Spin Stabilization of the ORION Satellite Using a Thruster Attitude Control System with Optimal Control Considerations
Abstract
The controlled system is the ORION satellite spinning about its single axis of symmetry. Hydrazine thrusters are used as the control and are modeled by ideal, constant magnitude step functions. The system is normalized and driven from non-zero initial angular velocities of the two axes other than the spin axis to the final condition zero. The control profiles required to do this are determined based on a desired controller duty cycle. Adaption of the duty cycle changes the ratio of the time the thrusters are on (fuel use) and total time to completion of the evolution. A comparison between a single axis and a dual axis controller is presented. Simulation programs for the normalized system using a single axis controller simulation program, with each controller having a duty cycle of no more than 50%, are developed. Operation of the system is optimized using a system cost function. An equation relating the controller duty cycle of the dual system to the fuel/time trade-off parameter of the system cost function is required. A nonlinear feedback control algorithm (function of attitude angle rates) is developed from iterations of the simulation, and a priori knowledge of the form of the control from optimal control theory. This numerical solution will allow system designers to incorporate a closed form state feedback control for minimum fuel/time strategies using the ORION satellite's onboard software. Keywords: Spin stabilization; Satellite attitude control systems. Theses.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1989
- Accession Number
- ADA208484
Entities
People
- Janet L. Cunningham
Organizations
- Naval Postgraduate School