Rendezvous control method for libration point orbit with unknown relative speed

Abstract

The invention relates to a rendezvous control method for a libration point orbit with the unknown relative speed. The rendezvous control method comprises the steps that a nonlinear libration point orbit relative dynamic model is established, a finite time convergence differentiator is designed, and finite time convergence preset performance of libration point orbit rendezvousing is controlled. Through a provided finite time convergence preset performance controlling method based on a finite time convergence observer, it can be ensured that a rendezvous system state meets the actual preset performance in the finite time, that is to say, safe and accurate rendezvous between a tracking spacecraft and a target spacecraft can be achieved in the finite time, and a high-precision robust control strategy is provided for the libration point orbit rendezvous task in deep space exploration.

Description

technical field [0001] The invention belongs to the technical field of autonomous rendezvous of deep-space spacecraft, and relates to an autonomous control method for orbital rendezvous of a translation point based on a finite-time convergent differentiator that only requires relative position information. Background technique [0002] Due to the fact that the circumflex point orbit of the circular restricted three-body problem has properties that low-Earth orbit does not have, it has received a lot of attention. In the past few decades, countries around the world have launched many spacecraft in the sun-Earth libration point orbit. , the Earth-Moon L2 point can attract a lot of attention as a relay station for studying the solar system due to its special spatial location. China successfully launched the "Magpie Bridge" relay satellite on June 14, 2018 to make it run along the Halo orbit at the Earth-Moon L2 point. The cost of these deep-space exploration spacecraft is high...

AI Technical Summary

Problems solved by technology

However, in practical applications, the sensors used to measure the relative velocity are generally expensive. When the spacecraft does not carry the sensor for measuring the relative velocity, the orbital rendezvous of the translation point without velocity measurement will be a challenge

Another problem faced by the rendezvous point orbit is the convergence time of the rendezvous control law

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