Dual rotor wind tunnel test platform

A wind tunnel test, dual rotor technology, applied in aerodynamic tests, machine/structural component testing, measuring devices, etc., to achieve the effects of low wind tunnel obstruction, small flow field interference, and low implementation cost

Active Publication Date: 2016-12-14
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

However, the new rotor aerodynamic problems such as high forward ratio, large regurgitation area, strong radial flow, and large hub resistance of this coaxial rigid dual-rotor helicopter have given the unsteady aerodynamic characteristics analysis and analysis of the coaxial rigid dual-rotor helicopter. Layout design presents serious challenges

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  • Dual rotor wind tunnel test platform
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  • Dual rotor wind tunnel test platform

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Embodiment Construction

[0021] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0022] like figure 1 , figure 2 The shown double-rotor wind tunnel test platform mainly includes a power resolver 2, a rotor mounting frame 12 and two rotor drive mechanisms. The two rotor drive mechanisms are installed on the rotor mounting frame 12, and are respectively located On the opposite sides of the gear 2, each auxiliary rotor drive mechanism includes an angular reducer 7, a rotor reducer 9 and a rotor transmission shaft 10. The rotor installation frame 12 is a rectangular frame, and its opposite sides are fixedly connected to the left shaft 24 and the right shaft 13 respectively, and...

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Abstract

The invention provides a dual rotor wind tunnel test platform. The dual rotor wind tunnel test platform comprises a power resolver (2), a rotor mounting frame (12) and two rotor driving mechanisms. The two rotor driving mechanisms are both installed on the rotor mounting frame (12) and are respectively arranged at two opposite sides of the power resolver (2), each rotor driving mechanism comprises an angle decelerator (7), a rotor decelerator (9) and a rotor transmission shaft (10), the power resolver (2) drives the angle decelerators (7) to synchronously move through two first transmission shafts (6), the angle decelerators (7) drive the rotor decelerators (9) to synchronously move through second transmission shafts (8), and the rotor decelerators (9) drive the rotor transmission shafts(10) to synchronously move relative to the rotor mounting frame (12). The dual rotor wind tunnel test platform is applied to dual rotor wind tunnel tests, synchronous motions of the dual rotors are achieved, a relatively-low wind tunnel obstruction degree can be maintained, interference on the flow field is low, and the reliability of the wind tunnel test result is improved.

Description

technical field [0001] The invention relates to the technical field of double-rotor wind tunnel tests, in particular to a double-rotor wind tunnel test platform capable of realizing double-rotor synchronous reverse rotation. Background technique [0002] Due to the lack of aerodynamic force, the current conventional configuration helicopter makes it difficult to improve its speed. The development of a coaxial rigid dual-rotor helicopter by introducing special components such as a coaxial rigid rotor system and a tail propulsion device can solve the problem that the speed of a conventional configuration helicopter is difficult to break through from the aerodynamic aspect. [0003] For the coaxial rigid dual-rotor helicopter, the coaxial dual-rotors are usually synchronously rotating in opposite directions at the same speed. However, the new rotor aerodynamic problems such as high forward ratio, large regurgitation area, strong radial flow, and large hub resistance of this co...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/02G01M9/04
CPCG01M9/02G01M9/04
Inventor 黄明其杨永东梁鉴王畅何龙
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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