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Configuration construction and attitude control method of a pyramidal off-orbit sail

A construction method and pyramid-shaped technology, which is applied in attitude control, control/regulation system, non-electric variable control and other directions, can solve the problem that the de-orbit efficiency of the pyramid-shaped off-orbit sail cannot meet the needs of use, and achieves improved attitude stability and stability. The effect of de-orbiting efficiency and improving accuracy

Active Publication Date: 2022-05-10
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0004] In order to solve the problem that the off-orbit efficiency of the pyramid-type off-orbit sail used for the de-orbit of the spacecraft at the end of its life or after completing the task cannot meet the use requirements, one of the purposes of the present invention is to provide a configuration of the pyramid-type off-orbit sail Method, based on the position vector and quaternion description, the three-dimensional orbit attitude coupling dynamic model of the pyramid off-orbit sail system is established, and the sail surface faces the wind when the airflow occlusion is considered in the three-dimensional orbit attitude coupling dynamic model of the pyramid off-orbit sail system The area affects the atmospheric resistance of the pyramid-type off-track sail, and then considers the influence of the windward area of ​​the sail surface on the track and attitude of the pyramid-type off-track sail when the airflow is blocked, and improves the three-dimensional orbit attitude coupling dynamics of the pyramid-type off-track sail system. Based on the accuracy of the learning model, and based on the model, the laws of attitude stability and off-orbit efficiency in different situations with respect to the cone angle and rod length are obtained. Based on the law analysis and optimization of the configuration parameters of the pyramid-shaped off-orbit sail system, the attitude stability is high. and a pyramid-shaped de-orbit sail with high de-orbit efficiency, thereby improving the attitude stability and de-orbit efficiency of the spacecraft

Method used

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  • Configuration construction and attitude control method of a pyramidal off-orbit sail
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  • Configuration construction and attitude control method of a pyramidal off-orbit sail

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Embodiment 1

[0111] It is known that the spacecraft body is a cube satellite with a side length of 0.01m and a mass of 1kg; the number of support rods and membrane sails of the pyramid-shaped off-orbit sail is 4, and the surface density of the membrane sail is 13.2g / m 2 , the linear density of the support rod is 16.3g / m; the initial angular velocity is 0; the initial attitude is y b coincides with the velocity direction; the initial orbital elements of the spacecraft relative to the inertial coordinate system are [a ei Ω ω f] 0 =[6971~7171km 0.005 0.1° 270° 90° 0°]; when the length of the support pole and the maximum area-to-mass ratio of the pyramidal off-track sail are set as constants in the follow-up comparative analysis, the value is l=1m, AMR max =b 2 / m=0.9m 2 / kg; Atmospheric density model adopts NRLMSISE-00 model, atmospheric drag coefficient c d = 2.2, select April 1, 2014 as the initial de-orbit time to calculate the atmospheric resistance at the corresponding time; the contr...

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Abstract

The invention discloses a configuration construction and attitude control method of a pyramid-shaped off-orbit sail, which belongs to the field of spacecraft attitude dynamics and control. The realization method of the present invention is: considering the atmospheric resistance and the environmental perturbation of the shape of the earth, establishing a three-dimensional orbit attitude coupling dynamics model based on the position vector and quaternion description, wherein the off-orbit sail is regarded as a rigid body, and the spacecraft body is regarded as The mass point and the windward area consider the airflow shielding situation to improve the accuracy of the dynamic model; and based on the model, the attitude stability and de-orbit efficiency of the spacecraft under different conditions are obtained. The rule analysis optimizes the configuration parameters of the pyramid-type off-track sail system, and obtains a pyramid-type off-track sail with high attitude stability and high off-track efficiency; based on the above-mentioned model and the selected configuration parameters, a quaternion feedback repositioning PID is designed The control law realizes the attitude stability of the spacecraft equipped with deorbit sails relative to the velocity direction, and improves the deorbit efficiency.

Description

technical field [0001] The invention relates to a configuration construction and attitude control method of a pyramid-shaped off-orbit sail, and relates to a stability analysis and attitude control method for a pyramid-shaped off-orbit sail configured on a spacecraft, belonging to spacecraft attitude dynamics and control field. Background technique [0002] In order to reduce the generation of space debris, active deorbiting of spacecraft at the end of their life or after completing their missions is considered a necessary removal measure. In low earth orbit, especially in the area below 800km, the atmospheric drag has a significant impact on the spacecraft, so the deorbit sail device can be used to increase the windward area of ​​the spacecraft to achieve rapid deorbit. At present, most of the deorbit sails for prototype development and on-orbit tests are planar deorbit sails, and the optimal configuration construction method for the highest deorbit efficiency is seldom pr...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08
CPCG05D1/0833Y02T90/00B64G1/407B64G1/245
Inventor 张景瑞张若楠杨科莹李林澄
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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