Algorithms of Stabilization of a Spacecraft with Flexible Elements
- 作者: Ovchinnikov M.1, Tkachev S.1, Shestopyorov A.1
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隶属关系:
- Keldysh Institute of Applied Mathematics, Russian Academy of Sciences
- 期: 卷 58, 编号 3 (2019)
- 页面: 474-490
- 栏目: Control Systems of Moving Objects
- URL: https://journals.rcsi.science/1064-2307/article/view/220398
- DOI: https://doi.org/10.1134/S1064230719030146
- ID: 220398
如何引用文章
详细
The methods of stabilization of a spacecraft (SC) main body with two flexible elements (antenna and panel) are studied in this paper. The process of stabilization is impeded by vibrations that occur in the nonrigid elements during the orbital and angular maneuvering of the SC and reduce the accuracy of its orientation. For this reason, the methods are also considered in the context of the problem of damping vibrations in the nonrigid elements. We consider the classical control methods, such as the Lyapunov control and linear-quadratic regulator, as well as the increasingly popular SDRE control (State Dependent Riccati Equation Control), which uses Riccati’s equation with the parameters dependent on the state vector. The control algorithms based on the reduced model of a SC with flexible elements are also described. An SC with flexible elements is assumed to be controlled only by the devices mounted on its body.
作者简介
M. Ovchinnikov
Keldysh Institute of Applied Mathematics, Russian Academy of Sciences
Email: alex.shestoperov@yandex.ru
俄罗斯联邦, Moscow, 125047
S. Tkachev
Keldysh Institute of Applied Mathematics, Russian Academy of Sciences
Email: alex.shestoperov@yandex.ru
俄罗斯联邦, Moscow, 125047
A. Shestopyorov
Keldysh Institute of Applied Mathematics, Russian Academy of Sciences
编辑信件的主要联系方式.
Email: alex.shestoperov@yandex.ru
俄罗斯联邦, Moscow, 125047
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