Integrated Power and Attitude Control for a Spacecraft with Flywheels and Control Moment Gyroscopes
Abstract
A law is designed for simultaneous control of the orientation of an Earth-pointing spacecraft, the energy stored by counter-rotating flywheels, and the angular momentum of the flywheels and control moment gyroscopes used together as all integrated set of actuators for attitude control. General. nonlinear equations of motion are presented in vector-dyadic form, and used to obtain approximate expressions which are then linearized in preparation for design of control laws that include feedback of flywheel kinetic energy error as it means of compensating for damping exerted by rotor bearings. Two flywheel 'steering laws' are developed such that torque commanded by all attitude control law is achieved while energy is stored or discharged at the required rate. Using the International Space Station as an example, numerical simulations are performed to demonstrate control about a torque equilibrium attitude and illustrate the benefits of kinetic energy error feedback.
- Publication:
-
NASA STI/Recon Technical Report N
- Pub Date:
- January 2003
- Bibcode:
- 2003STIN...0314725R
- Keywords:
-
- Attitude Control;
- Control Moment Gyroscopes;
- Flywheels;
- Spacecraft Control;
- Actuators;
- Control Simulation;
- Computerized Simulation;
- Equations Of Motion;
- Nonlinear Equations;
- Control Theory;
- Spacecraft Maneuvers;
- Flight Management Systems;
- Space Communications, Spacecraft Communications, Command and Tracking