Double-degree of freedom aeroelasticity experiment measuring device

An aeroelasticity and measurement device technology, which is applied in measurement devices, aerodynamic tests, and testing of machine/structural components, etc., can solve problems such as hindering the improvement of helicopter performance, complex aeroelastic response characteristics of dynamic characteristics, etc., and achieves a small error. , The installation method is simple, the result is accurate

Active Publication Date: 2017-12-29
SHANGHAI JIAO TONG UNIV
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Problems solved by technology

Since the rotor is a nonlinear time-varying system that is coupled with the unsteady flow field, the highly flexible structure and the control system, its aerodynamic flow field, dy...

Method used

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  • Double-degree of freedom aeroelasticity experiment measuring device
  • Double-degree of freedom aeroelasticity experiment measuring device
  • Double-degree of freedom aeroelasticity experiment measuring device

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Experimental program
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Embodiment Construction

[0026] Such as figure 2 As shown, the present embodiment includes: being arranged on the wind tunnel wall test section 1, a top fixing mechanism 2, a wing torsion mechanism 3 and a wing lateral movement mechanism 4, wherein: the top fixing mechanism 2 is arranged on the top of the wind tunnel testing section 1 to fix At one end of the wing, the wing torsion mechanism 3 is set at the bottom of the wind tunnel test section 1 and opposite to the top fixing mechanism 2 for axially twisting and fixing the other end of the wing. The wing torsion mechanism 3 is set at the straight line of the driving wing Mobile wing side shift mechanism 4.

[0027] The wing 5 to be tested is set between the top fixing mechanism 2 and the wing torsion mechanism 3, and the wing 5 to be tested is a three-section rectangular NACA0012 airfoil. This airfoil is used because it is widely used in experiments and numerical values. Research. With a wingspan of 0.9m and a chord length of 0.3m, it is placed v...

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Abstract

Disclosed is a double-degree of freedom aeroelasticity experiment measuring device, comprising a square framework, a top end fixing mechanism, a wing torsion mechanism and a wing side moving mechanism. The top end fixing mechanism is disposed at the top end of the square framework to fix one end of the wing. The wing torsion mechanism is disposed at the bottom end of the square framework, correspondingly disposed to the top end fixing mechanism for axial twisting and fixing the other end of the wing. The wing torsion mechanism is disposed at the wing side moving mechanism for driving the wing to move linearly. The invention is advantageous in that the response of angle of attack variation of a two-dimensional aeroelasticity system oscillation aerofoil and the response of bouncing motion displacement can be effectively measured, and the result is accurate and error is small; the installation method of spring is simple, stiffness factor of two directions of the system can be conveniently changed, and parameterization research can be conducted.

Description

technical field [0001] The invention relates to a technique in the field of wing wind tunnel experiments, in particular to a two-degree-of-freedom aeroelasticity experimental measuring device. Background technique [0002] The helicopter rotor is in a state of unsteady flow when it is flying forward. Since the rotor is a nonlinear time-varying system in which the unsteady flow field is coupled with the highly flexible structure and the control system, its aerodynamic flow field, dynamic characteristics, and aeroelastic response characteristics coupled with the two are extremely complex, which seriously hinders the development of helicopters. Performance improvements. [0003] Accurate measurement of aeroelastic response plays an important reference role for helicopter design. However, it is difficult to directly measure the aerodynamic force or displacement deformation of the three-dimensional rotor blade in the wind tunnel. In the process of related scientific research an...

Claims

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Application Information

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IPC IPC(8): G01M9/00
CPCG01M9/00
Inventor 王福新邱展徐文浩袁家信喻伯平李高华
Owner SHANGHAI JIAO TONG UNIV
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