A method for manufacturing an aircraft wind tunnel model shell

Abstract

The invention relates to an aerodynamic testing device, in particular to a method for manufacturing an aircraft wind tunnel model shell. The method adopts a large-component integral forming method, that is, an aircraft is divided into five parts: a front fuselage, a middle fuselage, a wing, a rear fuselage and a vertical flat tail, and each part is integrally formed by using a polymer composite material; the connecting mode between components adopts resin adhesive bonding; and the digital model design is completed on UG and CATIA design platforms. By adopting the method, the following effectscan be finally realized: the overall quality of an aircraft wind tunnel model is improved, and the light weight of the model is realized; and furthermore, fast manufacturing can be quickly performed,thereby greatly reducing the manufacturing cost.

Description

technical field [0001] The invention relates to an aviation aerodynamic test equipment, in particular to a method for manufacturing an aircraft wind tunnel model shell. Background technique [0002] The wind tunnel test is based on the principle of aerodynamics, fixing the aircraft model or its parts, such as the fuselage, wings, etc. Flight status, get test data. The wind tunnel is the most basic test equipment for aerodynamic research and aircraft development. The development of each new type of aircraft requires a large number of tests in the wind tunnel. The main purpose of the wind tunnel test is to obtain the variation law of various aerodynamic parameters of the aircraft model. To evaluate the flight performance of each aircraft, in addition to factors such as speed, altitude, aircraft weight and engine thrust, one of the most important criteria is the aerodynamic performance of the aircraft. The aircraft wind tunnel test needs to support the entire aircraft model ...

AI Technical Summary

Problems solved by technology

In the shape manufacturing process, only block aluminum sheets can be used, and cast aluminum materials cannot be used, because there may be pores on the surface of cast aluminum, which will affect the aircraft test data; the support frame is generally processed by tool steel, and the connection method is mostly bolts and positioning pins. For riveting, there are also a small number of products that are processed by stacking steel plates or aluminum plate building blocks as a whole, but this method consumes too much material and the overall weight is too large

[0004] In summary, the existing technology has the following disadvantages: 1) The overall manufacturing precision is low, and there are many joints on the surface, which causes turbulence to the high-velocity air and affects the test results; 2) Due to the use of metal materials, the overall quality is too heavy; 3) Manufacturing The cycle is too long, and the general manufacturing cycle is three to six months; 4) The manufacturing cost is high

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