摘要
软着陆燃耗最优制导控制的结果提出一种用于月球软着陆动力下降过程的显式制导方法。它不包含制动发动机的参数信息 ,也不需要迭代计算 ,测量简单 ,仅需要一个惯性测量单元 (IMU )。
An explicit guidance method based on a polynomial guidance law for the powered lunar soft landing is proposed. It is derived from the minimum fuel path solved by the optimal control theory. The guidance law can adjust the landing point. Information of system parameters are not necessary for the guidance law, neither is any iterative process. An example of a lunar landing is given to demonstrate the optimality and robustness of the guidance law.
出处
《高技术通讯》
EI
CAS
CSCD
2000年第7期88-92,共5页
Chinese High Technology Letters
基金
国家自然科学基金!(19782004)
关键词
月球软着陆
燃耗最优控制
制导控制
Lunar soft landing, Optimal fuel control, Guidance control
