Support device and test system for wind tunnel virtual flight test of revolution body aircraft model

Abstract

The invention discloses a supporting device and a testing system for a wind tunnel virtual flight test of a revolution body aircraft model, and the supporting device is characterized in that a tail supporting rod type six-component balance is fixedly connected with a balance rear taper sleeve with a reversely-buckled sleeve through a front taper sleeve at the front part of the model; a hollow flange edge at the end of a reverse-buckling sleeve of the balance rear taper sleeve is fixedly connected with an inner ring of the rolling bearing, the front part and the rear part of the model are connected in series into a whole through a plurality of connecting rods penetrating through the hollow flange edge of the balance rear taper sleeve and the inner ring of the rolling bearing, and the pitching bearing and the yaw bearing are installed on an outer ring of the rolling bearing. A traction cable of the supporting model is connected to an inner ring shaft of the pitching bearing and an inner ring shaft of the yawing bearing, and the retracting and releasing unit pulls the pitching bearing and the yawing bearing through the traction cable so as to pull the rolling bearing; by adopting the technical scheme, the mass center of the revolution body aircraft model can be kept immobile, the rolling, pitching and yawing freedom degrees of the model are released to carry out a wind tunnel virtual flight test, and the aerodynamic parameters of the model can be measured by using a tail support rod type six-component balance at the same time.

Description

technical field [0001] The invention relates to the technical field of missile or rocket wind tunnel virtual flight test, in particular to a test device and a test system for the virtual flight test of a revolved aircraft model wind tunnel. Background technique [0002] Wind tunnel virtual flight test is an advanced technology that simulates various flight states of the aircraft in real time through autonomous control in the wind tunnel, and achieves the purpose of verifying and evaluating the design of the flight control system. Dynamic characteristics research and so on provide the necessary technical basis. In addition, the main aerodynamic parameters of the model can be measured at the same time as the test to predict the aerodynamic performance of the aircraft. [0003] In the wind tunnel virtual flight test of the swivel or swivel-like aircraft model, some supports cannot release all the rotational degrees of freedom, and the conventional tail support balance design t...

AI Technical Summary

Problems solved by technology

[0004] In the prior art, the paper "Development of Support Device for Virtual Flight Test in 2.4m Transonic Wind Tunnel" published by Mao Daiyong, Zhao Zhongliang and others discloses a support device for virtual flight test in wind tunnel. The yaw mechanism in the support device According to the aerodynamic load on the model, the cylinder-driven model needs to make real-time response yaw motion. The overall mechanism is relatively complicated. At the same time, because the yaw mechanism is driven by the cylinder-driven model, it is easy to cause errors due to interference during the actual test process.

Moreover, in this paper, the support system divides the model into two sections, the tail-supported six-component balance design technology of the conventional test cannot be adopted, but the ring-type double-end supported four-component balance design technology with a mandrel is used instead. Capable of measuring the four aerodynamic components of normal force, lateral force, pitch moment and yaw moment

In addition, a relatively thick cross-bar support model is added in the middle of the model, which not only limits the degree of freedom of the model's yaw movement, but also increases interference to the incoming flow, affecting the quality of the test

Images