Control of spinning flexible spacecraft by modal synthesisA procedure is presented for the active control of a spinning flexible spacecraft. Such a system exhibits gyroscopic effects. The design of the controller is based on modal decomposition of the gyroscopic system. This modal decoupling procedure leads to a control mechanism implemented in modular form, which represents a distinct computational advantage over the control of the coupled system. Design procedures are demonstrated for two types of control algorithms, linear and nonlinear. The first represents classical linear feedback approach and the second represents an application of on-off control, both types made feasible by the modal decomposition scheme.
Document ID
19770028032
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Meirovitch, L. (Virginia Polytechnic Inst. and State Univ. Blacksburg, VA, United States)
Van Landingham, H. F. (Virginia Polytechnic Inst. and State Univ. Blacksburg, VA, United States)
Oz, H. (Virginia Polytechnic Institute and State University Blacksburg, Va., United States)