Flexible spacecraft integrated modeling method

Abstract

Provided is a flexible spacecraft integrated modeling method. A flexible spacecraft comprises flexible accessories and a central rigid body. The method includes the following steps of firstly, calculating the antithesis momentum of the flexible accessories relative to the mass center of the flexible spacecraft under dynamic conditions through a finite element method and an integration method underthe coordinate system of a flexible spacecraft body; secondly, calculating the antithesis momentum of the central rigid body relative to the mass center of the flexible spacecraft under dynamic conditions through the finite element method and the integration method under the coordinate system of the flexible spacecraft body; thirdly, summarizing the antithesis momentum of the flexible accessoriesrelative to the mass center of the flexible spacecraft in the first step and the antithesis momentum of the central rigid body relative to the mass center of the flexible spacecraft in the second step, and calculating the antithesis momentum of the flexible spacecraft relative to relative to the mass center of the flexible spacecraft under dynamic conditions; fourthly, calculating a flexible spacecraft posture orbit integrated kinetic equation according to the momentum theorem under the inertia coordinate system.

Description

technical field [0001] The invention relates to a spacecraft integrated modeling method, which belongs to the research field of spacecraft dynamics and control. Background technique [0002] At present, for the dynamic modeling of flexible spacecraft, most of them focus on attitude dynamic modeling. The usual method is to use the Newton-Eulerian method or Lagrangian method, and use the principle of mixed coordinates to derive the flexible attachment. A dynamic model of vibration effects on spacecraft attitude motion. For the influence of the vibration of the flexible attachment on the orbital motion of the spacecraft and the coupling effect between the attitude motion and the orbital motion of the spacecraft, there are very few studies on this at home and abroad, and most of the methods used are the Lagrangian method. The attitude motion and orbital motion of the flexible spacecraft are studied independently, and the attitude and orbital dynamics equations are established r...

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Problems solved by technology

This makes it difficult for traditional dynamic modeling methods to qualitatively separate the influence of attitude motion from vibration or orbital motion, which makes it difficult to design controllers and cannot accurately decompose the control to orbital actuators and orbital actuators at one time. Flexible attachment actuators, resulting in deviations in control

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