Three Axis Rotational Maneuver and Vibration Stabilization of Elastic Spacecraft
Document Type
Conference Proceeding
Publication Date
6-10-1987
Publication Title
American Control Conference, 1989
Publisher
IEEE
First page number:
1106
Last page number:
1111
Abstract
We present a control law for three-axis rotational maneuvers of a spacecraft-beam-tip body configuration based on nonlinear inversion and modal velocity feedback. A decoupling attitude control law is presented such that in the closed-loop system the attitude angles of the spacecraft are independently controlled using the control moments acting on the space vehicle. This controller asymptotically decouples the flexible dynamics from the rigid one and also allows the decomposition of the elastic dynamics into two subsystems representing the transverse deflections of the beam in two orthogonal planes. These low-order sub-systems are used for the derivation of a modal velocity feedback stabilizer using the force and moment actuators at the end body. Simulation results are presented to show the capability of the controller.
Keywords
Attitude control; Control systems; Force control; Force feedback; Nonlinear control systems; Open loop systems; Space vehicles; Torque control; Vehicle dynamics; Velocity control
Disciplines
Electrical and Computer Engineering | Engineering | Signal Processing | Systems and Communications
Language
English
Permissions
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.
Repository Citation
Singh, S. N.
(1987).
Three Axis Rotational Maneuver and Vibration Stabilization of Elastic Spacecraft.
American Control Conference, 1989
1106-1111.
IEEE.