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Contractor 3 II. Deployment I. Launch III. • Formation • Alignment with Star • Pictures • Data downlink • Stationkeeping IV. Deorbit 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 Pegasus XL – Orbital Sciences Cape Canaveral, FL : Latitude 28°N Launch due East i=28° Line Circle Concentric Circles Y Shape Plus Sin Wave Decided to focus formation on detecting NEAs with 140 m diameter. The equally spaced circle formation provided an acceptable maximum number of pixels Formation Most Likely # of Pixels Maximum # of Pixels Line 1 12 Circle 6 10 Concentric Circles 6 7 Y Shape 6 5 Plus 7 6 Sin Wave 5 8 12 Cube Sat Solution Resolution = 250 meters 3U Cubesat Components Optical System Camera System Attitude Control System Battery System Propulsion System Solar Panels Power System Solar panels Batteries Communication System Transmitter Antenna Propulsion System Thrusters Attitude System Attitude Determination & Control System Optical System Telescope parts Camera Primary Power Source: Solar Panels High quality PCB substrate & Kapton overlay. Generate up to 1 Watt of power each Number of panels is dependent power required and space available Backup Power Source: LithiumPolymer Batteries High energy density Previous success on satellites Battery size is dependent on power required (150 Watt-hour per kilogram) 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. 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 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 Blue Canyon Technologies XACT Fully integrated solution: 3 axis stellar attitude determination 3 Reaction Wheels 3 torque rods IMU Magnetometer Sun sensors Computer 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 COMPONENT Solar Panels COST 25,000 Battery 5,000 Antenna 4,500 Transmitter 8,900 Thrusters 18,000 Attitude Control System 18,000 Telescope 20,000 Photodetector/Camera 3,000 EPS 4,500 Power Distribution Module 7,750 Total Total Cube Sat Cost 114,650 1,210,800