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METEOR is a university-based project aiming to design a recoverable, airborne, high-altitude balloon tethered platform for small rocket launches and near-space experiments. This project faces challenges such as operating in near-space conditions, low atmospheric density, and varied temperatures. The architecture includes a zero-pressure balloon system, cut-down device, parachute, and various enclosures. The technologies utilized range from digital compasses to flight computers and communication devices. The project involves designing for rigorous near-space conditions and adhering to FAA regulations. The main objectives include creating an efficient launch platform that integrates various systems for successful small rocket launches with optimal hardware and cut-down mechanisms.
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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: • (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
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
Balloon System Architecture Zero Pressure Balloon Cut-Down Device Parachute Platform
Design • Accommodate 2 lb Rocket • Stepper Motor Orientation Device • 6 lb platform/payload weight limit • Simulated payload • High Definition Digital Camera
System Block Diagram Digital Compass
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
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
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)
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
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
Sensors • Magnetic Compass • Heading information • Pressure • Temperature (Internal, External) • Accelerometer • X,Y,Z acceleration • Donated by
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
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
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
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
Motivation for New Design • Motivation • Smaller Rocket • Federal Aviation Administration Regulations • Ease of launching • Senior Design Schedule
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
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
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