Adaptive Control and Stabilization of Elastic Spacecraft
Document Type
Article
Publication Date
1-1999
Publication Title
Institute of Electrical and Electronics Engineers Transactions on Aerospace and Electronic Systems
Volume
35
First page number:
115
Last page number:
122
Abstract
This work treats the question of large angle rotational maneuver and stabilization of an elastic spacecraft (spacecraft-beam-tip body configuration). It is assumed that the parameters of the system are completely unknown. An adaptive control law is derived for the rotational maneuver of the spacecraft. Using the adaptive controller, asymptotically decoupled control of the pitch angle of the space vehicle is accomplished, however this maneuver causes elastic deformation of the beam connecting the orbiter and tip body. For the stabilization of the zero dynamics (flexible dynamics), a stabilizer is designed using elastic mode velocity feedback. In the closed-loop system including the adaptive controller and the stabilizer, reference pitch angle trajectory tracking and vibration suppression are accomplished. Simulation results are presented to show the maneuver capability of the control system.
Keywords
Adaptive control; Adaptive control systems; Adaptive systems; Control systems; Feedback; Feedback control systems; Joining processes; Programmable control; Space vehicles; Space vehicles—Dynamics; Space vehicles—Vibration; Stability of space vehicles; Trajectory; Vehicle dynamics; Vibration control
Permissions
Use Find in Your Library, contact the author, or use interlibrary loan to garner a copy of the article. Publisher copyright policy allows author to archive post-print (author’s final manuscript). When post-print is available or publisher policy changes, the article will be deposited
Repository Citation
Singh, S. N.,
Araujo, A. D.
(1999).
Adaptive Control and Stabilization of Elastic Spacecraft.
Institute of Electrical and Electronics Engineers Transactions on Aerospace and Electronic Systems, 35
115-122.