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A lamination optimization method for a composite material structure

A composite material and optimization method technology, applied in design optimization/simulation, special data processing applications, instruments, etc., can solve problems such as simultaneous variable interaction, different scales of design variables, and a large number of design variables, etc., to reduce calculation time, Achieving versatility and reducing development time

Active Publication Date: 2019-04-05
CHINA ACAD OF LAUNCH VEHICLE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Not only increases the optimization cycle, but also cannot achieve universality
The second problem is that the scale of design variables for structural optimization of composite materials is different from that of metal structures. It is manifested in the large number of design variables, both discrete and continuous types, and the mutual influence between variables.

Method used

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  • A lamination optimization method for a composite material structure
  • A lamination optimization method for a composite material structure
  • A lamination optimization method for a composite material structure

Examples

Experimental program
Comparison scheme
Effect test

Embodiment

[0062] Such as figure 2 , to optimize the ply lay-up design of Beam1-Beam5 stringers, whose cross-section is π-shaped beam, and the optimization variables are W, H, W1 such as image 3 shown.

[0063] Material: T800H-6k-603A composite material fabric

[0064] Optimization method: gradient algorithm

[0065] Design variables: Beam sections W, H, W1 of Beam1-Beam5

[0066] Constraint response: 1mm

[0067] 1mm

[0068] 1mm

[0069] All beams are free from instability;

[0070] The maximum tensile and compressive strains of all elements are within the allowable range.

[0071] Optimization goal: the total mass is minimized.

[0072] Add the above optimization methods, optimization variables, responses, and optimization objectives into the BDF file for secondary development.

[0073] The BDF after secondary development is imported into Nastran for calculation, and it converges after 5 iterations. The optimization results are shown in Table 1.

...

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Abstract

The invention discloses a lamination optimization method for a composite material structure, and belongs to the field of aircraft structure mechanism design. According to the method, a finite elementmodel of the composite material laminated plate structure is established in the PATRAN according to the composite material structure needing to be optimized; Optimization objectives are set well, Constraint conditions, The method comprises the following steps: firstly, designing basic parameters such as variables according to NASTRAN calling parameters, thereby realizing subsequent content refinement of optimization algorithm embedding, optimization objectives, constraint conditions, design variables and the like on the basic parameters by using a PCL language, and finally establishing a composite material structure layering optimization model file for NASTRAN calling, thereby finishing the optimization design of the composite material structure layering.

Description

technical field [0001] The invention relates to a layer optimization method of a composite material structure, which belongs to the field of aircraft structural mechanism design. Background technique [0002] With the increasing design requirements of aircraft and the extremely harsh service environment, it is imminent to develop new materials and new structures. Composite materials have the advantages of high specific strength, high specific stiffness, fatigue resistance, and corrosion resistance. It has been widely used in manufacturing, and the designability of composite structures provides designers with a broader design space. By optimizing its layering angle and layering sequence, the performance indicators of the structure are finally improved. Therefore, the optimization of composite material structure has important practical significance. In the practical engineering application of composite material structure optimization, there are two main problems. One is that...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/23
Inventor 姚宇地吴迪肖凯刘赛张涛郭爱民熊艳丽陈飞邓云飞彭波孔文秦徐方舟石小亮宋春雨张斌
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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