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Reconfiguration method for optimal formation under J2 perturbation and adopting relative navigation information

A relative navigation and optimal technology, applied in non-electric variable control, three-dimensional position/channel control, instruments and other directions, it can solve the problems of low model accuracy, unable to meet the formation reconstruction accuracy, etc. The effect of real-time processing and strong on-orbit application value

Inactive Publication Date: 2019-04-05
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology

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

Method used

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  • Reconfiguration method for optimal formation under J2 perturbation and adopting relative navigation information
  • Reconfiguration method for optimal formation under J2 perturbation and adopting relative navigation information
  • Reconfiguration method for optimal formation under J2 perturbation and adopting relative navigation information

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Embodiment Construction

[0042] refer to figure 1 , the coordinates of the slave spacecraft relative to the master spacecraft are defined as follows: O-XYZ is the earth-centered inertial coordinate system (ECI), and the orbital radius of the master 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 ; from the orbital radius of the spacecraft to r d , the position vector of the slave spacecraft relative to the master 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 main spacecraft, where the x-axis is related to the orbital radius r of the main spacecraft c In the same direction, the angular momentum of the z-axis and the main spacecraft The directions are the same, and the y-axis satisfies the right-hand rule.

[0043] The purpose of the present invention is to provide a ...

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Abstract

The invention relates to a reconfiguration method for optimal formation under J2 perturbation and adopting relative navigation information, and belongs to the field of space-flight trajectory control.Aiming at the formation reconfiguration problem of formation flying spacecraft considering the J2 perturbation, under the condition that information of a primary spacecraft is unknown and a followingsecondary spacecraft only adopts the relative navigation information, a continuous thrust optimal formation reconfiguration control strategy which does not need an initial predictive value, can perform rapid calculation and is suitable for being used on satellites is provided. The formation flying spacecraft using the reconfiguration method can automatically complete formation reconfiguration without ground guidance information. According to the reconfiguration method for the optimal formation under the J2 perturbation and adopting the relative navigation information, a relative motion equation is not subjected to linear treatment, meanwhile, the influence of earth J2 perturbation on formation reconfiguration is considered, and the reconfiguration method is suitable for continuous thrustformation reconfiguration under an elliptical orbit; and only relative motion information of the primary spacecraft and the secondary spacecraft is used, the formation reconfiguration of formation flying is realized, and ground support is not needed in the reconfiguration process, so that high in-orbit application value is achieved.

Description

technical field [0001] The present invention relates to a method of optimal formation reconstruction under J2 perturbation using relative navigation information, especially a formation reconstruction problem of formation flight, the movement of the master spacecraft considers the earth's J2 perturbation, and the slave spacecraft is in The invention relates to a continuous thrust optimal formation reconfiguration method under the condition of only using relative navigation information, which belongs to the field of spacecraft orbit control. Background technique [0002] With the development of aerospace application technology, there are more and more scenarios where two or more spacecraft fly in formation to complete a task together. During these tasks, it is usually necessary to change the relative position of two or more spacecraft from one mode to Adjusting to another pattern is a process called formation reconfiguration. In addition, it is more hoped that the above tasks...

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Application Information

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IPC IPC(8): G05D1/10
CPCG05D1/104
Inventor 张相宇黄美丽王大轶王永富邹元杰包泽宇赵小宇李佳宁周静
Owner BEIJING INST OF SPACECRAFT SYST ENG
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