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Secondary polycondensation method of finite element model of spacecraft

A spacecraft and finite element technology, applied in the field of secondary polycondensation of spacecraft finite element models

Active Publication Date: 2018-05-15
CHINA ACADEMY OF SPACE TECHNOLOGY
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Problems solved by technology

[0009] The technical problem solved by the present invention is: to overcome the deficiencies of the prior art, to provide a secondary polycondensation method of the spacecraft finite element model, to solve the problem that the existing primary polycondensation method cannot handle the secondary polycondensation, and to increase the polycondensation model. Error assessment, and improved computational efficiency and method scalability

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[0064] Some details in the technical solution of the present invention will be further described below in conjunction with the accompanying drawings and a specific embodiment.

[0065] A secondary polycondensation method for a spacecraft finite element model, the process is as follows figure 1 shown, including the following steps:

[0066] Step 1, use MSC.Patran software to establish the finite element physical model of the main structure of the satellite in the launch state, such as figure 2 As shown, the satellite adopts the main structure of "central load-bearing tube + box-plate type", and the finite element physical model of the main structure is modeled by shell elements, with a total of 24,567 nodes and 25,134 units; among them, the central load-bearing tube axial It is parallel to the Z axis of the satellite coordinate system, and the X and Y directions of the coordinate system are respectively parallel to the two normal directions of the satellite deck; the payload ...

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Abstract

The invention relates to a secondary polycondensation method of a finite element model of a spacecraft. Finite element physical models of a main structure and all secondary structures of the aircraftare built respectively, then the finite element physical models of part of the secondary structures are subjected to primary polycondensation through a mixed interface mode synthesis method, and the finite element physical models or a primary polycondensation model of the secondary structures and the finite element physical model of the main structure of the aircraft are assembled to obtain a mixed model; finally, the mixed model is subjected to secondary polycondensation to an aircraft-rocket master node of the aircraft and a carrier rocket through a fixed interface mode synthesis method, a rigidity and quality matrix obtained after secondary polycondensation and a transfer matrix corresponding to an internal response point are acquired, and results are output to be used for coupling loadanalysis of the spacecraft and the rocket. The method solves the problem that an existing primary polycondensation method cannot handle secondary polycondensation, calculation and evaluation of polycondensation errors are added, and the calculation efficiency and accuracy are improved.

Description

technical field [0001] The invention relates to a secondary polycondensation method of a finite element model of a spacecraft, and the model after the secondary polycondensation can be provided to a carrier rocket development party for coupling load analysis. Background technique [0002] The finite element polycondensation technology uses the modal synthesis method to condense the stiffness and mass information of all internal nodes of the finite element physical model on a small number of boundary nodes to generate a polycondensation model and replace the physical model for mechanical analysis. Using the finite element polycondensation model for mechanical analysis can not only avoid outputting technical details of structural design, but also play a role in technical confidentiality when the model is transferred, and can also significantly reduce the number of degrees of freedom in the model itself, which is conducive to improving the calculation efficiency of mechanical an...

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Application Information

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IPC IPC(8): G06F17/50G06F17/16
CPCG06F17/16G06F30/15G06F30/23G06F2111/10
Inventor 尹家聪谢伟华陈曦刘波林勇文李正举田野
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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