摘要
文中研究了空间飞行器大角度机动飞行的姿态控制律的设计问题。空间飞行器姿态系统的数学模型由四元数方法描述,以克服欧拉角描述方法在大角度机动时存在的奇异性问题,通过引入状态变换,应用稳定性理论研究了姿态控制律的设计问题,并在设计中考虑了外部扰动存在时的鲁棒性问题。针对某飞行器的参数进行了数值仿真,结果说明了文中方法的有效性。
Attitude controller design of spacecraft large angle maneuver flight is descussed in this paper.To eliminate the singularity of Euler description arising in large angle maneuver flight,quaternion description is used to describe attitude system of spacecraft.By the introduction of state transformation,stability theory is applied to the study of attitude controller design problem.The robustness to external disturbances is also considered in the design. Numerical simulation is conducted for parameters of certain spacecraft,and the results justify the effectiveness and feasibility of the proposed method.
出处
《弹箭与制导学报》
CSCD
北大核心
2003年第S3期256-258,共3页
Journal of Projectiles,Rockets,Missiles and Guidance
