Dynamics modeling method and system of space film diffractive imaging satellite

A technology for dynamic modeling and imaging of satellites, applied in the field of dynamics and control of flexible satellites, can solve problems such as ignoring the coupling effect of satellite systems, unfavorable controller design and control accuracy

Active Publication Date: 2018-06-12
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

[0004] For the dynamic modeling of flexible satellites, the common modeling method is to consider the linear velocity and angular velocity of the flexible attachment and the central rigid body of the flexible satellite separately, solve their linear momentum and angular momentum respectively, and then use the momentum theorem and The moment of momentum theorem solves the dynamic equ

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  • Dynamics modeling method and system of space film diffractive imaging satellite
  • Dynamics modeling method and system of space film diffractive imaging satellite
  • Dynamics modeling method and system of space film diffractive imaging satellite

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[0085] The specific embodiments of the present invention will be further described below in conjunction with the drawings.

[0086] Such as figure 1 As shown, a dynamic modeling method of a space thin film diffraction imaging satellite is disclosed, and the modeling method specifically includes;

[0087] S1. Establish satellite body coordinate system, orbit coordinate system and flexible attachment coordinate system.

[0088] Such as figure 2 As shown, the satellite body coordinate system O b X b Y b Z b : O b Is the satellite centroid, O b Z b The axis points perpendicularly to the installation surface of the star, O b X b The axis points to the flying direction of the satellite, O b Y b The direction of the axis is determined by the right-hand rule.

[0089] Orbital coordinate system O o X o Y o Z o : O o Is the satellite centroid, O o Z o The axis points to the center of the earth, O o X o The axis is perpendicular to O in the satellite orbit plane o Z o Point to the direction of ...

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Abstract

The invention discloses a dynamics modeling method and system of a space film diffractive imaging satellite. The method includes: acquiring the dual quaternion of the posture transformation among a satellite body coordinate system, an orbit coordinate system and a flexible appendage coordinate system; using a dual quaternion method to describe the dual momentum of a flexible appendage relative tothe flexible appendage coordinate system and the orbit coordinate system, the dual momentum of the central rigid body of a flexible satellite relative to the orbit coordinate system, the posture integrated dynamics model of the flexible satellite, and the integrated dynamics model of the flexible appendage relative to the central rigid body of the flexible satellite; describing the constraint pf the flexible appendage relative to the rotation of the central rigid body of the flexible satellite. The method has the advantages that the dynamics double-coupling relation of the flexible satellite is described compactly, calculation efficiency is increased, programming can be achieved easily, subsequent controller design is facilitated, and control precision is increased.

Description

technical field [0001] The invention relates to the research field of dynamics and control of flexible satellites, in particular to a dynamic modeling method and system for space film diffraction imaging satellites. Background technique [0002] The development of high-resolution earth observation technology is of great significance to my country's disaster relief search, key area observation and other fields. Space film diffraction imaging binary star formation observation method is a research hotspot in high-resolution observation. Space thin-film diffraction imaging binary star formation is composed of two satellites, one of which carries an eyepiece, and the other carries a diffraction film. The diameter of the diffraction film can reach several meters to tens of meters, and the thickness is only tens of microns. Therefore, the satellite cannot be treated as a rigid body in dynamic description. [0003] The thin-film diffraction imaging binary star formation working in ...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/23G06F2111/10G06F2119/06
Inventor 孙俊张宪亮宋婷宁雷
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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