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A rapid generation method of common-node mesh of beam-slab composite satellite structure

A composite satellite and common-node technology, applied in instrumentation, design optimization/simulation, calculation, etc., can solve a lot of time, high-skilled, tedious work and other problems

Active Publication Date: 2018-11-13
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Since there are generally dozens of honeycomb panels in the satellite structure, the generation of the finite element grid with common nodes of the entire satellite structure will require high skills and a large time and tedious work

Method used

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  • A rapid generation method of common-node mesh of beam-slab composite satellite structure
  • A rapid generation method of common-node mesh of beam-slab composite satellite structure
  • A rapid generation method of common-node mesh of beam-slab composite satellite structure

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Embodiment Construction

[0073] The present invention will be described in detail below in conjunction with the accompanying drawings and embodiments, wherein the finite element software adopts MSC.SimXpert2012.

[0074] The invention discloses a method for quickly generating common-node grids of a beam-slab composite satellite structure, see figure 1 As shown, it includes the following steps:

[0075] Step 1: Import the CAD 3D design model of the satellite structure into the MSC.SimXpert software in the parasolid neutral file format, and then use the midplane extraction function of the software to extract the midplane of all selected honeycomb structural panels; the midplane used in this step The menu of the surface extraction function is Geometry->Mid-Surface->Automatic in turn. In the pop-up user interface, select Constant thickness for the Body type option and select the Delete Solid option. After extracting the mid-surface, the original 3D solid model will be automatically delete;

[0076] Step...

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Abstract

A method for rapidly generating a beam plate composite satellite structure common node mesh is provided. The method comprises the following steps of: step 1: extracting intermediate faces from a geometric model of a satellite structure; step 2: acquiring an intermediate face set that needs to be processed and the number N of elements in the intermediate face set; step 3: performing related operations on all face pairs (A, B); step 4: creating simulated lines of beams; step 5: integrating the simulated lines of the beams into faces on which the simulated lines are located; step 6: stitching all the faces; step 7: partitioning the geometric model of the structure into a two-dimensional finite element mesh; and step 8: creating one-dimensional units. By using the method, the geometric model acquired by extracting the intermediate faces from the three-dimensional entity model of the satellite structure can be automatically processed; gaps between faces can be eliminated; excess parts can be deleted; and the finally generated geometric model can be partitioned into the high-quality beam plate common node finite mesh. The method avoids a large number of human-computer interaction operations, requires less time, is highly universal, is widely applicable, and has great practical engineering value.

Description

Technical field: [0001] The invention relates to a method for quickly generating a common-node grid of a beam-slab composite satellite structure, and belongs to the technical field of spacecraft structure analysis. Background technique: [0002] At present, most satellite structures use honeycomb sandwich panels to bear and transmit mechanical loads, and provide installation support for instruments and equipment. With the advancement of design methods and manufacturing processes, some satellite platforms have begun to adopt beam-slab composite structures as the main load-bearing form, in which the beams are rectangular or I-beams wound with high modulus carbon fibers, which are pre-buried inside the main diaphragm of the satellite. It plays the main load-bearing role; the plate is a carbon fiber skinned aluminum honeycomb panel, which plays an auxiliary supporting role. In order to verify whether the design of the satellite structure meets the requirements, the finite eleme...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
CPCG06F30/23
Inventor 赵军鹏付志方刘腾达王春洁
Owner BEIHANG UNIV