1. Contractor 3

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

3.  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. Pegasus XL – Orbital Sciences Cape Canaveral, FL : Latitude 28 °N Launch due East i=28°

5. Line CircleConcentric Circles Y ShapePlusSin Wave

6. FormationMost Likely # of PixelsMaximum # of Pixels Line112 Circle610 Concentric Circles67 Y Shape65 Plus76 Sin Wave58  Decided to focus formation on detecting NEAs with 140 m diameter.  The equally spaced circle formation provided an acceptable maximum number of pixels

7. Resolution = 250 meters 12 Cube Sat Solution

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

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

11.  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: Lithium- Polymer Batteries  High energy density  Previous success on satellites  Battery size is dependent on power required (150 Watt-hour per kilogram)

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

17.  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. COMPONENTCOST Solar Panels25,000 Battery5,000 Antenna4,500 Transmitter8,900 Thrusters18,000 Attitude Control System18,000 Telescope20,000 Photodetector/Camera3,000 EPS4,500 Power Distribution Module7,750 Total114,650 Total Cube Sat Cost1,210,800