Coorbital satellite autonomous relative position keeping method based on laser loads

Abstract

The invention relates to a coorbital satellite autonomous relative position keeping method based on laser loads. On-satellite autonomous orbit determination is achieved through a navigation constellation or orbit determination is measured through a ground station, the satellite position initial reference is obtained, determination of the relative positions between two space satellites and time unification of systems are achieved by combining inter-satellite laser ranging and communication integrated loads with rotary table pointing information, a target constellation is resolved through the current position of each star of the constellation, the existing position information and the target position information are compared, the relative position keeping requirement of each star is determined, the enveloping and pose deformation requirements of each star are resolved, the change rate of a satellite orbit is changed by solar wing position adjustment and deformation and adjustment of the perturbation influence, and accordingly relative position keeping of coorbital satellites is achieved, all the stars in the constellation can run in a relative good form after the orbit is affected by perturbation, and the orbit decay influence is reduced.

Description

Technical field [0001] The invention relates to the technical field of satellite operation trajectory and attitude control, in particular to a method for maintaining the autonomous relative position of a co-orbit satellite based on a laser load. Background technique [0002] Aerospace technology is one of the most promising high-tech technologies in the world today. Space applications have evolved from traditional high-orbit and single-satellite applications to high- and low-orbit satellites, constellation group applications and single-satellite independent applications. . At the same time, with the fierce competition for high orbit positions in space, low-orbit constellation applications have become an important form of space applications. The low-orbit communication system represented by the Iridium satellite system and the orbital communication system, the composite constellation navigation system represented by Beidou and GPS, and the low-orbit ground remote sensing system r...

AI Technical Summary

Problems solved by technology

In the propeller-based active control mode, the satellite uses the propeller to change orbit to maintain the relative position of the constellation. The position is determined by using the ground measurement and control network, the navigation constellation and the inter-satellite communication, and the data is processed by the ground. Due to the non-renewable nature of the propellant , The system has poor long-term on-orbit ca

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