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Aircraft model driving system in wind tunnel and performance measurement method

A model-driven, aircraft technology, applied in the direction of measuring devices, machine/structural component testing, instruments, etc., to achieve the effect of verifying accuracy

Active Publication Date: 2020-11-13
RIZHAO KUNLUN INTELLIGENT TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

That is to say, the test equipment must have all-round, large-scale and high-speed performance, which is rarely provided by the existing technology

Method used

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  • Aircraft model driving system in wind tunnel and performance measurement method
  • Aircraft model driving system in wind tunnel and performance measurement method
  • Aircraft model driving system in wind tunnel and performance measurement method

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Embodiment Construction

[0059] In order to make the technical problems, technical solutions and advantages to be solved by the present invention clearer, the following will describe in detail with reference to the drawings and specific embodiments.

[0060] The invention provides a driving system for an aircraft model in a wind tunnel, such as Figure 1-2 As shown, it includes a pole device 103, a six-bar parallel mechanism 106 and a linear guide 112, wherein:

[0061] The pole device 103 is positioned at the rear of the aircraft model 101, and is used to support the aircraft model 101 through the multi-component balance 102 inside the model;

[0062] The rod device 103 includes a hollow tail rod body 1031 and a rotatable rear tail rod 1032 protruding from one end of the tail rod body 1031 (the rear tail rod 1032 can be specifically supported in the tail rod body 1031 through the front and rear bearings 206) , the front end of the rear tail strut 1032 supports the aircraft model 101 through the mult...

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Abstract

The invention discloses an aircraft model driving system in a wind tunnel and a performance measurement method, and belongs to the technical field of wind tunnel aerodynamics and flight dynamics experiments and comprises a supporting rod device, a six-rod parallel mechanism and a linear guide rail, the supporting rod device is located on the rear part of an aircraft model, and the aircraft model is supported by a multi-component balance in the model; a rolling driving and measuring device is mounted in the supporting rod device; the six-rod parallel mechanism comprises six connecting rods, universal hinges are arranged at the two ends of each connecting rod, and the universal hinge at the front end is connected with the supporting rod device; the universal hinge at the rear end is connected with a sliding block of the linear guide rail; the linear guide rail is installed on the inner wall of the wind tunnel experiment section. Omnibearing, large-range and high-speed movement can be provided in the wind tunnel at the same time, enough rigidity and strength and low interference are achieved, and the method can be used for measuring aerodynamic force and virtual flight performance ofan aircraft with high maneuverability and agility in the high-speed wind tunnel.

Description

technical field [0001] The invention relates to the technical field of wind tunnel aerodynamics and wind tunnel flight dynamics (wind tunnel virtual flight) experiments, in particular to an aircraft model drive system in a wind tunnel and performance measurement of wind tunnel aerodynamics and wind tunnel virtual flight mechanics method. Background technique [0002] High maneuverability, high agility and post-stall maneuvering are important indicators of modern high-performance military aircraft and tactical missiles. In order to achieve this requirement, the aircraft should have excellent large-angle variation range, angular velocity variation range and instantaneous angular acceleration, as well as stability and control capabilities after stall flight. In these complex maneuvering flights, the aircraft's longitudinal and lateral three-dimensional flow disturbances, serious nonlinear and unsteady characteristics make the aircraft's aerodynamics and flight dynamics perform...

Claims

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Application Information

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IPC IPC(8): G01M9/04G01M9/06G01M9/08
CPCG01M9/04G01M9/06G01M9/08
Inventor 黄兴中楼海烨顾思践陈李明孙浩陈庆江
Owner RIZHAO KUNLUN INTELLIGENT TECH CO LTD
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