Flexible spacecraft maneuver: Inverse attitude-control and modal stabilization

Document Type



We present a control law for three-axis rotational maneuvers of a spacecraft (orbiter)-beam-tip body (antenna or a reflector) configuration based on nonlinear inversion and modal velocity feedback. Using invertibility and functional reproducibility results, 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 subsystems are used for derivation of a modal velocity feedback stabilizer using the force and moment actuators at the end body. Simulation results are presented to show that in the closed-loop system attitude control and elastic mode stabilization are accomplished in spite of the parameter uncertainty and disturbance torque input in the system.


Aeronautical Vehicles | Aerospace Engineering | Controls and Control Theory | Electrical and Computer Engineering | Electrical and Electronics | Electronic Devices and Semiconductor Manufacturing | Multi-Vehicle Systems and Air Traffic Control | Navigation, Guidance, Control and Dynamics | Power and Energy | Propulsion and Power | 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.

UNLV article access

Search your library