Spacecraft long-term management stage orbit parameter automatic adjustment method and system

Abstract

The embodiment of the invention provides a spacecraft long-term management stage orbit parameter automatic adjustment method and system. The method comprises an orbit parameter optimization adjustment step of carrying out the optimization adjustment of orbit parameters based on the current target start and stop time of the orbit parameters in a spacecraft long-term management stage, the target orbit periodic change rate at a starting moment, a threshold parameter group, and an extrapolation time amount, generating a corresponding set parameter sequence and an injection orbit parameter of the spacecraft, carrying out difference calculation on the prediction result calculated by the ground control center after the injection orbit parameter is extrapolated by the analogue simulation spacecraft, determining an orbit parameter evaluation sequence used for representing the data characteristics of the multi-dimensional deviation value, and if the evaluation sequence meets the threshold requirement, further optimizing and adjusting the target starting and ending time and the target orbit periodic change rate, and returning to execute the orbit parameter optimization and adjustment step. The method can automatically adjust the orbit parameters of the spacecraft in the long-term management stage, so as to guarantee the stability of the flight attitude of the spacecraft.

Description

technical field [0001] The present application relates to the technical field of spacecraft control, in particular to a method and system for automatic adjustment of orbital parameters in the long-term management stage of spacecraft. Background technique [0002] The guidance, navigation, and control subsystem (GNC subsystem for short) of the spacecraft requires the ground control center to calculate the orbital root number and perturbation parameters of the spacecraft based on the forecast results of the precise tracking and orbit measurement on the ground, and calculate the corresponding orbital parameters Injected into the spacecraft, the spacecraft’s GNC sub-system extracts the instantaneous orbital elements of the spacecraft at that time, the position velocity of the spacecraft, and the azimuth of the sun, etc., to ensure the stability of the spacecraft’s flight attitude. [0003] The existing calculation method of spacecraft injection orbit parameters, according to the...

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Problems solved by technology

[0004] However, due to the long interval of injection of orbital parameters in the long-term management stage of the spacecraft, various sensors on the spacecraft have strict requirements on the flight attitude. For example, during the long-term management of the space laboratory, orbital parameter injection is required to extrapolate the orbital position deviation within 18-24 hours It is not greater than 5km, and the orbital velocity deviation is not greater than 5m / s. Therefore, the existing methods of manually adjusting the orbital parameter epoch time and orbital period variability have low implementation efficiency, many manual operations, and low selection accuracy

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