摘要
针对航天器接近操作中的制导律设计为主要研究对象。建立了接近操作过程中航天器的相对运动模型,借鉴了巡航导弹的制导方法,通过改进将其应用于空间接近操作中,为使航天器制导系统具有良好的鲁棒性能和自适应性,利用滑模变结构控制理论,提出了基于平行接近法的自适应滑模制导方法,并进行了相应的推导与说明,通过方法证明了闭环系统跟踪误差的渐进收敛。最后以仿真算例验证了方法的有效性,制导结构比较简单,便于工程应用。
In this paper,the design of guidance law in spacecraft proximity operation is the main research object. It establishes the model of relative motion of spacecraft approaching in the course of operation,proposed an adaptive sliding mode guidance method based on parallel approaching method,using the method of cruise missile guidance,through the improvement of its application in spatial proximity operation,and were deduced and the corresponding simulation results,verify the validity of the method.
作者
杨佳
闫杰
尉建利
YANG Jia;YAN Jie;WEI Jian-li(Institute of Flight Control and Simulation,School of Aeronautics,Northwestern Polytechnical University,Xi＇an 710072,China)
出处
《航空计算技术》
2018年第3期13-16,20,共5页
Aeronautical Computing Technique
关键词
接近操作
自适应
制导
变结构
proximity operation
adaptive
guidance
variable structure
