摘要
本文采用四元数法给出了航天器姿态机动的动力学模型，通过引入一种拟欧拉角，根据最优控制理论建立了一种姿态反馈开关控制逻辑，并对闭环系统的稳定性进行了分析。仿真结果验证了所述方法的有效性。
Attitude dynamics model of spacecraft is presented using Euler parameters.Four Euler parameters are transformed into three quasi-Euler angles by a linear transformation. Feedback control laws are designed on the basis of an uncertainty dynamicS model which is expressed in terms of quasi-Euler angles. Simulation is included to illustrate Application of the methods presented.
出处
《宇航学报》
EI
CSCD
北大核心
1994年第2期41-47,共7页
Journal of Astronautics
关键词
姿态控制
反馈控制
姿态动力学
Attitude maneuver, Nonlinear system control, Feedback control, Attitude dynamics.
