Dynamic modeling method and system for space film diffraction imaging satellite

Abstract

The invention discloses a dynamic modeling method of a space thin film diffraction imaging satellite. The modeling method includes: acquiring a dual quaternion for pose transformation between a satellite body coordinate system, an orbital coordinate system and a flexible attachment coordinate system; The dual quaternion method describes the dual momentum of the flexible attachment relative to the flexible attachment coordinate system and the orbital coordinate system, the dual momentum of the central rigid body of the flexible satellite relative to the orbital coordinate system, and the pose-posture integration dynamics of the flexible satellite The integrated dynamics model of the model and the central rigid body movement of the flexible attachment relative to the flexible satellite; describes the constraints of the flexible attachment relative to the central rigid body rotation of the flexible satellite. The invention compactly describes the double-coupling relationship of the dynamics of the flexible satellite, improves calculation efficiency, is easy to program, facilitates subsequent controller design, and improves control precision.

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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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 equation, although the coupling effect between the central rigid body and the flexible attachment of the flexible satellite is considered, but the coupling effect between the position motion and the attitude motion during the maneuver of the satellite system is ignored, and this independent modeling The method is not conducive to the improvement of controller design and control accuracy

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