Spacecraft multi-stage driving rigid-flexible coupling response acquisition method

A rigid-flexible coupling and acquisition method technology, which is applied in the field of spacecraft dynamics, can solve problems such as the coupled dynamics calculation of complex mechanism motion and elastic vibration of spacecraft

Active Publication Date: 2015-07-29
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology

[0004] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, and to provide a method for obtaining the rigid-flexible coupling response of the multi-stage drive of the spacecraft, by providing a set of generalized flexible multi-body dynamics analytical model, and Solve the model to obtain the dynamic response of the spacecraft, and solve the problem of coupling dynamics between the complex mechanism motion and elastic vibration of this type of spacecraft, which can be used for dynamic modeling and rigid-flexible coupling Response calculation, control system design, and co-simulation with control system provide technical support

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  • Spacecraft multi-stage driving rigid-flexible coupling response acquisition method
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  • Spacecraft multi-stage driving rigid-flexible coupling response acquisition method

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specific Embodiment approach

[0041] The implementation process of the whole invention is as follows: image 3 shown. The specific implementation is described in detail as follows:

[0042] (1) Component flexible modeling

[0043] against image 3 For the i-th component in , its dynamic model is established below, and its vibration equation can be written as

[0044] x · · + kx = f - - - ( 1 )

[0045] Among them, m is the mass matrix, k is the stiffness matrix, f is the internal force including the connection with the i-1th structure and the i+1th structure, and x is the node response.

[0046] When component i is connected with front and rear components, its connection interface points need to be considered, such as Figure 4 ξ in ai,1 and ξ ai,2 . Therefore, according to the internal coordinates and interfa...

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Abstract

The invention discloses a spacecraft multi-stage driving rigid-flexible coupling response acquisition method, which comprises steps: (1) the spacecraft is considered to be composed of three structures: a body, parts and joints; (2) kinetic energy and potential energy of the body, the parts and the joints are built respectively; (3) according to a connection condition, kinetic energy and potential energy of the entire spacecraft are built; (4) the kinetic energy and the potential energy of the spacecraft obtained in the third step are used, and a Lagrange equation is adopted to build a kinetic equation of the spacecraft; (5) the kinetic equation obtained in the fourth step is solved, and a rigid-flexible coupling kinetic response of the spacecraft during the multi-stage driving process is acquired. The method of the invention can be applied to a complex spacecraft with flexible multi-body motion features, a precise kinetic response to the motion process of the spacecraft of the complex multi-body structure is acquired, and an important role is played in control system design and system level simulation verification.

Description

technical field [0001] The invention belongs to the field of spacecraft dynamics and relates to a dynamic response acquisition method for flexible multi-body spacecraft. Background technique [0002] With the development of manned spaceflight and communication technology, the spacecraft is gradually developing from a single-axis driven solar wing to a multi-body direction, such as a manned space manipulator, a dual-axis driven solar wing, and a multi-degree-of-freedom driven antenna. This hybrid system of rigid body and flexible body has a large range of rotational driving motion between the bodies, and the elastic vibration of the flexible body is superimposed. This complex dynamic effect of rigid-flexible coupling, as well as the control-structure cross-coupling with the control system, makes the dynamic characteristics analysis of this type of complex spacecraft, especially the dynamic model of the flexible multi-body system in the verification of the GNC control scheme ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B17/02
Inventor 葛东明于伟邹元杰史纪鑫范晶岩关晓东
Owner BEIJING INST OF SPACECRAFT SYST ENG
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