Change-material model test design method of load transfer characteristics of aircraft thin-wall structure

Abstract

The invention relates to a change-material model test design method of load transfer characteristics of an aircraft thin-wall structure. The method comprises: firstly, determining scaling ratios of anoverall dimension, a structure stand position and structure thickness of a model test piece; secondly, determining a material of the model test piece; thirdly, determining similarity ratios of physical quantities of an aircraft prototype and the model test piece under a plane stress condition according to similarity indexes; and fourthly, calculating and obtaining a load of the model test piece according to a load of the aircraft prototype and the similarity ratio, finally measuring and obtaining the remaining physical quantities of the model test piece according to the load applied to the model test piece, and reversely inferring and calculating a test result of the aircraft prototype. According to the change-material model test design method of load transfer characteristics of aircraftthin-wall structure provided by the invention, engineering manufacturing difficulty can be eliminated; a material of a model test is changed, and the material with a short material preparation cycle and a low price is used; a test cycle and scale are shortened in a multiplied manner, and costs are saved; and design risks of an aircraft scheme demonstration phase are reduced.

Description

technical field [0001] The invention belongs to the technical field of aircraft structure strength tests, and in particular relates to a design method for a material model test with variable load transmission characteristics of an aircraft thin-walled structure. Background technique [0002] In the demonstration stage of the aircraft structure design scheme, it is necessary to design a static model test to verify the load-carrying characteristics of the structure, accurately and quickly evaluate the structural efficiency of different schemes, and verify the numerical analysis results. [0003] In the existing aircraft structure design method, the design method of model test is generally adopted. However, if the scaling ratio is large in the model design, and the same scaling is used for the thickness and in-plane size of the thin-walled structure of the aircraft, there will be insurmountable manufacturing difficulties in the actual engineering manufacturing process. For exam...

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Problems solved by technology

However, if the scaling ratio is large in the model design, and the same scaling is used for the thickness and in-plane size of the thin-walled structure of the aircraft, there will be insurmountable manufacturing difficulties in the actual engineering manufacturing process. For example, the thickness of the aircraft structural material is 2mm, If the scaling ratio is 20 (too large), the thickness of the model size is 0.1mm. For manufacturing, it is difficult to control the process; if the material used in the prototype has a long preparation period and is expensive, the same material is still used in the model test Will inevitably increase the cost of testing

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