Finite-thrust driven spacecraft automatic-rendezvous trajectory planning method on basis of convex optimization technology

Abstract

The invention provides a finite-thrust driven spacecraft automatic-rendezvous trajectory planning method on the basis of convex optimization technology. The finite-thrust driven spacecraft automatic-rendezvous trajectory planning method includes building a mathematic model for describing relative motions of two spacecrafts, then executing an automatic-rendezvous trajectory planning algorithm, and finally considering the limitation of the finite thrust in automatic-rendezvous. According to the convex optimization technology, the problem about automatic-rendezvous trajectory planning is optimized and solved, and accordingly the global optimality is guaranteed. Besides, by an efficient solving method, the finite-thrust driven spacecraft automatic rendezvous trajectory planning method is a trajectory planning algorithm with high real-time performance.

Description

Technical field [0001] The invention relates to an autonomous rendezvous trajectory planning method for spacecraft with limited thrust. Background technique [0002] In the past ten years, continuous thrust propulsion technologies represented by electric propulsion, ion propulsion, and light sail propulsion have gradually developed. Compared with high-thrust chemical rockets, this type of propulsion system has large specific impulse, long life, and consumption. It has the characteristics of less fuel and can increase the effective load. The application prospects are very broad. For example, the spacecraft can be sent into the parking orbit by the high-thrust chemical rocket engine, and then the continuous thrust propulsion system will take over the work to complete the follow-up mission. The problem of trajectory optimization under limited thrust has gradually become the research focus of orbit design workers in various countries. [0003] The limited thrust orbit change can be di...

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Problems solved by technology

[0004] The current trajectory planning method for spacecraft autonomous rendezvous lacks the research on applying convex optimization technology to spacecraft trajectory planning

At the same time, other existing trajectory planning algorithms often have a large amount of calculation and a long calculation time. In the case of limited on-board computing power, it is difficult to perform real-time calculations, and thus it is difficult to obtain practical applications.

[0005] In general, a real-time and effective limited-thrust autonomous rendezvous trajectory planning method based on convex optimization technology has not yet been proposed.

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