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Method for controlling optimal continuous thrust under J2 perturbation by adopting relative navigation information

A technology of relative navigation and thrust control, applied in the direction of non-electric variable control, three-dimensional position/course control, control/regulation system, etc. The effect of real-time processing on board and strong application value in orbit

Inactive Publication Date: 2019-04-12
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology

[0003] The existing satellite relative motion dynamics model based on the linearization model has low accuracy and cannot meet the requirements of higher rendezvous accuracy

Method used

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  • Method for controlling optimal continuous thrust under J2 perturbation by adopting relative navigation information
  • Method for controlling optimal continuous thrust under J2 perturbation by adopting relative navigation information
  • Method for controlling optimal continuous thrust under J2 perturbation by adopting relative navigation information

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Embodiment Construction

[0042] see figure 1 , the coordinate system of the tracking spacecraft approaching the target spacecraft is defined as follows: O-XYZ is the inertial coordinate system (ECI) centered on the earth, and the orbital radius of the target spacecraft is r c , the orbital inclination is i c , the right ascension of the ascending node is Ω c , the argument of latitude is θ c ; The orbital radius of the tracking spacecraft is r d , the position vector of the tracking spacecraft relative to the target spacecraft is ρ=[x,y,z] T And ||ρ|| is much smaller than ||r c ||. In order to facilitate the description of relative motion, o-xyz is defined as the LVLH coordinate system centered on the target spacecraft, where the x-axis is related to the orbital radius r of the target spacecraft c In the same direction, the z-axis is the same as the angular momentum of the target spacecraft The directions are the same, and the y-axis satisfies the right-hand rule.

[0043] The object of the p...

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Abstract

The invention relates to a method for controlling optimal continuous thrust under J2 perturbation by adopting relative navigation information, and relates to the field of spaceflight orbit control. The method aims at solving the problem of rendezvousing of two spacecrafts operating on an elliptical orbit under J2 perturbation, and the continuous thrust optimal orbit control method which achieves rapid calculation and can be used in orbit is provided under the situation that information of the target aircraft is unknown, and the tracking spacecraft only adopts the relative navigation information. The method does not need an optimized initial predicted value, the influences of earth J2 perturbation on the two-satellite approaching process are considered, and the method is suitable for continuous thrust orbit rendezvousing under the elliptical orbit. The method faces the field of orbit rendezvousing, autonomous orbit rendezvousing of the tracking spacecraft to the target spacecraft can beachieved only through relative motion information of the tracking spacecraft and the target spacecraft without the need of support provided by the ground, and thus quite high on-orbit application value is achieved.

Description

technical field [0001] The present invention relates to an optimal continuous thrust control method under J2 perturbation using relative navigation information, in particular to a rendezvous and docking elliptical orbit spacecraft considering the earth's J2 perturbation, the optimal thrust control method under only using relative navigation information A continuous thrust control method belongs to the field of spacecraft orbit control. Background technique [0002] With the development of aerospace technology, there are more and more demands for on-orbit rendezvous and docking of two satellites, and the technical demand for autonomous operation of spacecraft in orbit without relying on ground control is becoming more and more urgent. At present, advanced continuous thrust technologies such as electric propulsion and solar sails have also been applied to the orbit control of spacecraft, and the requirements for the control accuracy of spacecraft are getting higher and higher....

Claims

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Application Information

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IPC IPC(8): G05D1/10
CPCG05D1/101
Inventor 王大轶张相宇黄美丽包泽宇赵小宇王永富史文华周静赵峭
Owner BEIJING INST OF SPACECRAFT SYST ENG
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