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Double star formation integrated modeling method

A modeling method and double-star technology, which is applied in the directions of space navigation equipment, space navigation aircraft, attitude control, etc., can solve the problems affecting the formation configuration change time and control accuracy, spacecraft collision, and is not suitable for high-precision formation motion descriptions, etc. question

Active Publication Date: 2018-03-16
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

In the actual control process of orbiting satellites, especially for high-density and high-precision formation tasks, the traditional formation dynamics model is adopted. When the formation satellites adjust and maintain the configuration, due to the coupling between attitude motion and orbital motion Influence, attitude control and orbit control need to be adjusted many times, which affects the transformation time and control accuracy of the formation configuration, and may cause collisions between spacecraft at the same time, which is not suitable for the motion description of high-precision formation

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Embodiment Construction

[0136] 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.

[0137] 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

A double star formation integrated modeling method includes a first step of utilizing a finite element method and an integral method to calculate the dual momentum of a flexible attachment with respect to the centroid of a flexible body satellite under dynamic conditions; a second step of using the finite element method and the integral method to calculate the dual momentum of a first center rigidbody with respect to the centroid of the flexible body satellite under dynamic conditions; a third step of calculating the dual momentum of the flexible body satellite relative to the centroid of theflexible body satellite under dynamic conditions; acquiring an attitude track integrated kinetic equation of the flexible body satellite; a fourth step of using the finite element method and the integral method to calculate the dual momentum of a rigid body satellite relative to the rigid body satellite centroid under dynamic conditions; acquiring an attitude track integrated kinetic equation ofthe rigid body satellite; and a fifth step of acquiring a double star formation attitude track integrated kinetic equation according to the attitude track integrated kinetic equation of the flexible body satellite in the third step and the attitude track integrated kinetic equation of the rigid body satellite in the fourth step.

Description

technical field [0001] The invention relates to a double-star formation integrated modeling method, which belongs to the research field of spacecraft power and control. Background technique [0002] For the dynamic modeling of formation satellites, the currently adopted method is usually to model the satellite attitude motion and orbital motion separately, that is, the independent-coupled modeling method, the orbital motion is described by the T-H equation, and the attitude motion is described by the quaternion The method is described because the attitude and trajectory modeling adopt different mathematical methods, which lead to different controller design methods. In the actual control process of orbiting satellites, especially for high-density and high-precision formation tasks, the traditional formation dynamics model is adopted. When the formation satellites adjust and maintain the configuration, due to the coupling between attitude motion and orbital motion Influence,...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
CPCB64G1/244
Inventor 孙俊宋婷张宪亮宁雷
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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