Proposal – 9/21/2006 Conceptual Design Review Presentation – 9/21/2006 Prototype Design – 10/3/2006 Design Document Revision A – 10/9/2006 Acquire All Hardware – 10/10/2006 Critical Design Presentation – 10/17/2006 Design Document Revision B – 10/17/2006 Testing Final Structural Design – 10/19/2006 Integrate Hardware – 10/24/2006 System Functional Test – 10/31/2006 Cold Test – 11/1/2006 Design Document Revision C – 11/9/2006 Launch Day – 11/11/2006 Design Document Revision D – 11/30/2006 Final Presentation – 12/05/2006

9. Mass Budget ItemMass (g) Still Camera, Film, and Battery150 HOBO Data Logger35.3 Heating units (2)33.2 POCKETek Digital Video Recorder and SD Card30 G-Force Data Logger16.8 Timing Circuit and 12V Battery Pack62.5 9V Batteries (6)273.8 Structure190 Total791.6

10. Monetary Budget ItemAmount Space Grant Funds$275.00+ Pledged Team Funds(if needed)$120.00+ POCKETek Digital Video Recorder$99.50- SanDisk 2GB SD Memory Card$52.99- HOBO Pendant G-Logger Package$99.00- Spare Parts$30.00- Total Shipping$24.00- Total Funds$395.00+ Total Expenses$305.49- Total$89.51+

11. Structural Tests Whip Test: Evaluate the satellite’s ability to withstand the forces acting on it during flight. –Fill structure with mass and attach to flight string –Swing around at high speeds –Success: Structure has no damage after test Drop Test: Evaluates the satellite’s ability to withstand the forces acting on upon landing. –Fill structure with mass –Drop from 10 meters –Success: Structure survives drop intact and with only minor dents. Should have no holes through which hardware could escape. Stair Pitch Test: Evaluates the satellite’s ability to withstand the forces acting on it after landing. –Fill structure with mass –Kick down a flight of stairs –Success: Structure survives intact with only minor dents. Should have no holes through which hardware could escape. Completion Deadline: Thursday, October 19, 2006

12. Environmental Tests Cooler Test: Evaluates the satellite’s ability to withstand the extreme cold of near space. –Fully integrated structure placed in a cooler filled with dry ice for three hours –Data from subsystems collected and analyzed –Success: Data collection of all subsystems occurs with no error and internal temperature remains above 0°C Completion Deadline: Wednesday, November 1, 2006

13. Functional Tests Subsystem Tests: Evaluate the flight-readiness of the satellite’s hardware components. –Still Camera: Ensures that the timing circuit will cause the camera to take pictures for as long as film lasts. –Video Camera: Ensures that the video camera’s battery and memory allow for uninterrupted video footage of the entire flight. –HOBO Data Logger: Ensures that the HOBO Data Logger can be launched on an interval start and that the logger will collect data for the duration of the flight. –Accelerometer: Ensures that the accelerometer can be launched on an interval start and that it will collect data for the duration of the flight. Full System Functional Test: Evaluates the ability of the satellite to operate as a fully integrated system. –Components turned on and left alone for three hours –Data from subsystems collected and analyzed –Success: Data collection of all subsystems occurs with no error Completion Deadline: Tuesday, October 31, 2006

14. Expected Results Still Camera –Timing Circuit will cause camera to take pictures for the duration of the flight –Camera will capture images that will show the curvature of the earth, as well as other features that are only visible from near space Video Camera –Video Camera will record constant, uninterrupted video of the BalloonSat in flight –Video will show views of part of the satellite as well as the current surroundings as the spacecraft ascends and descends

15. Expected Results (Continued) Accelerometer –HOBO Pendant G-Logger will record the forces acting on the satellite along the x-, y-, and z-axes for the duration of the flight –Results will demonstrate the times at which the most stress is placed on the satellite –Highest values will occur directly following burst, when speeds can exceed Mach 1 HOBO Data Logger –Data Logger will track the internal and external temperature of the satellite, as well as relative humidity –Internal temperature will stay above 0°C, while external temperature will drop below -80 °C