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A distributed aerodynamic fusion orbit coupling attitude perturbation analysis method

A technology of perturbation analysis and orbit coupling, applied in the field of spacecraft flight research, can solve the problems of deflection of solar panels, affecting the windward area, and the angle between the solar panels and the main body of the spacecraft, so as to improve calculation accuracy and improve simulation. The effect of efficiency

Active Publication Date: 2022-07-05
中国空气动力研究与发展中心设备设计与测试技术研究所
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Problems solved by technology

However, for large-scale spacecraft flying without control, there is no reliable and effective method to predict the random rollover of its attitude. At the same time, collisions may occur during high-speed motion. There is a certain angle between the solar panel and the main body of the spacecraft, which affects the determination of the windward area

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  • A distributed aerodynamic fusion orbit coupling attitude perturbation analysis method
  • A distributed aerodynamic fusion orbit coupling attitude perturbation analysis method
  • A distributed aerodynamic fusion orbit coupling attitude perturbation analysis method

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Embodiment 1

[0067] Please refer to figure 1 , figure 1 This is a schematic flow chart of a method for analyzing a distributed aerodynamic fusion orbit coupling attitude perturbation. Embodiment 1 of the present invention provides a distributed aerodynamic fusion orbit coupling attitude perturbation analysis method. The method includes:

[0068] Step 1: Establish a perturbation analysis model for the number of spacecraft on-orbit flight orbits;

[0069] Step 2: use the quaternion method to describe the position and attitude motion of the spacecraft, and establish a perturbation analysis equation of the aerodynamic fusion orbit coupling attitude based on the attitude dynamics equation and the perturbation analysis model of the on-orbit flight orbit element;

[0070] Step 3: Obtain multi-source data of the spacecraft's on-orbit flight process, the multi-source data includes: the position information of the spacecraft, the speed information of the spacecraft, the attitude information of the ...

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Abstract

The invention discloses a distributed aerodynamic fusion orbit coupling attitude perturbation analysis method, which relates to the field of spacecraft flight research. pose motion, and establish the perturbation analysis equation of the coupled attitude of the aerodynamic fusion orbit based on the attitude dynamics equation and the perturbation analysis model of the orbital number of the orbital flight; obtain the multi-source data of the spacecraft in-orbit flight process, the multi-source data includes: The position information of the spacecraft, the speed information of the spacecraft, the attitude information of the spacecraft and the sailboard information of the spacecraft are processed by using the perturbation analysis equation of the aerodynamic fusion orbit coupling attitude to process the multi-source data to obtain the tracking results of the spacecraft state. The parameter identification of the solar panel angle of the spacecraft is carried out to obtain the identification results; the error factors of the identification results are quantitatively analyzed, which improves the calculation accuracy of the spacecraft on-orbit flight and re-entry prediction.

Description

technical field [0001] The invention relates to the field of spacecraft flight research, in particular to a distributed aerodynamic fusion orbit coupling attitude perturbation analysis method. Background technique [0002] At the end of its life, the process of uncontrolled return and re-entry of a large spacecraft to the earth's atmosphere needs to go through the process of orbital decay, re-entry disintegration, and dispersal of disintegrated debris. In order to reliably predict the time and position and velocity information of the spacecraft's de-orbit and re-entry, it is necessary to take countermeasures in advance and provide feasible de-orbit input parameters for the calculation of the disintegration process and debris scattering, which requires a reliable orbit prediction model. However, the flight process of large spacecraft will be affected by cross-basin aerodynamic forces in the atmospheric environment of low-Earth orbit. At the same time, under the action of spac...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/20G06F30/15G06F113/08G06F113/26G06F119/14
CPCG06F30/20G06F30/15G06F2119/14G06F2113/26G06F2113/08Y02T90/00
Inventor 高兴龙李志辉陈钦丁娣彭傲平蒋新宇梁杰唐小伟
Owner 中国空气动力研究与发展中心设备设计与测试技术研究所
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