Apparatus for measuring three-degree-of-freedom dynamic stability parameters of aircraft in high-speed wind tunnel

A high-speed wind tunnel and aircraft technology, applied in the direction of measuring devices, instruments, aerodynamic tests, etc., can solve problems such as the influence of measurement results, model motion waveform errors, etc., and achieve the effect of high sensitivity and large internal installation space

Active Publication Date: 2017-02-22
RIZHAO KUNLUN INTELLIGENT TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This kind of mechanism can only use the form of abdominal support to support the model and drive the model for pitching vibration, and it is only used in low-speed wind tunn...

Method used

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  • Apparatus for measuring three-degree-of-freedom dynamic stability parameters of aircraft in high-speed wind tunnel
  • Apparatus for measuring three-degree-of-freedom dynamic stability parameters of aircraft in high-speed wind tunnel
  • Apparatus for measuring three-degree-of-freedom dynamic stability parameters of aircraft in high-speed wind tunnel

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Experimental program
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Embodiment Construction

[0027] The present invention will be described in detail below in conjunction with the accompanying drawings.

[0028] Such as Figure 1 to Figure 7 As shown, the aircraft model 110 is installed at the front end of the barrel balance, and the pitch-excited piezoelectric ceramic exciter group 102 installed in the tail support rod 101 is assembled by the frame 103, and the first connecting rod is pushed by the in-line hinge 104 108 pitches and vibrates around the axis of the first cross hinge 105. The front end of the first connecting rod is connected to the vibrating cylinder 114 through the front in-line hinge 106 and pushes the vibrating cylinder 114 to pitch and vibrate along the axis of the second cross-shaped hinge 107 that the vibrating cylinder is connected to the tail strut. In this way, when the piezoelectric ceramic exciter vibrates linearly up and down, the first connecting rod can perform pitching vibration around the rotation center of the middle part of the first...

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PUM

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Abstract

The invention provides an apparatus for measuring three-degree-of-freedom dynamic stability parameters of an aircraft in a high-speed wind tunnel. A pitching exciting piezoelectric ceramic vibration exciter is arranged in a support sting, one end of the vibration exciter is connected with the support sting, the other end is connected with a frame in parallel and is then connected with the rear end of a first connecting rod in a hinged manner, the central part of the first connecting rod is supported on the support sting through an elastic hinge, the front end of the first connecting rod is connected with a vibration cylinder in a hinged manner, an inner cavity of the vibration cylinder is provided with a T-shaped support rod, two ends of a vertical shaft of the T-shaped support rod are connected with the vibration cylinder in a hinged manner, two ends of a horizontal shaft of the T-shaped support rod is connected with a cylindrical balance in a hinged manner, a first yawing/rolling piezoelectric ceramic vibration exciter and a second yawing/rolling piezoelectric ceramic vibration exciter are arranged in the cylindrical balance, one ends of the first yawing/rolling piezoelectric ceramic vibration exciter and the second yawing/rolling piezoelectric ceramic vibration exciter are fixed to the vibration cylinder, and the other ends are connected with a corresponding second connecting rod in a hinged manner. The apparatus is arranged in the wind tunnel, and can accurately measure the three-degree-of-freedom dynamic stability parameters of the aircraft in the high-speed wind tunnel.

Description

technical field [0001] The invention relates to the technical field of measurement of aircraft three-degree-of-freedom dynamic stability parameters, in particular to a device for measuring aircraft three-degree-of-freedom dynamic stability parameters in a high-speed wind tunnel. Background technique [0002] The dynamic and static stability parameters or the dynamic and static stability derivatives of the aircraft are important parameters to measure the maneuverability and stability of the aircraft. The characteristic parameter of the change of the aerodynamic force or moment (coefficient). [0003] In order to improve its combat performance, modern military fighters are often required to be able to perform various difficult maneuvers. The aircraft must not only have sufficient stability, but also have precise maneuverability or guidance. The better the maneuverability of the aircraft and the higher the maneuverability value, the stronger the combat effectiveness and survi...

Claims

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Application Information

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IPC IPC(8): G01M9/00
Inventor 朱兴荣黄兴中朱珈成
Owner RIZHAO KUNLUN INTELLIGENT TECH CO LTD
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