Transcript PTAR_Contractor 3

Contractor 3
II. Deployment
I. Launch
III.
• Formation
• Alignment with Star
• Pictures
• Data downlink
• Stationkeeping
IV. Deorbit
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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
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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
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Power System
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 Solar panels
 Batteries
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Communication
System
 Transmitter
 Antenna
Propulsion System
 Thrusters
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Attitude System
 Attitude Determination
& Control System
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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
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Backup Power Source: LithiumPolymer 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.
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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
Blue Canyon Technologies XACT
Fully integrated solution:
 3 axis stellar attitude determination
 3 Reaction Wheels
 3 torque rods
 IMU
 Magnetometer
 Sun sensors
 Computer
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Cassegrain Reflector
 primary concave mirror
 secondary convex mirror
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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