Static aeroelasticity analysis method, device and apparatus for aircraft and storage medium

Abstract

The invention relates to a static aeroelasticity analysis method, device and apparatus of an aircraft and a storage medium. The static aeroelasticity analysis method, device and apparatus are appliedto high-lift aircraft configuration in a climbing or landing scene. The method comprises the following steps: generating a three-dimensional skin grid of each component in a target component; carryingout steady flow field analysis on each component to obtain an aerodynamic load generated on each component; determining the structural deformation of each component according to the aerodynamic loadon each component; and according to the structural deformation amount of each component, deforming the aerodynamic surface grid and the aerodynamic space grid of each component, and outputting an analysis result of each component when it is determined that static aerodynamic elasticity analysis of each component reaches a preset convergence condition. According to the method, the static aeroelasticity analysis of the low-speed high-lift aircraft configuration can be automatically realized in the whole process, the complexity of the static aeroelasticity analysis of the low-speed high-lift aircraft configuration is simplified, and the analysis efficiency is improved. Meanwhile, the accuracy of an analysis result is also improved.

Description

technical field [0001] The present application relates to the field of aeronautical design, in particular to a static aeroelastic analysis method, device, equipment and storage medium of an aircraft. Background technique [0002] As we all know, the aircraft will deform under the action of aerodynamic force, especially for the large-aspect-ratio aircraft that uses composite materials, the aerodynamic deformation is quite significant, which will lead to a decrease in the control efficiency of the aircraft, and even lead to anti-manipulation and other phenomena. Therefore, for the aircraft It is of great significance to conduct static aeroelastic analysis. [0003] Usually, the static aeroelastic analysis of the aircraft can be carried out by means of the surface element method. However, for low-speed high-lift aircraft configurations, in order to increase the lift of the aircraft, various lift-increasing components have been added to the aircraft, such as leading edge inner ...

AI Technical Summary

Problems solved by technology

However, for low-speed high-lift aircraft configurations, in order to increase the lift of the aircraft, various lift-increasing components have been added to the aircraft, such as leading edge inner slats, leading edge outer slats, leading edge drooping, and trailing edge inner slats. Flaps, trailing edge outer flaps, and multi-section flaps, etc., thus greatly increasing the geometric complexity of the low-speed high-lift aircraft configuration

However, the above-mentioned panel method cannot accurately analyze the static aeroelastic analysis of the complex low-speed high-lift aircraft configuration.

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