Elliptical orbit spacecraft relative position regressing control method based on cascade connection equation

Abstract

The invention provides an elliptical orbit spacecraft relative position regressing control method based on a cascade connection equation. Firstly, an elliptical orbit relative dynamical model of the cascade connection equation is set up. Secondly, a relative position regressing controller is designed based on a cascade connection equation manner. The elliptical orbit spacecraft relative position regressing control method based on the cascade connection equation has the advantages of structuralization and systematization. The design process is made to be more flexible. Subsystems of all ranks of a system can be designed respectively. In addition, the special problems existing in the subsystems can be considered independently. The system can obtain the good overall or local stability, the good following characteristic and the good parameter robustness.

Description

technical field [0001] The invention relates to a short-distance regression control method for an elliptical orbit spacecraft. Background technique [0002] With the in-depth development of space technology, spacecraft with more and more complex structures and functions are continuously sent into space, and the autonomous on-orbit operation of spacecraft and space robots has attracted extensive attention. However, many invalid satellites still in orbit constitute more and more space junk, and even spacecrafts are affected by atmospheric resistance, which causes the orbital altitude to continuously decrease and eventually fall. All of these constitute a non-negligible threat to the development of space missions and the safety of ground personnel. Space debris cleanup and technologies for recovering or repairing failed satellite captures need to be solved urgently, and the spacecraft's short-distance relative orbit control technology is the basis for implementing the above ta...

AI Technical Summary

Problems solved by technology

[0004] In order to meet the requirements of high control accuracy and small control error of the relative position of the spacecraft during on-orbit operation, so as to ensure the safety and reliability of the operation mission, the existing optimal control methods often take a long time to solve and have a large amount of computation. In the case of limited computing power of the on-board computer, it is difficult to realize real-time autonomous control of the relative orbit of the spacecraft, thus limiting its application in space missions.

In general, a mathematical model in the form of cascaded equations suitable for fast calculation of the relative orbit of the spacecraft has not yet been established, nor has it been possible to propose a real-time effective high-precision method for the relative position of the spacecraft terminal approaching process Control Method

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