Method and system for obtaining aerodynamic loads on aircraft components

Abstract

The invention relates to a method and a system for acquiring the aerodynamic load of an aircraft component. The method comprises steps as follows: an appearance mathematical model and pressure distribution database of the aircraft component and a calculation work condition are input; a force coefficient and moment coefficient database is acquired in combination with the appearance mathematical model and pressure distribution database of the aircraft component with a gridding vector method; a force coefficient and a moment coefficient under the work condition are acquired through interpolation on the basis of the force coefficient and moment coefficient database, and the aerodynamic load of the aircraft component is acquired. The method and the system for acquiring the aerodynamic load of the aircraft component have the benefits as follows: the mathematical principle is correct, operation is simple and convenient to implement, the method and the system have remarkable advantages in treatment of the aerodynamic load of an irregular structure of an aircraft, and the work efficiency is improved; the method and system are suitable for solving the aerodynamic load of any component of the aircraft and is superior to a traditional profile integral method due to the fact that the appearance of the aircraft is taken into consideration.

Description

technical field [0001] The present invention relates to methods and systems for obtaining aerodynamic loads of aircraft components. Background technique [0002] Based on the wind tunnel test pressure measurement data or the component pressure distribution database provided by the computational fluid dynamics major, the total load and distributed load of the aircraft components under specified working conditions can be calculated and solved for strength calculation and analysis by the strength professional. [0003] The conventional method for the flight load major to process the wind tunnel pressure measurement data or the pressure distribution data provided by the computational fluid dynamics major into the aerodynamic load of aircraft components is the cross-section integral method. The core of this method is to project the aircraft components, and obtain the basic elements (such as action center, area, moment arm, etc.) The workload is large, the operation is complicate...

AI Technical Summary

Problems solved by technology

The core of this method is to project the aircraft components, and obtain the basic elements (such as action center, area, moment arm, etc.) The workload is heavy, the operation is complicated, and the completion cycle is long. If the component configuration changes, the rework cycle is long and the efficiency is low.

Moreover, this method cannot consider the real shape of aircraft components, especially for small parts with irregular shapes, the calculation accuracy is insufficient, and the calculation efficiency is not high

Images