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A method for measuring the vibration displacement of helicopter rotor in low-speed wind tunnel test

A technology for helicopter rotor and wind tunnel testing, which is used in measurement devices, aerodynamic testing, and testing of machine/structural components. Effect

Active Publication Date: 2019-12-03
AERODYNAMICS NAT KEY LAB +1
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Moreover, in the wind tunnel test, the high-speed rotation of the rotor will cause the entire rotor test bench to vibrate

Method used

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  • A method for measuring the vibration displacement of helicopter rotor in low-speed wind tunnel test
  • A method for measuring the vibration displacement of helicopter rotor in low-speed wind tunnel test
  • A method for measuring the vibration displacement of helicopter rotor in low-speed wind tunnel test

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Embodiment Construction

[0035] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0036] like figure 1 As shown, this embodiment provides a method for measuring the vibration displacement of a helicopter rotor in a low-speed wind tunnel test.

[0037] Step 1: If figure 2 As shown, five coding marking points are arranged on the hub 1 of the helicopter rotor, which are respectively located at the center of the hub and the upper, lower, left and right positions equidistant from the center of the hub.

[0038] Step 2: If imag...

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Abstract

The invention discloses a helicopter rotor vibration displacement measuring method in a low-speed wind tunnel test, and belongs to the technical field of low-speed wind tunnel test measurement. The method comprises the following steps: arranging a certain number of coded marking points on a helicopter rotor hub; acquiring image data of the helicopter rotor in a stationary state; calculating the three-dimensional coordinates of the coded marker points in the image data, and constructing a rotor coordinate system; acquiring the transient image data of the helicopter rotor in a high-speed rotation state; calculating the three-dimensional coordinates of the hub central coded marker point in the rotor coordinate system; and calculating the transient vibration displacement vector of the helicopter rotor in the high-speed rotation state. The method provided by the invention can effectively measure the vibration displacement deviation caused by the high-speed rotation of the helicopter rotor,is easy to operate, achieves noncontact measurement, and is high in precision and good in safety.

Description

technical field [0001] The invention relates to the technical field of low-speed wind tunnel test measurement, in particular to a method for measuring the vibration displacement of a helicopter rotor in a low-speed wind tunnel test. Background technique [0002] The low-speed wind tunnel test is an important means to measure the performance parameters of the helicopter rotor and study the aerodynamic characteristics of the rotor. In the wind tunnel test, by using various means to measure the performance parameters of the rotor, such as flapping angle, shimmy angle, torsional deformation, etc., the range of motion, deformation status and tip motion trajectory of the rotor can be determined, so as to provide a comprehensive analysis of the rotor structure. The design of the upper and lower limit blocks of the hub, the design of the blade load, and the adjustment of the common taper of the rotor provide important basis. [0003] However, due to the characteristics of the power...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/06G01B11/02
CPCG01B11/022G01M9/06
Inventor 左承林马军梁磊岳廷瑞宋晋王勋年武文军张卫国
Owner AERODYNAMICS NAT KEY LAB
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