The invention relates to a deep space probe approach section guidance method based on rendezvous probability, which belongs to the technical field of deep space detection, and aims to solve the problem of low rendezvous guidance precision of an existing deep space probe approach section guidance method. According to the method, the problems of complex deep space environment and more perturbation force are considered in the aspect of navigation, and a more accurate navigation result is obtained by adopting a rank filtering navigation system. In the guidance aspect, the thought of suppressing the sight rotation angular velocity and predicting the guidance law to eliminate the terminal error is combined, and the rendezvous probability is defined as the probability that the detector reaches the target celestial body in the approaching process. Then, the predicted miss distance is determined through the rendezvous probability, and an engine switch curve related to the sight rotation angularspeed is designed through the relation between the miss distance and the sight rotation angular speed, so that the detector can autonomously determine the maneuvering moment, fuel can be well saved,and high guidance precision is achieved.
本发明涉及一种基于交会概率的深空探测器接近段制导方法,属于深空探测技术领域。本发明的目的是为了解决现有的深空探测器接近段制导方法存在交会制导精度低的问题。该方法在导航方面考虑了深空环境复杂摄动力较多的问题,采用秩滤波导航系统获得更精确的导航结果。在制导方面结合抑制视线旋转角速度和预测制导律的消除终端误差的思想,定义了“交会概率”:探测器在接近过程中到达目标天体的概率。然后通过交会概率来确定预测脱靶量,通过脱靶量与视线旋转角速度的关系,设计了与视线旋转角速度相关的发动机开关曲线,使探测器能够自主地确定机动时刻,能够很好地节省燃料并且达到较高的制导精度。
Deep space probe approach section guidance method based on rendezvous probability
基于交会概率的深空探测器接近段制导方法
14.07.2020
Patent
Elektronische Ressource
Chinesisch
Rendezvous guidance of space vehicles
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