Attitude control of nonrigid spacecraft
Flexible spacecraft attitude control and classification systems based on mathematical models
Engineering topics
Publications and source records attributed to Likins, P. W..
Flexible spacecraft attitude control and classification systems based on mathematical models
Hybrid coordinate formulation for flexible space vehicle attitude control system design
Comparative evaluation of attitude control system
The purpose of this report is twofold: (1) to survey the established analytic procedures for the simulation of controlled flexible space vehicles, and (2) to develop in detail methods that employ a combination of discrete and distributed ("modal") coordinates, i.e., the hybrid-coordinate methods. Analytic procedures are described in three categories: (1) discrete-coordinate methods, (2) hybrid-coordinate methods, and (3) vehicle normal-coordinate methods. Each of these approaches is described and analyzed for its advantages and disadvantages, and each is found to have an area of applicability. The hybrid-coordinate method combines the efficiency of the vehicle normal-coordinate method with the versatility of the discrete-coordinate method, and appears to have the widest range of practical application. The results in this report have practical utility in two areas: (1) complex digital computer simulation of flexible space vehicles of arbitrary configuration subject to realistic control laws, and (2) preliminary control system design based on transfer functions for linearized models of dynamics and control laws.
Computerized simulation of attitude controlled flexible space vehicles
Hybrid coordinate formulation for flexible space vehicle attitude control system design
Rotational dynamics equations in linearized matrix form applied to satellite librations in circular orbit and gyroscope motion
Rotating spacecraft attitude changes due to energy dissipation from angular deformation treated by modal method
Modal model using deformation modes of slightly flexible, lightly damped structure to analyze effects of energy dissipation on free body motions of spacecraft
Rotating spacecraft attitude changes due to energy dissipation from angular deformation treated by modal method