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

A support system and wind tunnel test technology, applied in aerodynamic tests, machine/structural component testing, measuring devices, etc., can solve the problems of high cost, high precision of results, large scale error, etc., and achieve reusability Good, small frictional damping, safe protection effect

Inactive Publication Date: 2011-09-07
BEIHANG UNIV
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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

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

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Embodiment Construction

[0028] The specific implementation manner of the present invention will be described below in conjunction with the accompanying drawings.

[0029] Such as figure 1 Shown is an axonometric view of a two-degree-of-freedom support system, which includes a rotating module ( figure 2 ), translation module (such as image 3 shown), measurement modules (such as Figure 4 shown), the protection module (as shown in Figure 5) and the interface module (such as Figure 6 Show).

[0030] Such as figure 1 and figure 2 As shown, the rotary module includes a rotary pair, which includes a turntable bearing (10) and a trolley platform (4), for simulating the pitching motion of an aircraft. Turntable bearings have small frictional damping moment and can withstand axial and radial loads.

[0031] Such as figure 1 and 3 As shown, the translation module according to an embodiment of the present invention includes two linear guide rails (11) and such as four slide blocks (9), which form a...

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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...

Claims

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Application Information

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IPC IPC(8): G01M9/04
Inventor 吴志刚韩鹏王立波杨超
Owner BEIHANG UNIV
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