Method for analyzing composite structure with complex configuration of lunar explorer

A technology of composite materials and analysis methods, applied in the field of analysis of composite material structures, can solve problems such as complex structural connections, lack of complex composite material structure analysis of lunar exploration vehicles, etc.

Active Publication Date: 2016-04-13
SHANGHAI AEROSPACE SYST ENG INST
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Problems solved by technology

[0003] The load-bearing spherical crown adopts a "dome-type" structure, which bears a large concentrated load and is complicated to connect with other adjacent structures. It is a composite material structure made of carbon fiber composite material prepreg. This method for analyzing composite structures of complex configurations of lunar exploration vehicles

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  • Method for analyzing composite structure with complex configuration of lunar explorer
  • Method for analyzing composite structure with complex configuration of lunar explorer
  • Method for analyzing composite structure with complex configuration of lunar explorer

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Embodiment Construction

[0041] The following will combine Figure 1 to Figure 11 The analysis method for the complex structure of the lunar exploration vehicle provided by the present invention is elaborated in detail, which is an optional embodiment of the present invention. It is revised and polished.

[0042] The invention provides a method for analyzing a complex composite material structure of a lunar exploration vehicle, comprising the following steps:

[0043] S1: Establish the finite element model of the overall propulsion instrument cabin structure, the finite element model includes the load-bearing spherical crown 4, the cylinder section 2, the installation inverted cone 5, the cross partition 1 and the storage tank arranged on the load-bearing spherical crown , its structure matches the overall structure of the actual propulsion instrument cabin;

[0044] In an optional embodiment of the present invention, in the step S1, when establishing the finite element model of the tank, it is simp...

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Abstract

The invention provides a method for analyzing a composite structure with complex configuration of a lunar explorer. The method comprises the following steps of S1 establishing a finite element model for an integral structure of a cabin of a propulsion apparatus; S2 defining a material of each structural member and modelling a composite in the structure; S3 setting a preset load condition and submitting to carry out operation, and then outputting a stress strain result of a bearing spherical crown and entering the step S4; outputting a displacement result of the bearing spherical crown and entering the step S5; S4 utilizing the stress strain result to analyze the strength and viewing whether to meet design requirements; S5 utilizing the displacement result as a boundary to carry out stability analysis and viewing whether to meet design requirements; after completing the steps S4 and S5, if the design requirements are both met, entering the step S6; S6 carrying out experimental verification on the actual load condition of the integral structure for force transmission and load bearing of the bearing spherical crown in the integral structure; and S7 carrying out static experimental verification on the independent bearing spherical crown.

Description

technical field [0001] The invention relates to the field of lunar exploration aircraft, in particular to an analysis method for composite material structures with complex configurations of the lunar exploration aircraft. Background technique [0002] Aircraft (flightvehicle) is an instrumental flying object that is manufactured by humans, can fly off the ground, fly in space and is controlled by humans in the atmosphere or in the space outside the atmosphere (space). [0003] The load-bearing spherical crown adopts a "dome-type" structure, which bears a large concentrated load and is complicated to connect with other adjacent structures. It is a composite material structure made of carbon fiber composite material prepreg. This is a method for analyzing complex composite structures of lunar exploration vehicles. Contents of the invention [0004] In order to solve the above technical problems, the present invention provides a method for analyzing composite material struct...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/23
Inventor 王瑞凤杨颜志张玉花韩涵王勇宋林郁
Owner SHANGHAI AEROSPACE SYST ENG INST
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