CP2 Information
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Systems Engineering
System Requirement Review (SRR) and System Definition Review (SDR)
- PolySat SubSystem Requirments (pdf)(2/19/2003)
Preliminary Design Review (PDR)
- PolySat PDR Presentation (ppt)(6/18/03)
Documents and Files
- CP2 Project Milestones and Schedule (pdf)(1/9/2003)
- Mission Concept and Definition Review (MCR/MDR) (pdf)(1/9/2003)
Command & Data Handling
- 1 PIC 18 Microcontroller at 4MHz 256KB Flash storage capacity
- Constantly monitoring over 50 sensors for voltages, currents, and temperatures throughout the BUS
- Real time clock with 1 sec accuracy Uses I2C Bus at 100 kHz
Documents and Files
- Microcontroller Comparison (xls)(1/13/2003)
- Serial Peripherals List (xls)(1/20/2003)
Communications
- Dual systems provide full redundancy Single dipole antenna
- FSK modulated half-duplex system
- Software configured frequencies (ISM 300MHz - 900MHz)
- 1200 bps downlink, 600 bps uplink
- 500 mW output power
- Onboard AX-25 encoding / decoding
Power
- 2 Li-ion Batteries in parallel configuration
- Designed for both dual and triple junction solar cells
- Max power draw of 3.6 W
- Custom DC-DC conversion for the payload
Mechanical
- 7075 Aluminum structure
- CP Bus mass is only 600 grams, leaving 400 grams for a payload
- Optionally, one face can be used for a payload (8cm x 10cm)
- Volume for payload: 256 cubic centimeters
Attitude Determination and Control
- Magnetorquers in each side board
- 2-axis magnetometer on each side board
- Autonomous detumbling algorithm
Target Missions
All components used on the CP Bus are COTS components. The CP Bus is geared for shorter mission life times of about 3-6 months, Sun-Synchronous Low Earth Orbits (LEO) , and missions that need a responsive conception to launch timeline.
Services Available for Payload
- Volume: 256 cubic centimeters
- Mass: 400 grams
- 3.6 Watt peak power
- 300 mW average power
- One side panel dedicated to the payload (for outside access)
- 128 KB of data storage on bus EEPROM
Prospective Missions
- Remote Sensing
- Communications
- Attitude Determination and Control
- Deployables
- Component Testing (space qualifying)
- Propulsion