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Tail slurry variable pitch fatigue test device

A fatigue test and tail rotor technology, which is applied in the field of helicopters, can solve the problems of lack of fatigue test equipment for the tail rotor pitch variable ring and difficulty in determining the fatigue performance.

Active Publication Date: 2020-12-29
CHINA HELICOPTER RES & DEV INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In the prior art, there are mainly the problems of lack of fatigue test equipment for the tail rotor variable pitch ring of unmanned helicopters and difficulty in determining the fatigue performance

Method used

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  • Tail slurry variable pitch fatigue test device
  • Tail slurry variable pitch fatigue test device
  • Tail slurry variable pitch fatigue test device

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Embodiment Construction

[0022] The application will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the related application, not to limit the application. In addition, it should be noted that, for ease of description, only parts relevant to the present application are shown in the drawings.

[0023] It should be noted that, in the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and embodiments.

[0024] It should be noted that, in the description of the present application, terms such as "center", "upper", "lower", "left", "right", "front", "rear" and other indicated directions or positional relationships are Based on the orientation or positional relationship shown in th...

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Abstract

The invention provides a tail rotor variable pitch fatigue testing device. The tail rotor variable pitch fatigue testing device comprises a single lug module, a support seat and a base, wherein the single lug module comprises a support arm and a lug piece which are connected with each other, and the lug piece is provided with a connecting hole for connecting a test piece; the support seat comprises an upper boss and a lower boss which are integrally formed, the upper boss is used for fixing the test piece, and the lower boss is connected with the base; the included angle between the side wherethe base and the support seat are connected and the opposite other side is a preset angle.

Description

technical field [0001] The application relates to the technical field of helicopters, and specifically provides a tail rotor variable pitch fatigue test device. Background technique [0002] The tail rotor is an important part of the helicopter structure. It mainly balances the torque generated by the helicopter rotor. At the same time, by generating variable torque, the helicopter's body posture is guaranteed to ensure the stability of the helicopter during flight. The tail rotor operating system is transmitted through the tail rotor pitch ring. The force is applied to the tail rotor to control the aircraft's body posture and flight stability, and the fatigue performance of the tail rotor pitch change ring has an important impact on the flight state of the helicopter. [0003] In the prior art, there are mainly the problems of lack of fatigue test equipment for the tail rotor pitch variable ring of unmanned helicopters and difficulty in determining the fatigue performance. ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M13/00B64F5/60
CPCG01M13/00
Inventor 宋云孙云伟夏国旺高国良
Owner CHINA HELICOPTER RES & DEV INST