Application of discrete time sliding mode control to a spacecraft in 6DoF with parameter identification
Application of discrete time sliding mode control to a spacecraft in 6DoF with parameter identification
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DOI：
10.1080/00207179.2010.510173
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发表时间：
2010-04
影响因子：
2.1
通讯作者：
N. Lincoln;S. Veres
中科院分区：
文献类型：
--
作者：
N. Lincoln;S. Veres
本文介绍了两个离散时间滑模控制器的应用，结合势函数制导方法，提供控制的刚性，完整的航天器机构只使用推力器的位置和姿态。还包括质量和惯性矩阵参数的识别。这两种控制器的有效性证明了现实的执行器约束下。其中一个控制器还在具有代表性的5自由度（5DoF）测试平台环境中的硬件上实现，以显示该方法的实际性能。
This article presents the application of two discrete-time sliding mode controllers, developed in conjunction with a potential function guidance method, to provide control in both position and attitude for a rigid, holonomic spacecraft body using thrusters only. Identification of mass and inertial matrix parameters is also included. Both controllers are demonstrated for their effectiveness under realistic actuator constraints. One of the controllers is also implemented on hardware in a representative 5 degrees of freedom (5DoF) testbed environment to show the practical performance of the methods.