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- W58804230 abstract "We consider an orbiting spacecraft which consists of a rigid body and a flexible body attached to it. The problem of simultaneous attitude control and vibration suppression of a flexible spacecraft is analyzed in this paper. We derive the equations of motion based on Lagrangian dynamics, taking the motion of instantaneous center of mass into consideration. In the result, we obtain a coupled system of linear partial differential equations governing the elastic vibration of the flexible body and linear ordinary differential equations governing the rotational motion of the rigid body. Since non-standard partial differential equations are derived as a model of the elastic vibration, we consider a finite-dimensional approximation of the solution and its convergence." @default.
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- W58804230 date "1989-06-01" @default.
- W58804230 modified "2023-09-24" @default.
- W58804230 title "Modeling and Control of a Flexible Orbiting Spacecraft" @default.
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- W58804230 doi "https://doi.org/10.1016/s1474-6670(17)53562-4" @default.
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