Autonomous orbit maintaining method of satellite based on increment on-line estimation

Abstract

The invention discloses an autonomous orbit maintaining method of a satellite based on increment on-line estimation. The autonomous orbit maintaining method comprises the following steps of S1, acquiring six average orbit instantaneous elements of a satellite orbit; S2, compared with a referring semi-major axis, when an average semi-major axis is attenuated to a certain threshold, placing an orbitcontrol allowing mark; S3, if an orbit mean anomaly of at current moment indicates that the situation that the satellite is located at a far point away from the orbit, entering the orbit keeping control; S4, if in the first control cycle of the orbit keeping control, according to the attenuate degree of the current orbit average semi-major axis, performing calculating to obtain the required increment of the semi-major axis; adopting orbit control increment which can be updated on-line to calculate the jet duration of the orbit control, if not in the first control cycle of the orbit keeping control, judging whether the jet duration of the current orbit control achieves the jet duration of the orbit control or not, and if not, continuing performing jetting, or else, placing an orbit controlfinishing mark, and exiting the orbit control; and S5, calculating deviation between the change quantity of a target semi-major axis and the actual variation of the semi-major axis, and changing theorbit control increment through an update rule of the orbit control increment.

Description

technical field [0001] The invention relates to a satellite autonomous orbit keeping method based on gain online estimation. Background technique [0002] Satellite orbit keeping control generally refers to the control force generated by the control algorithm acting on the satellite, so that the orbital parameters of the satellite can be changed meaningfully, and it is generally realized by the thruster installed on the satellite. [0003] There are two types of thrusters currently in use: pulse jet thrust and continuous small thrust, and the vast majority of spacecraft use pulse jet thrusters of chemical propulsion. Because this thruster can provide a large thrust, the spacecraft can obtain the required speed in a short time, so the problem of orbit control can be simplified, and the design of the controller can be simplified. However, since the output thrust of the thruster is not a constant value, but changes with the change of the fuel reserves on the star, and the mass...

AI Technical Summary

Problems solved by technology

[0004] In summary, due to the change of satellite mass, the error of orbit model modeling and the change of thrust caused by the change of jet pressure, etc., it will have a great impact on the accuracy of orbit control.

In order to ensure the accuracy of orbit control, the orbit control parameters need to be calculated on the ground every time the orbit is controlled. For satellites with very frequent orbit control, it will consume a lot of energy of the relevant staff, which is very inconvenient

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