Airfoil model force measurement system

A model and airfoil technology, applied in the field of measurement systems, can solve problems such as load mismatch, small resistance component signal, small resistance, etc., to achieve the effect of improving measurement accuracy, high support stiffness, and eliminating errors

Inactive Publication Date: 2017-01-04
CHINA ACAD OF AEROSPACE AERODYNAMICS
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Problems solved by technology

However, there are still the following two problems: (1) the resistance is very small and the load is extremely mismatched, the signal of the resistance component is small, and the anti-interference ability is weak; (2) the stiffness of the cantilever support system of the single balance is weak, and the model is under the action of aerodynamic force. It will produce a large elastic deformation, and there will be a relatively severe jitter phenomenon at a high angle of attack

Method used

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  • Airfoil model force measurement system
  • Airfoil model force measurement system
  • Airfoil model force measurement system

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Embodiment Construction

[0063] The present invention will be further described in detail below in conjunction with the accompanying drawings, so that those skilled in the art can implement it with reference to the description.

[0064] Such as Figures 1 to 4 As shown, the present invention provides an airfoil model force measuring system, comprising: a pair of brackets 63, 56, all vertically arranged; Slidingly arranged on each support; resistance measurement balance 47, which is connected to one of the connecting seats, used to measure the side resistance of the airfoil model under the wind tunnel test; resistance and pitching moment measurement balance 54, which is connected to another connecting seat, used to measure the pitching moment and resistance on the other side of the airfoil model under the wind tunnel test; a pair of connecting rods 50, 52 are arranged between the pair of brackets Between, one end of one of the connecting rods is connected to the resistance measuring balance, one end o...

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Abstract

The invention discloses an airfoil model force measurement system comprising a pair of supports, a pair of connecting bases, a drag measurement scale, a drag and pitch moment measurement scale, a pair of connecting rods, and a pair of lift measurement devices. The supports are arranged vertically. The connecting bases are respectively arranged on the supports in such a way that the connecting bases can slide along the supports without friction loss. The drag measurement scale is connected to one connecting base. The drag and pitch moment measurement scale is connected to the other connecting base. One end of one connecting rod is connected to the drag measurement scale, one end of the other connecting rod is connected to the drag and pitch moment measurement scale, and the other ends of the connecting rods are connected to the front end of an airfoil model to support the airfoil model between the supports. The lift measurement devices are respectively arranged on the supports, and the lift transfer components of the lift measurement devices are respectively connected to the connecting bases. A double-support system is adopted, and the airfoil model is supported between the supports. The system is of high support rigidity, and the airfoil model has little deformation under the action of gravity and wind load.

Description

technical field [0001] The invention relates to a measurement system, in particular to an airfoil model force measurement system. Background technique [0002] The aerodynamic characteristics of the airfoil are the key to the success of aircraft design, so it is of great engineering significance to improve the measurement accuracy of the airfoil aerodynamic characteristics measurement system in wind tunnel tests to match the actual needs of developing high-performance aircraft. [0003] Through a series of experimental studies on airfoil aerodynamic direct measurement, it is found that the three-stage layout can isolate the influence of the boundary layer on the side wall of the wind tunnel, and the lift-drag test results are more reasonable. However, there are still two problems: (1) the resistance is very small and the load is extremely mismatched, the signal of the resistance component is small, and the anti-interference ability is weak; (2) the stiffness of the cantileve...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/06
CPCG01M9/06
Inventor 杨中艳黄浩刘丹赵金海
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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