Optimal orbital transfer method of low-earth-orbit satellite under limited thrust by taking J2 perturbation into consideration

Abstract

The invention discloses an optimal orbital transfer method of a low-earth-orbit satellite under a limited thrust by taking J2 perturbation into consideration, relates to the optimal orbital transfer method of the low-earth-orbit satellite, and belongs to the field of aerospace. The optimal orbital transfer method comprises the following steps of: establishing a dynamic equation of a spacecraft by taking the J2 perturbation into consideration; solving a Hamiltonian function H corresponding to an optimal fuel consumption performance index according to the states of the spacecraft at the beginning and the end; solving an optimal control rate and a corresponding covariance equation according to a pontryagin maximum principle; constructing a two-point boundary value problem shooting equation set meeting the optimal fuel consumption according to an optimal control condition of a variational method; solving the two-point boundary value problem shooting equation set according to the states of the spacecraft at the beginning and the end as well as the flight time to obtain the optimal control rate formed by an optimal thrust control direction and an engine switching function; and controlling the orbital transfer of the satellite by using the control rate, so that the real-time performance and the orbital transfer precision in the transfer process of the low-earth-orbit satellite can be increased, and the fuel consumption required for the orbital transfer is reduced. The optimal orbital transfer method disclosed by the invention is suitable for the orbital transfer process of the low-earth-orbit satellite when a limited thrust model is adopted by an engine.

Description

technical field [0001] The invention is an optimal orbit change method of a near-earth satellite considering J2 perturbation, which is applicable to the orbit change process of a near-earth satellite under a limited thrust model, and belongs to the technical field of aerospace. Background technique [0002] Satellite orbit change is one of the most common operations for spacecraft in space. Compared with the large thrust vector of the rocket engine, the thrust of the engine on the spacecraft is generally small. In the process of implementing the thrust, the single thrust time and the thrust arc are relatively long, resulting in the thrust vector being a real-time variable in the inertial space. , still using the pulse design can not reasonably reflect this control process. Therefore, the real-time control design should be adopted for the orbit change strategy with limited thrust. For spacecraft in orbit, the quality of its fuel determines the working life of the spacecraft...

AI Technical Summary

Problems solved by technology

[0005] The technical problem to be solved by the method for the optimal orbit change of a near-earth satellite with limited thrust considering J2 perturbation disclosed by the present invention is to improve the real-time performance and orbit change accuracy of the near-earth satellite transfer process, and reduce the fuel required for orbit change transfer. consume

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