An Integrated Modeling Method for Flexible Spacecraft

A flexible spacecraft and modeling method technology, applied in design optimization/simulation, geometric CAD, special data processing applications, etc., can solve problems such as controller design difficulties, uncontrollable decomposition, and control deviations

Active Publication Date: 2021-02-05
SHANGHAI AEROSPACE CONTROL TECH INST
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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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  • An Integrated Modeling Method for Flexible Spacecraft
  • An Integrated Modeling Method for Flexible Spacecraft
  • An Integrated Modeling Method for Flexible Spacecraft

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Embodiment Construction

[0093] In order to make the object, technical solution and advantages of the present invention clearer, the implementation manner of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0094] figure 1 Provided the composition schematic diagram of the central rigid body and the flexible attachment of the flexible spacecraft of the inventive method, set up the flexible spacecraft body coordinate system O b x b Y b Z b :O b is the center of mass of the satellite, O b Z b axis perpendicular to the star-to-ground mounting surface, O b x b The axis points to the direction of satellite flight, O b Y b The orientation of the axes is determined by the right-hand rule. Establish inertial coordinate system O I x I Y I Z I :O I is the center of mass of the satellite, O I Z I axis pointing to the center of the earth, O I x I Axis perpendicular to O in the orbital plane of the satellite I Z I Pointing to the d...

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Abstract

An integrated modeling method for a flexible spacecraft, the flexible spacecraft includes flexible accessories and a central rigid body, comprising the following steps: Step 1, under the coordinate system of the flexible spacecraft body, using the finite element method and the integral method to calculate The dual momentum of the flexible attachment relative to the center of mass of the flexible spacecraft under dynamic conditions; step 2, in the coordinate system of the flexible spacecraft body, using the finite element method and the integral method, calculate the central rigid body relative to the flexible spacecraft under dynamic conditions The dual momentum of the center of mass; step 3, add the dual momentum of the flexible attachment relative to the center of mass of the flexible spacecraft in step 1 and the dual momentum of the central rigid body relative to the center of mass of the flexible spacecraft in step 2, and calculate the flexible spaceflight under dynamic conditions The dual momentum of the spacecraft relative to the center of mass of the flexible spacecraft; step 4, in the inertial coordinate system, according to the momentum theorem, calculate the dynamic equation of the flexible spacecraft attitude-orbit integration.

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...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/23G06F30/15
CPCG06F30/15G06F30/23
Inventor 孙俊张宪亮宋婷宁雷
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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