Rotational Maneuver and Stabilization of an Elastic Spacecraft
26th IEEE Conference on Decision and Control, 1987
First page number:
Last page number:
The question of attitude control and elastic mode stabilization of a spacecraft (orbiter) with "beam/tip mass" type payloads is considered. A three-axis moment control law is derived to control the attitude of the spacecraft. The derivation of the control moments acting on the spacecraft does not require any information on the system dynamics. The control law includes a reference model and a dynamic compensator in the feedback path. For damping out the elastic motion excited by the slewing maneuver, an elastic mode stabilizer is designed. The stabilization is achieved by modal velocity feedback using force and torque actuators located at the payload end of the elastic beam. Collocated actuators and sensors provide robust stabilization.
Actuators; Dynamics; Feedback control systems; Space vehicles--Attitude control systems
Controls and Control Theory | Dynamics and Dynamical Systems | Electrical and Computer Engineering | Navigation, Guidance, Control and Dynamics | Space Vehicles
Use Find in Your Library, contact the author, or interlibrary loan to garner a copy of the item. Publisher policy does not allow archiving the final published version. If a post-print (author's peer-reviewed manuscript) is allowed and available, or publisher policy changes, the item will be deposited.
Singh, S. N.
Rotational Maneuver and Stabilization of an Elastic Spacecraft.
26th IEEE Conference on Decision and Control, 1987, 26