Contractor 3. I. Launch III. Formation Alignment with Star Pictures Data downlink Stationkeeping II....
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Transcript of Contractor 3. I. Launch III. Formation Alignment with Star Pictures Data downlink Stationkeeping II....
![Page 1: Contractor 3. I. Launch III. Formation Alignment with Star Pictures Data downlink Stationkeeping II. Deployment IV. Deorbit.](https://reader031.fdocuments.in/reader031/viewer/2022012918/56649ef05503460f94c014f4/html5/thumbnails/1.jpg)
Contractor 3
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I. Launch
III.•Formation•Alignment with Star•Pictures•Data downlink•Stationkeeping
II. Deployment
IV. Deorbit
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Twelve 3U cubesats External, deployable telescope
featureThruster and Attitude control systemSolar and battery powerAbility to individually transmit data
to groundCircular formation for maximum
resolution
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Pegasus XL – Orbital Sciences
Cape Canaveral, FL : Latitude 28°N
Launch due East i=28°
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Line Circle Concentric Circles
Y Shape Plus Sin Wave
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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
Decided to focus formation on detecting NEAs with 140 m diameter.
The equally spaced circle formation provided an acceptable maximum number of pixels
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Resolution = 250 meters
12 Cube Sat Solution
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3U Cubesat
Camera System
Attitude ControlSystem
Battery System
Propulsion System
Solar Panels
Optical System
Components
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Power System Solar panels Batteries
Communication System Transmitter Antenna
Propulsion System Thrusters
Attitude System Attitude
Determination & Control System
Optical System Telescope parts Camera
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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)
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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.
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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
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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
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Blue Canyon Technologies XACT
Fully integrated solution:3 axis stellar attitude determination3 Reaction Wheels3 torque rods IMUMagnetometerSun sensorsComputer
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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
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COMPONENT COSTSolar Panels 25,000Battery 5,000Antenna 4,500Transmitter 8,900Thrusters 18,000Attitude Control System 18,000Telescope 20,000Photodetector/Camera 3,000EPS 4,500Power Distribution Module 7,750
Total 114,650Total Cube Sat Cost 1,210,800