Relative formation flying and position transfer controlling method based on relative orbit element

Abstract

The invention discloses a relative formation flying and position transfer controlling method based on a relative orbit element. The method comprises long-term formation flying control near a given formation flying point and position transfer control among different formation flying points. Compared with the prior art, the relative formation flying and position transfer controlling method based on the relative orbit element has the advantages of being capable of achieving the control of formation flying, approaching and retreating based on the relative orbit element, achieving the establishment and maintenance of a relative formation flying state between two spacecrafts, and providing conditions for the close space missions.

Description

technical field [0001] The invention relates to satellite guidance, navigation and control technology, in particular to the accompanying flight and formation flight control technology among multiple spacecraft. Background technique [0002] In recent years, small satellite technology has been rapidly developed and applied, providing a wider range of applications in the space field. It is a trend in the development of space technology in the future that multiple small satellites form a formation in a certain configuration to replace the original single complex satellite to complete the task. Compared with the traditional single complex large satellite, the "virtual satellite" composed of multiple small satellites through formation can replace or even surpass the original single complex large satellite in function, and has low cost, strong adaptability, and high reliability Sex and other advantages. [0003] The simplest formation flight technology is to keep two satellites ...

AI Technical Summary

Problems solved by technology

[0003] The simplest formation flight technology is to keep two satellites at a certain distance for accompanying flight. In the current aerospace practice, the method of ground control is generally used to realize the establishment and maintenance of the accompanying flight state of space spacecraft. Hill equation or real-time closed-loop control of the accompanying flight control scheme, the control scheme based on the Hill equation is based on the linearized relative dynamics equation for control law design, the disadvantage of this scheme is that the accompanying flight distance cannot be too far, otherwise the linearization error will be very large and lead to low control accuracy; the accompanying flight control scheme based on real-time closed-loop control law can achieve high control accuracy, but the fuel consumption is large

Images