In this paper, a minimum and near-minimum time optimal control laws are developed and compared for a rigid space platform with flexible links during an orientating maneuver with large angle of rotation. The control commands are considered as typical bang-bang with multiple symmetrical switches, the time optimal control solution for the rigid-body mode is obtained as a bang-bang function and app...

This paper is concerned with the development of a control system for rotational maneuver and vibration suppression of a flexible spacecraft. It is assumed that the system parameters are unknown. The design approach presented here treats the problem of spacecraft attitude control separately from the elastic vibration suppression problem. As a stepping stone, a state feedback sliding mode control...

This paper proposes a robust control algorithm for stabilization of a three-axis flexible spacecraft in the presence of model uncertainty, external disturbances and control input nonlinearities. This control algorithm is based on variable structure output feedback control design technique that explicitly accounts for the control input nonlinearities in the stability analysis. Asymptotically and...

ORBCOMM is a LEO communications spacecraft, providing global point to point packet messaging. Two are in operation now, and the rest of the (eventually 36) constellation design spacecraft are currently in integration and test. The ORBCOMM ACS mission is to point a communications antenna to nadir, while maintaining continuous Sun tracking via spacecraft yaw maneuvers. This mission is achieved us...

This paper presents a design of a novel feedforward controller for a large-angle reorientation maneuver of a spacecraft with exible appendages, such as a telecommunication satellite. The controller combines collocated feedback and feedforward control. It uses an eÆcient and conceptually simple numerical method for the computation for an optimal feedforward input shape for a nonlinear exible sys...

The problem of angular motion stabilization by mechanical systems with nonrigid construction is considered. The control is realized in the class of discrete systems with piecewise constant control actions which can lead to appearance and growth of the elastic oscillations of the object construction. The notion of the influence function of a base control on the elastic oscillations is introduced...

The robust optimal attitude control problem for a flexible spacecraft is considered. Two optimal sliding mode control laws that ensure the exponential convergence of the attitude control system are developed. Integral sliding mode control ISMC is applied to combine the first-order sliding modewith optimal control and is used to control quaternion-based spacecraft attitudemanoeuvres with externa...

Abstract This paper aims to study the dynamic modeling and attitude control of a kind slender flexible spacecraft. The basic structure this spacecraft is different from traditional center rigid body with appendages, but bodies at both ends, which are connected by truss structure. Firstly, finite element method adopted establish model spacecraft, vibration frequency damping obtained. unconstrain...