Dynamics modeling method and system of space film diffractive imaging satellite

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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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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