Upload
von
View
41
Download
5
Tags:
Embed Size (px)
DESCRIPTION
Contractor 3. AsteroidGazer (AG) Design Review. Mission Overview. III. Formation Alignment with Star Pictures Data downlink Stationkeeping. II. Deployment. IV. Deorbit. I. Launch. Design Overview. Twelve 3U cubesats External, deployable telescope feature - PowerPoint PPT Presentation
Citation preview
Contractor 3
I. Launch
III.•Formation•Alignment with Star•Pictures•Data downlink•Stationkeeping
II. Deployment
IV. Deorbit
Twelve 3U cubesats External, deployable telescope
featureThruster and Attitude control systemSolar and battery powerAbility to individually transmit data
to groundCircular 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
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
Resolution = 250 meters
12 Cube Sat Solution
3U Cubesat
Camera System
Attitude ControlSystem
Battery System
Propulsion System
Solar Panels
Optical System
Components
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: Lithium-Polymer 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 determination3 Reaction Wheels3 torque rods IMUMagnetometerSun sensorsComputer
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 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