A method for evaluating the thermal strength of aerospace aircraft with large gradient and extremely high temperature

Abstract

The invention discloses a method for evaluating the thermal strength of an aerospace aircraft with a large gradient and extremely high temperature, which relates to the technical field of aircraft design and includes the following steps: S1, intercepting actual feature data; S2, thermal strength experiment; Construction; S4, data comparison; S5, secondary experiment of thermal strength; S6, secondary construction of thermal strength calculation model; S7, secondary comparison of data; S8, weighted calculation of final value of strain; S9, weighted calculation of final value of displacement. The present invention provides an accurate and comprehensive thermal strength evaluation method for a complex curved surface structure of an aerospace aircraft with a large gradient and extremely high temperature, aiming at the complex curved surface structure of an aircraft under a large gradient and fast time-varying extreme high temperature environment. The development of aerospace aircraft provides theoretical support.

Description

technical field [0001] The invention relates to the technical field of aircraft design, in particular to a method for evaluating the thermal strength of an aerospace aircraft with a large gradient and extremely high temperature with a complex curved surface structure. Background technique [0002] In the field of aerospace, with the strong military demand and the promotion of advanced technology, hypersonic aerospace aircraft has become a cutting-edge weapon and equipment developed by countries all over the world in the 21st century. In the field of aircraft design technology, accurate thermal strength assessment for key structural components of aerospace aircraft is an indispensable link in the development process of aerospace aircraft. [0003] The nose cone is a key structural component of an aerospace aircraft, and usually has a complex curved surface shape, which is referred to as a "complex curved surface structure" in the present invention. During the flight of the a...

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Problems solved by technology

The main problems of the thermal strength evaluation based on numerical calculation are: the thermal strength calculation model of complex curved surface structures under the environment of large gradient and fast time-varying extreme high temperature cannot fully reflect the real structural state, resulting in inaccurate thermal strength evaluation; The main problem in the evaluation of thermal strength is that it is difficult to obtain strain data at places with large curvature of complex curved surface structures (such as corners / edges) and high temperature places above 1000°C during the experiment, which makes the thermal strength characteristics of complex curved surface structures unable to be comprehensive. Mastery, resulting in an incomplete assessment of the corresponding heat intensity

[0005] In view of the fact that the main problems of the above two evaluation methods cannot be solved for a long time, how to realize accurate and comprehensive thermal intensity evaluation for the complex surface structure in the extreme high temperature environment with large gradient and fast time-varying has become the key point in the development process of aerospace aircraft. One of the problems, there is an urgent need for corresponding technical inventions

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