28-07-2012, 02:17 PM
Cube Satellite Systems Engineering Example
Cube Satellite Structure
The cube structure is an enclosed aluminum box with solar cells clamped on the outside walls. Antennas are deployed perpendicular to the faces at the corners. Internals include sensors, a camera and printed circuit boards.
Mission Information
Pre-imposed design requirements (http://cubesat) include a 10 cm cube, 1 kg mass limitation
The mission objective for this student team is to test in space a GaN-based Ultraviolet (UV) photodetector. The student team was tasked to design, build and operate the CubeSat in Low Earth Orbit (LEO) carrying the photodetector as the payload.
The satellite will be deployed using the standard Poly Picosatellite Orbital Deployer (P-POD). The orbit is 700 km altitude (Low Earth Orbit), sun-synchronous, near-polar, 98° inclination orbit, orbital period: +/- 98 minutes, with 3-5, 10-14 minute communications windows/day, with low power and low data rate.
Design for launch on a Russian Dnepr Rocket
Currently in Phase B: Preliminary Design and Technology Completion.
Management Structure
The program manager is in this case the faculty advisor.
The project manager is responsible for scheduling the development cycle, defining mission requirements and goals, as well as the overall success of the project. He is also responsible for keeping the project costs within budget.
The systems engineer is responsible for guiding the engineering of the project; for defining, verifying and validating system requirements’ flow down to each subsystem; and for the integration and test phases of the project. He/she is also responsible for coordinating system trade studies, managing critical resources/interfaces for each subsystem and failure mode and risk analysis.
Each subsystem leader is responsible for the development and testing of their individual subsystem, and must remain aware of how changes in their subsystem affect other subsystems and the system as a whole. The subsystem leads were selected in anticipation of the probable subsystems.
Team Responsibilities
Systems Engineering Team – Analyzes the characteristics of the mission such as orbit and environment. Ensure all subsystems interface properly and work as one fully integrated satellite. They also guide the engineering of the satellite, ensuring that all mission requirements are met, while bridging the various engineering disciplines. They manages mass and volume budget and oversees all other budgets.
Ground Station Team – Designs, builds, and operates ground station antennas, mounting, enclosure, and computer. Selects and installs operating programs and data processing. Handles communication with AS-1 and tracking of other amateur satellites.
Communications Team – Designs, builds, tests the communication system including: antennas, transceivers and TNCs. Manages the link budget.
Attitude Determination and Control Team– Designs, builds and tests the ADC subsystem to for solar cell orientation to the sun for the EPS and antenna orientation for communication, and includes magnets, hysteresis dampeners, attitude determination algorithm design based on solar cell orientation.
Cube Satellite Structure
The cube structure is an enclosed aluminum box with solar cells clamped on the outside walls. Antennas are deployed perpendicular to the faces at the corners. Internals include sensors, a camera and printed circuit boards.
Mission Information
Pre-imposed design requirements (http://cubesat) include a 10 cm cube, 1 kg mass limitation
The mission objective for this student team is to test in space a GaN-based Ultraviolet (UV) photodetector. The student team was tasked to design, build and operate the CubeSat in Low Earth Orbit (LEO) carrying the photodetector as the payload.
The satellite will be deployed using the standard Poly Picosatellite Orbital Deployer (P-POD). The orbit is 700 km altitude (Low Earth Orbit), sun-synchronous, near-polar, 98° inclination orbit, orbital period: +/- 98 minutes, with 3-5, 10-14 minute communications windows/day, with low power and low data rate.
Design for launch on a Russian Dnepr Rocket
Currently in Phase B: Preliminary Design and Technology Completion.
Management Structure
The program manager is in this case the faculty advisor.
The project manager is responsible for scheduling the development cycle, defining mission requirements and goals, as well as the overall success of the project. He is also responsible for keeping the project costs within budget.
The systems engineer is responsible for guiding the engineering of the project; for defining, verifying and validating system requirements’ flow down to each subsystem; and for the integration and test phases of the project. He/she is also responsible for coordinating system trade studies, managing critical resources/interfaces for each subsystem and failure mode and risk analysis.
Each subsystem leader is responsible for the development and testing of their individual subsystem, and must remain aware of how changes in their subsystem affect other subsystems and the system as a whole. The subsystem leads were selected in anticipation of the probable subsystems.
Team Responsibilities
Systems Engineering Team – Analyzes the characteristics of the mission such as orbit and environment. Ensure all subsystems interface properly and work as one fully integrated satellite. They also guide the engineering of the satellite, ensuring that all mission requirements are met, while bridging the various engineering disciplines. They manages mass and volume budget and oversees all other budgets.
Ground Station Team – Designs, builds, and operates ground station antennas, mounting, enclosure, and computer. Selects and installs operating programs and data processing. Handles communication with AS-1 and tracking of other amateur satellites.
Communications Team – Designs, builds, tests the communication system including: antennas, transceivers and TNCs. Manages the link budget.
Attitude Determination and Control Team– Designs, builds and tests the ADC subsystem to for solar cell orientation to the sun for the EPS and antenna orientation for communication, and includes magnets, hysteresis dampeners, attitude determination algorithm design based on solar cell orientation.