Spacecraft relative position control method based on finite-time distributed type speed observer

Abstract

The invention provides a spacecraft formation relative position control method based on a finite-time distributed type speed observer, and belongs to the field of spacecraft formation relative position control. Firstly, according to a spacecraft relative position dynamics model, the graph theory is used for representing the communication topological relationship between formation members; secondly, the finite-time distributed type speed observer is designed; finally, based on velocity observation information, a potential function method is adopted, and the control method which can make the spacecraft formation members reach their desired positions while avoiding collisions during flight is designed. The method achieves the finite-time estimation of the spacecraft speed, a controller can beindependently designed, and the method is suitable for the relative position control of spacecrafts with missing velocity information. The finite-time distributed type velocity observer is adapted totimely and accurately provide velocity estimation information, the relative position of the spacecraft is ensured to reach expected value, and meanwhile the occurrence of collision is avoided.

Description

technical field [0001] The invention belongs to the technical field of relative position control of spacecraft formations, and in particular relates to a relative position control method of spacecraft based on a finite-time distributed velocity observer. Background technique [0002] With the development of aerospace science and technology, spacecraft formation technology has become a new model for performing tasks such as deep space exploration and earth observation. In order to ensure the smooth implementation of the above tasks, multiple spacecraft need to fly in formation in a specific configuration, so relative position control is the most basic requirement in the field of spacecraft formation. Usually the spacecraft flying in orbit can obtain position and velocity information from the measurement of ground target references and known beacons, or use on-board navigation instruments for autonomous sidetracking. However, considering that the velocity of the spacecraft ca...

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Problems solved by technology

[0005] The object of the present invention is to provide a method for controlling the relative position of spacecraft based on a finite-time distributed velocity observer, solve the problem of relative position control of spacecraft formations without velocity measurement information, realize the relative position control of spacecraft formations and avoid the Collision in

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