Small-deformation wind tunnel train balance

A technology of strain balance and small deformation, which is applied in the direction of measuring devices, instruments, aerodynamic tests, etc., can solve the problems of insufficient balance rigidity and bearing capacity, and insufficient utilization of balance design, so as to reduce the difficulty of design and benefit balance components Structure and layout optimization design, the effect of enlarging the balance diameter

Active Publication Date: 2016-05-25
INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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AI Technical Summary

Problems solved by technology

[0004] In order to solve the defects of insufficient rigidity and bearing capacity of the equal-diameter three-section rod balance and the lack of full use of the inner cavity space of the model in the design of the balance, the present invention provides a small deformation wind tunnel strain b

Method used

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  • Small-deformation wind tunnel train balance
  • Small-deformation wind tunnel train balance
  • Small-deformation wind tunnel train balance

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Embodiment Construction

[0025] figure 1 It is a schematic diagram of the assembly of a small deformation wind tunnel strain balance of the present invention. A strain balance in a small deformation wind tunnel according to the present invention mainly includes a rod-type balance and a support rod, and the rod-type balance and the support rod are tightened through a tapered surface and a wedge, and the cone is located inside the inner cavity of the model. The maximum diameter of the rod-type balance element is slightly smaller than the minimum diameter of the inner cavity at the tail of the model, which facilitates the installation and disassembly of the model while increasing the diameter of the rod-type balance element. The minimum diameter of the tapered part of the rod-type balance element is greater than the diameter of the straight section such as the support rod, and the value is calculated through the constraints of the balance and the taper at the front end of the support rod.

[0026] fig...

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Abstract

Provided is a small deformation wind tunnel train balance, comprising a rod-type balance and a support pole. Two ends of the rod-type balance have a conical structure. A balance element is arranged between the two ends of the rod-type balance. The balance element has a conical structure, which is provided thereon with a five-component element adjacent to the large-end part and a resistance element adjacent to the small-end part. The support pole comprises a conical front end and a straight segment. The rod-type balance and the conical front end of the support pole are matched via a conical surface and are tensioned via a wedge. The rod-type balance is arranged in an inner cavity of a tested model. The minimum diameter of the inner cavity of the tested model is greater than the maximum diameter of the rod-type balance. The invention breaks through the traditional equal-diameter balance support rod design method and the three-segment type rod-type balance structure, increases the diameter of the balance, shortens the balance length, realizes little deformation of the balance, improves the rigidity and the bearing ability of the balance, is applicable to balance development for wind tunnel experiments with large impact load or severe vibration, and achieves good practicability and popularization values.

Description

technical field [0001] The invention belongs to the technical field of aerodynamic force measurement for aerospace dynamometer tests, and is especially aimed at the problem of severe vibration of models and rod-type balance rod systems during the start-up and shutdown of temporary high-speed and ultra-high-speed wind tunnel dynamometer tests. The compact layout of the component structure and measuring components improves the overall rigidity of the balance and the support rod, enhances the anti-vibration capability of the model support system, and conducts safer and more accurate six-component aerodynamic measurement of the aircraft model. Background technique [0002] In the temporary high-speed wind tunnel dynamometer test, the impact load caused by airflow pulsation and shock wave sweeping during startup and shutdown may be several times or even ten times the scale range, and the dispersion is very large, making it difficult to measure and control. The vibration amplitude...

Claims

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Application Information

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IPC IPC(8): G01M9/06
CPCG01M9/062
Inventor 向光伟苗磊彭超米鹏王树民陈竹王超王俊兰
Owner INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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