AsteroidGazer (AG) Design Review - PowerPoint PPT Presentation

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AsteroidGazer (AG) Design Review

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  1. Contractor 3 AsteroidGazer (AG) Design Review

  2. Mission Overview • III. • Formation • Alignment with Star • Pictures • Data downlink • Stationkeeping II. Deployment IV. Deorbit I. Launch

  3. Design Overview • Twelve 3U cubesats • External, deployable telescope feature • Thruster and Attitude control system • Solar and battery power • Ability to individually transmit data to ground • Circular formation for maximum resolution

  4. Phases I and IILaunch and Deployment Pegasus XL – Orbital Sciences Cape Canaveral, FL : Latitude 28°N Launch due East i=28°

  5. Formation Design Line Circle Concentric Circles Y Shape Plus Sin Wave

  6. Formation Design • Decided to focus formation on detecting NEAs with 140 m diameter. • The equally spaced circle formation provided an acceptable maximum number of pixels

  7. 12 Cube Sat Solution Resolution = 250 meters

  8. Configuration Design 3U Cubesat Components Optical System Camera System Solar Panels Attitude Control System Battery System Propulsion System

  9. Telescope Deployment

  10. Components • Power System • Solar panels • Batteries • Communication System • Transmitter • Antenna • Propulsion System • Thrusters • Attitude System • Attitude Determination & Control System • Optical System • Telescope parts • Camera

  11. Power • Primary Power Source: Solar Panels • High quality PCB substrate & Kaptonoverlay. • Generate up to 1 Watt of power each • Number of panels is dependent power required and space available • Backup Power Source: Lithium-Polymer Batteries • High energy density • Previous success on satellites • Battery size is dependent on power required (150 Watt-hour per kilogram)

  12. Power • Regulator: EPS board • Will regulate and monitor power generated. • Under-voltage and over-current protection. • Distributor: Power Distribution Module • Will distribute power to all components in the Cubesat. • Under-voltage and over-current protection.

  13. Communications • Calculated data rate of 80 kb/s. • Estimated fly over GS time of 7 min. • Individual communication of each satellite with ground station. • S – Band Transmitter • 2 mb/s data rate • S – Band patch antenna

  14. Propulsion • Large maneuvers: Pulse Plasma Thruster • Delta V = 250 m/s for mission duration • Typical shot energy 1.8J • Mass <200g including 10g of propellant • Copper Tungsten electrode provides durability • Power draw of less than 0.5W • Specific impulse measured at 590s

  15. ADCS Blue Canyon Technologies XACT Fully integrated solution: • 3 axis stellar attitude determination • 3 Reaction Wheels • 3 torque rods • IMU • Magnetometer • Sun sensors • Computer

  16. ADCS

  17. Optics and Detectors • Cassegrain Reflector • primary concave mirror • secondary convex mirror • CCD (Charge-Coupled Device) Detector • CCD 595 from Fairchild Imaging • Designed for space applications • 9216 x 9216 full frame CCD array

  18. Cost