Pneumatic elastic mechanical characteristic analytical method of hypersonic speed aircraft in thermal environment

Abstract

The invention relates to a pneumatic elastic analytical method, and provides a pneumatic elastic mechanical characteristic analytical method of a hypersonic speed aircraft in thermal environment. According to the method, the piston theory is used for carrying out frequency domain nonsteady aerodynamic calculation on a full-aircraft finite element model of the hypersonic speed aircraft; on the basis, the pneumatic thermal effect on the model in the hypersonic speed thermal environment is considered; the weak coupling effect of pneumatic thermal input in aerodynamic input and elastic force input is ignored; only the structure temperature steady-state characteristics under the pneumatic thermal load effect are considered; after the steady aerodynamic calculation, the thermal flux density on the surface of the aircraft is obtained by adopting a reference enthalpy method; further, the steady temperature distribution on the surface of the aircraft is calculated; the practical equivalent rigidity matrix of the structure at the moment is obtained; and the critical flutter speed is calculated by an engineering method. The pneumatic elastic mechanical characteristic analytical method has the advantages that the pneumatic elastic analytical problem of the hypersonic speed aircraft in the pneumatic thermal environment is solved, and the pneumatic elastic performance of the hypersonic speed aircraft is improved through flutter speed analysis.

Description

technical field [0001] The invention relates to an aeroelastic analysis method in the field of aerospace, in particular, it is an aeroelastic analysis method for a hypersonic vehicle in consideration of thermal effects. Background technique [0002] In the initial stage of aeroelastic research, the usual method is to make linearization assumptions based on structural and fluid dynamic models, and the flutter boundary problem is ultimately the solution of the eigenvalues ​​of the non-self-accompanied system model. The non-self-accompanied system model is constructed based on the differential equations of flutter motion, and reliable results can also be obtained for the analysis of simple harmonic vibration characteristics near the critical point of flutter. The disadvantage of this method is that the model needs to be assumed to be linear, and if there is a nonlinear aeroelastic problem in the system, it is powerless. With the development of aircraft theory, the structure ad...

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Problems solved by technology

The disadvantage of this method is that it is necessary to make a linear assumption on the model. If there is a nonlinear aeroelastic problem in the system, it is powerless

However, the calculation process is complicated and the workload is heavy, especially in the direct coupling of CFD / CSD in the time domain method, which puts forward high requirements on the configuration of the computer, which limits its application range in engineering practice

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