Track control method applied to non-cooperative maneuvering target interception

Abstract

The invention discloses a track control method applied to non-cooperative maneuvering target interception. The method presents an interception concept taking a target motion estimation as basis and aclose distance approached terminal control as the interception concept; the method presents two-impulse optimal track changing method on the basis of track changing fuel optimization model in a remoteguiding stage; at the close distance tracking and approaching stage, a relative motion model is built up by considering that the target has maneuvering uncertainty, and the target motion estimation method is presented; finally, for achieving accurate interception, the method of applying the optimal controlled optimal tracking method to approach the target before the target is not maneuvered and then applying a slide mode control method after the target is maneuvered can be presented to carry out the final interception.

Description

Technical field: [0001] The invention relates to a satellite interception technology, in particular to an orbit control method for non-cooperative maneuvering target interception. Background technique: [0002] Although satellite interception experiments have been carried out for decades, maneuverable targets will undoubtedly bring new challenges. In the event of a war, important space targets in the future will not sit still and will take maneuvering measures to avoid them when they are attacked. Therefore, Space warfare is bound to become increasingly complex. [0003] Therefore, this application proposes the interception technology of non-cooperative maneuvering targets in space, which includes two parts, the long-range guidance stage and the short-range approach stage. [0004] Remote guidance includes the whole process from launching satellite into orbit to running to a position closer to the target, which is similar to the remote guidance in the rendezvous and docking...

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Problems solved by technology

However, there are relatively few studies on this direction at home and abroad. Lu Shan [3] (Lu Shan and Xu Shijie, Research on the Autonomous Approach Control Law of Non-cooperative Targets. China Space Science and Technology, 2008 (5): p. 7-12) etc. Humans use the Lyapunov max-min method to design the autonomous approach control rate for non-cooperative targets maneuvering, but do not consider the trajectory optimization problem in combination with target motion estimation; Lin Jian [4] (Lin Jian, Lin Xiaohui and Cao Xibin, based on adaptive Autonomous orbit determination of maneuvering targets with Kalman filter. Shanghai Aerospace, 2008 (2): 14-18) and others designed an adaptive Kalman filter to determine the target orbit for non-cooperative target maneuvers, providing a Base

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