Two-degrees-of-freedom supporting system for wind tunnel test of airplane

Abstract

The invention provides a two-degrees-of-freedom supporting system for a wind tunnel test of an airplane. The entire system comprises a rotating module (rotary table bearing for simulating pitching movement of the airplane), a translational module (linear guide rail for simulating plunging motion of the airplane), measuring modules (an angular displacement meter and a linear displacement meter formeasuring angular displacement and linear displacement), protecting modules (a disc brake and a shock absorber for limiting and protecting a test model) and an interface module (a shaft connected with the test model). The system is connected with an airplane module through a connecting module, and two degrees of freedom including pitching and plunging can be provided to simulate the flying pitching and plunging movement of the airplane; the angular displacement meter and the linear displacement meter can be used for measuring an attack angle and plunging displacement; a disc brake braking device can be used for limiting the pitching movement of the airplane model; and the shock absorber is used for limiting the plunging displacement of the airplane model and can be used for reducing an impact load, so that the test model is protected.

Description

technical field [0001] The patent of the present invention relates to a two-degree-of-freedom support system for aircraft wind tunnel tests, which can realize the simulation of the two rigid-body degrees of freedom of aircraft pitching and sinking, thereby completing wind tunnel test research with real aircraft as the object. Background technique [0002] Wind tunnel test is an important technical method to study the characteristics of aircraft. The plane is flying in the air, in a free-free state, not only has elastic modes, but also has six rigid body modes. Traditional wind tunnel tests are mainly aimed at aircraft components (such as wings), and the test models are mostly fixed at the root. In this way, only the elastic mode of the aircraft can be considered, while the rigid body motion mode of the aircraft is ignored. In addition, the wind tunnel test of simple components ignores the influence between aircraft components, and the test results are not as accurate as the...

AI Technical Summary

Problems solved by technology

Traditional wind tunnel tests are mainly aimed at aircraft components (such as wings), and the test models are mostly installed at the root. In this way, only the elastic mode of the aircraft can be considered, while the rigid body motion mode of the aircraft is ignored.

In addition, the wind tunnel test of simple components ignores the influence between aircraft components, and the test results are not as accurate as the results of the wind tunnel test of the whole aircraft

The conventional full-aircraft wind tunnel test also has many problems, such as complex manufacturing of the full-aircraft test model, large scale error, high cost, suspension system will affect the flow field around the aircraft, etc.

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