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2004 Team

John Shoots. 2004 Team. Nate Stockey. Jared Schott. Caitlin Vanderbush. Mike Wilson. Stephanie Sprague. Josh Shreve. METEOR BACKGROUND. To our knowledge, METEOR is the first, university-based, project in the world whose ultimate goal is to launch and place small payloads:

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2004 Team

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  1. John Shoots 2004 Team Nate Stockey Jared Schott Caitlin Vanderbush Mike Wilson Stephanie Sprague Josh Shreve

  2. METEOR BACKGROUND • To our knowledge, METEOR is the first, university-based, project in the world whose ultimate goal is to launch and place small payloads: • (1) In low Earth Orbit, • (2) on near Earth asteroids, and • (3) lunar surfaces will serve as launching point for future projects, experiments, and research • Benefits of Launching from upper atmosphere • <1% atmospheric density of sea level • Less parasitic drag. Rockets can be launched without payload caps • Eliminates the need for permanent ground launch facilities • Enables launches from different latitudes

  3. Project Objective: Design a recoverable, airborne, high altitude, balloon tethered, 3-axes stabilized platform for future small rocket launches and near space scientific experiments Challenges: To design a system for the rigors of near space (>80,000’), • <1% atmospheric density • High temperature range • Fast and high temperature changes • Radiation • Limited weight

  4. Balloon System Architecture Zero Pressure Balloon Cut-Down Device Parachute Platform

  5. Design • Accommodate 2 lb Rocket • Stepper Motor Orientation Device • 6 lb platform/payload weight limit • Simulated payload • High Definition Digital Camera

  6. System Block Diagram Digital Compass

  7. Flight Computer/FPGA • Altera Apex 20K Development Board • Nios Processor @ 33.33 MHz • 32 bit Processor Core • Virtually Unlimited Serial Ports • Architecture is Defined via GUI/Block Diagram • 5V Digital I/Os through custom daughter-card • 1 Mbyte FLASH Memory • 512 Kbytes Data Memory • Allows Storage of Two Processor Layouts

  8. Communications • Kenwood TH-D7A(G) • Built in TNC • APRS Capable • Global Positioning System (GPS) • Navman Jupiter 8 • NMEA Compatible • Non-System beacon • 147.80 MHz • 7 messages in Morse Code

  9. ATV and High Resolution Camera • Amateur Television (ATV) • Downlink Only: 439.25 MHz (Cable Channel 60) • Low Resolution Board Camera • Monitor payload • Video TX • Video OSD • High Resolution Camera • 5 Mega Pixel Camera Donated by • Payload (first mission)

  10. Cut-down Device • Why do we need a cut-down device? • Detach balloon from system after mission phase is complete • Satisfy FAA requirements • NiChrome wire • Melts through fishing line when sufficient current passed through • 2 Methods of current activation for redundancy • Wireless System • KEYFOB TX on platform, RX on cut-down device • Passes current through NiChrome upon command • PIC Controller (Microchip 12F675) • Redundancy in case of system failure • Cuts down after pre-programmed time

  11. Power • Batteries • Three Battery Packs • UltraLife 9 Volt Lithium Batteries • Regulated to 5 Volts • 2 batteries in parallel • Stepper Motor • 9 Volts • 6 batteries in parallel • Nios and connected circuitry • Regulated to 12 Volts • 3 sets of 2 batteries in series in parallel • ATV (Video TX, OSD, Low-Res Camera) • Donated by

  12. Sensors • Magnetic Compass • Heading information • Pressure • Temperature (Internal, External) • Accelerometer • X,Y,Z acceleration • Donated by

  13. Tracking/Recovery • Ground Station • Mobile Equipment Used • Van, Laptops, 2m XCVR, GPS, Antennas (Mobile, Yagi), Maps (Aeronautical, Road), TV/VCR, Cell Phones • Positions • Range Officer, Flight Director, Communications, Sensors, Dynamics, Payload, CapCom, Recovery Teams

  14. Dynamic Simulation • Atmospheric Soundings for current wind conditions • Updatable APRS data from the platform • Flight Predictions • Buoyant forces • Velocity based drag • Elevation based gas property lookups

  15. Descent path, landing position and mapping • Location recalculated to Longitude and Latitude • Necessary to assess optimal cut-down time and landing location • Post-Mission analysis for improvement of model

  16. Survivability Enclosure

  17. Conclusions • Senior Design Requirements • Provided a prototype of launch platform • Includes necessary hardware to conduct successful launch • Improvements/Suggestions • Carbon Fiber Structure • Batteries that can provide more current • Lower power consumption • Integrated orientation control system

  18. Questions?

  19. BACKUP

  20. Motivation for New Design • Motivation • Smaller Rocket • Federal Aviation Administration Regulations • Ease of launching • Senior Design Schedule

  21. GROUND PLATFORM 2 m AX.25 Packet Encoder AX.25 Packet Encoder Mobile 144 MHz Transceiver Handheld 144 MHz Transceiver LAPTOP RS-232Interface RS-232 Interface Nios AX.25 Packet Decoder AX.25 Packet Decoder 70 cm Packet Modem Packet Modem Amateur TV Receiver Amateur TV Transmitter LNA LR Cam VCR TV Display Video OSD RS-232 Emergency DF Setup 2m Beacon

  22. Ascent and Recovery Stage • Balloon • Zero-Pressure Balloon • Allows for pressure to equilibrate • Initial Volume of 357.9 ft2 • Final Volume of 19,000 ft2 • Parachute • 5 ft diameter nylon • Terminal Velocity of 22 ft/s

  23. Rules & Regulations • Title 14 of the Code of Federal Regulations • Part 101: Moored Balloons, Kites, Unmanned Rockets and Unmanned Free Balloons • Title 47 of the Code of Federal Regulations • Part 97: Amateur Radio Service

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