A control method for spacecraft rendezvous between orbits of unstable translation points of the sun-earth system

Abstract

The invention provides a method for controlling the rendezvous between orbits of a spacecraft at an unstable translation point of the sun-terrestrial system. The method includes: determining the initial orbit, target orbit and time of the rendezvous process of the spacecraft at the orbit rendezvous of the translation point of the sun-terrestrial system, and establishing a controlled aerospace based on the established controlled spacecraft rendezvous dynamics model, a nonlinear optimal control problem is established; the nonlinear optimal control problem is solved by the symplectic numerical method in a finite time, and the co-state variables are obtained; The obtained co-state variables update the control input of the current sub-time interval, complete the dynamics simulation of a sub-time interval, and use the navigation method to obtain the current spacecraft state variables; carry out the progress of the sub-time interval, taking the current spacecraft terminal state as the lower For the initial state of a sub-time interval, steps 302 to 400 are repeated in sequence until the task of rendezvous between the orbits of the unstable translation point of the spacecraft is completed. The invention can ensure the objectivity and performance of high-precision spacecraft rendezvous.

Description

technical field [0001] The invention relates to the technical field of spacecraft deep space exploration, in particular to a control method for spacecraft rendezvous between orbits of unstable translation points of the sun-earth system. Background technique [0002] Deep space exploration, especially space exploration near the translation point, is an important research task in the field of spaceflight in recent years. figure 1 It is a schematic diagram of the circular restrictive three-body model of the Sun-Earth system. refer to figure 1 , due to the balance of gravity and centrifugal force at the three collinear unstable translation points of the circular restricted three-body problem, these spatial positions are ideal places for placing space equipment such as space stations and space telescopes. figure 2 It is the rendezvous diagram of the spacecraft between the north and south Halo near the L2 translation point of the sun-earth system. refer to figure 2 , a typic...

AI Technical Summary

Problems solved by technology

[0003] The invention mainly solves the problem that the open-loop control of the rendezvous of the spacecraft between the orbit families of the unstable translation points of the sun-earth system is easily affected by external interference and model errors, and proposes a method for the spacecraft to rendezvous between the orbits of the unstable translation points of the sun-earth system. The rendezvous control method adopts online solution for open-loop nonlinear optimal control, and continuously updates the control input to form closed-loop control. Feedback information can be used to offset the influence of external disturbances and model errors, ensuring the objectivity and performance of high-precision spacecraft rendezvous

Images