V-shaped tail support device for flat fusion-body aircraft in transonic wind tunnel

Abstract

The invention discloses a V-shaped tail support device suitable for a flat fusion-body layout aircraft in a transonic wind tunnel. The device aims at solving the problem that when the flat fusion-bodylayout aircraft is subjected to a wind tunnel test, it is difficult for existing straight tail support devices and oblique tail support devices to meet the transonic wind tunnel test requirements ofthe flat fusion-body layout aircraft. The V-shaped tail support device comprises a front section, an equivalent straight section, a first expansion section, a second expansion section, a rear section,a rear-end connection section for being connected with a wind tunnel test section connector and a measuring platform. According to the V-shaped tail support device, a V-shaped inner concave tail support rod is designed, so that it is ensured that the front and rear sections of the V-shaped inner concave tail support rod are coaxial, the axis coincides with the axis of a model fuselage, and therefore the V-shaped inner concave tail support rod can be viewed as an equivalent straight support rod in the test process; a bending design is adopted for the front section of the support rod, the correction difficulty of rear-body damage and support interference of the model is reduced, so that the V-shaped tail support device has the technical advantages of existing straight tail supports and oblique tail supports and overcomes defects of the two kinds of tail supports, and therefore the connection installation and load measurement of the flat fusion-body aircraft in the transonic wind tunnelare achieved.

Description

technical field [0001] The invention relates to the technical field of wind tunnel tests, in particular to a V-shaped tail support device suitable for flat fusion aircraft in a transonic wind tunnel. Background technique [0002] At present, wind tunnel test is the main means to obtain the aerodynamic characteristics of aircraft. During wind tunnel testing, it is most common to use a tail support device to fix the aircraft model in the test section. The selection and design criteria of the aircraft model tail support device in the transonic wind tunnel mainly have the following considerations: 1. The angle of the support system has a simple corresponding relationship with the angle of the model, so that the accurate change of the model test angle can be realized by driving the movement of the support system; 2. .The damage of the support device to the tail of the model should be as small as possible, to avoid excessive damage to sensitive areas such as the sharp rear edge, ...

AI Technical Summary

Problems solved by technology

[0014] The purpose of the present invention is to provide a transonic wind tunnel test for the existing straight tail brace support device and inclined tail brace device when performing wind tunnel tests on a flat fusion body layout aircraft. V-shaped tail support for flat fusion aircraft in wind tunnel

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