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A Spin Angular Velocity Estimation Method for Non-cooperative Spacecraft Based on Space Circular Trajectory

A spacecraft and non-cooperative technology, applied in the direction of integrated navigator, etc., can solve the problems of divergence of iterative calculation results, large amount of calculation, high initial value requirements, etc., and achieve good engineering realizability, simple method, and avoid the influence of errors Effect

Active Publication Date: 2019-06-18
BEIJING INST OF CONTROL ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The disadvantage of this method is that numerical iteration is used to solve nonlinear problems, the amount of calculation is large, and the iteration has high requirements on the initial value, and there is a problem of divergence of iterative calculation results.

Method used

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  • A Spin Angular Velocity Estimation Method for Non-cooperative Spacecraft Based on Space Circular Trajectory
  • A Spin Angular Velocity Estimation Method for Non-cooperative Spacecraft Based on Space Circular Trajectory
  • A Spin Angular Velocity Estimation Method for Non-cooperative Spacecraft Based on Space Circular Trajectory

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Embodiment

[0099] Such as figure 1 and figure 2 As shown, this part illustrates the calculation process and results of the method provided by the present invention for an embodiment. The purpose of this embodiment is to obtain the direction and magnitude of the spin angular velocity of the non-cooperative spacecraft in the inertial system.

[0100] First, the following assumptions are given:

[0101] a) A non-cooperative spacecraft orbits its own system X T axis spin, the spin angular velocity is 25° / s, and the direction of the spin axis in the inertial system Set to: Spin Axis X T in inertial frame X I Z Iin the plane, and with X I The angle between the axes is 5°, and Z I The included axis angle is 95°. Then, the spin axis X T The unit vector in the inertial system can be expressed as follows:

[0102]

[0103] b) The distance between the binocular camera and the non-cooperative spacecraft is set as L=70m, and the imaging time interval is Δt=1.0s.

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Abstract

The invention relates to a non-cooperative spacecraft spin angular velocity estimation method based on a space circle path. The method is a method for estimating the spin angular velocity and spin direction of a non-cooperative aircraft by utilizing a binocular camera. The method can be used for identifying the spin motion parameter of the space non-cooperative aircraft, has a given engineering application value in the fields such as on-orbit service control, deep space unknown celestial body detection and the like, and belongs to the technical field of on-orbit service. The method of the invention is used for the unknown non-cooperative aircraft on a characteristic point position, and on the premise of not considering the spin nutation, the target spin angular velocity and direction can be directly solved by utilizing a space closed circle path formed by the spin of the characteristic point on the non-cooperative aircraft body. The method is low in requirement for the image quality, and the target spin angular velocity can still be obtained under the situation that the image is fuzzy.

Description

technical field [0001] The invention relates to a method for estimating the spin angular velocity of a non-cooperative spacecraft based on a space circular trajectory. The method is a method for estimating the magnitude and direction of the spin angular velocity of a non-cooperative spacecraft by using a binocular camera, and can be used for a non-cooperative spacecraft in space. The spin motion parameter identification has certain engineering application value in the fields of on-orbit service manipulation, deep space unknown celestial body detection, etc., and belongs to the field of on-orbit service technology. Background technique [0002] For future major projects of on-orbit service, estimating the magnitude and direction of the spin angular velocity of a highly dynamic rolling failure spacecraft or a non-cooperative spacecraft is the basis for its approach and subsequent maintenance operations, and the on-orbit manipulation of such space targets It is also quite diffi...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/24
CPCG01C21/24
Inventor 王鹏基毛晓艳魏春岭何英姿李涛
Owner BEIJING INST OF CONTROL ENG