Method for determining orbit transferring strategy of time-limited spacecraft coplanar rendezvous

Abstract

The invention provides a method for determining an orbit transferring strategy of time-limited spacecraft coplanar rendezvous, and belongs to the field of the time-limited spacecraft coplanar rendezvous. The problem that the accuracy of the rendezvous algorithm calculation is affected caused by the poor observation effect at rendezvous time due to the fact that an existing spacecraft rendezvous technology has relatively low requirements on lighting conditions is solved. The method comprises the steps that the theoretical limiting time of the entire rendezvous process between a target spacecraft and a service spacecraft is calculated; then the two speed increments and the used time of orbit transferring in the service spacecraft orbit transferring process are calculated; initial values of the movement time of an initial orbit and initial values of the movement time of a target orbit for the optimized variable service spacecraft are calculated; integral is carried out on the rendezvous process to obtain position vectors of the service spacecraft and the target spacecraft at the rendezvous time and the angle of the position vectors; when the angle reaches 0 degree, at the moment, themovement time of the initial orbit and the movement time of the target orbit are used as the orbit transferring parameters and the orbit transferring strategy. According to the method, the calculationresults are accurate, and the iterative calculation process is simple.

Description

technical field [0001] The present invention relates to the design of a coplanar rendezvous strategy for spacecraft, in particular to a strategy that provides a feasible limited time interval for the on-orbit service mission planning of a coplanar circular orbit spacecraft, and has high illumination and distance requirements at the end of the rendezvous process. The design of the track change strategy. Background technique [0002] In the coplanar rendezvous problem of geosynchronous orbiting spacecraft, the orbital inclination of the target spacecraft is less than 0.05°. And in the process of co-planar rendezvous, the service spacecraft needs to observe or detect the target spacecraft at a closer distance at the end of the process, so as to complete the on-orbit service process or provide the necessary target spacecraft information for the subsequent on-orbit service process . Therefore, in the coplanar rendezvous process, at the end of the process, it is necessary to ens...

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve the problem that the existing spacecraft rendezvous technology has relatively low requirements on illumination conditions, which leads to poor observation effect at the rendezvous moment and affects the calculation accuracy of the rendezvous orbit change strategy, and proposes a limited-time spacecraft rendezvous Determination method of track change strategy for face-to-face meeting

Images