Integrated Orbit and Attitude Control for a Nanosatellite with Power Constraints
Integrated Orbit and Attitude Control for a Nanosatellite with Power Constraints
- New search for: B. J. Naasz
- New search for: M. M. Berry
- New search for: H. Kim
- New search for: C. D. Hall
- New search for: B. J. Naasz
- New search for: M. M. Berry
- New search for: H. Kim
- New search for: C. D. Hall
Small satellites tend to be power-limited, so that actuators used to control the orbit and attitude must compete with each other as well as with other subsystems for limited electrical power. The Virginia Tech nanosatellite project, HokieSat, must use its limited power resources to operate pulsed-plasma thrusters for orbit control and magnetic torque coils for attitude control, while also providing power to a GPS receiver, a crosslink transceiver, and other subsystems. The orbit and attitude control strategies were developed independently. The attitude control system is based on an application of LQR to an averaged system of equations, whereas the orbit control is based on orbit element feedback. In this paper we describe the strategy for integrating these two control systems and present simulation results to verify the strategy.
Document information
Integrated Orbit and Attitude Control for a Nanosatellite with Power Constraints
2003
22 pages
Report
No indication
English
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