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Configuration construction and attitude control method of pyramid type deorbit sail

A construction method and pyramid-shaped technology, which is applied in attitude control, non-electric variable control, control/regulation system, etc., 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: 2021-12-31
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

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  • Configuration construction and attitude control method of pyramid type deorbit sail
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  • Configuration construction and attitude control method of pyramid type deorbit 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 type deorbit sail, and belongs to the field of spacecraft attitude dynamics and control. The implementation method comprises the steps that atmospheric resistance and environmental perturbation of the earth shape are considered, a three-dimensional orbit attitude coupling dynamic model based on position vector and quaternion description is established, a deorbit sail is regarded as a rigid body, a spacecraft body is regarded as a mass point, the airflow shielding condition is considered in the windward area, and the precision of the dynamic model is improved; the law of the attitude stability and the deorbit efficiency of the spacecraft about the cone angle of the pyramid-shaped deorbit sail and the rod length of a supporting rod under different conditions is obtained based on the model, the configuration parameters of the pyramid-shaped deorbit sail system are analyzed and optimized based on the law, and the pyramid-shaped deorbit sail with high attitude stability and high deorbit efficiency is obtained; and based on the model and the selected configuration parameters, a quaternion feedback repositioning PID control law is designed. The attitude of the spacecraft provided with the deorbiting sail is stable relative to the speed direction, and the deorbiting efficiency is improved.

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 Applications(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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