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Helicopter tail rotor simulation test device and vortex ring verification method

A technology for helicopter tail rotor and simulation testing, which is used in measurement devices, aircraft component testing, and machine/structural component testing. Verify the effect of the test

Pending Publication Date: 2020-04-24
中国人民解放军陆军航空兵学院陆军航空兵研究所
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, if the experiment is carried out directly on the tail rotor of the helicopter, there are problems such as high cost, high risk, uncontrollable experimental flow field environment, and inconvenient data collection.

Method used

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  • Helicopter tail rotor simulation test device and vortex ring verification method
  • Helicopter tail rotor simulation test device and vortex ring verification method
  • Helicopter tail rotor simulation test device and vortex ring verification method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0036] see figure 1 , which is a schematic structural diagram of the helicopter tail rotor simulation test device shown in Embodiment 1 of the present application.

[0037] Such as figure 1 As shown, the helicopter tail rotor simulation test device provided in this embodiment includes a base 100, a bracket 300, a power unit 400, a transmission unit 500, a tail rotor unit 600, a manipulation unit 700 and a data acquisition unit 200, wherein the data acquisition unit 200 is installed On the base 100, the support 300 is installed on the data acquisition unit 200; the power unit 400, the transmission unit 500, and the manipulation unit 700 are installed on the support 300; the transmission unit 500 includes a gear pair and a main shaft 503, the driving wheel 501 of the gear pair and The power part 400 is connected, and the power part 400 drives the driving gear to rotate; the driven wheel 502 of the gear pair is connected to the first end of the main shaft 503, and the driven whe...

Embodiment 2

[0097] see Figure 8 , which is a flowchart of a method for verifying a vortex ring by the helicopter tail rotor simulation test device shown in Embodiment 2 of the present application.

[0098] Such as Figure 8 As shown, the method for verifying the vortex ring by the helicopter tail rotor simulation test device provided in this embodiment includes:

[0099] Step S201, start the power component, and the power component drives the transmission component to rotate, so that the power component drives the tail rotor component to rotate.

[0100] In this embodiment, the power component is used to provide power for the rotation of the tail rotor component, and the transmission component is used to transmit the power provided by the power component to the tail rotor component to drive the tail rotor component to rotate, so as to simulate the operating state of the helicopter tail rotor .

[0101] Step S202, adjusting the driving power of the power component, and manipulating the...

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PUM

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Abstract

The invention discloses a helicopter tail rotor simulation test device and a vortex ring verification method. The helicopter tail rotor simulation test device comprises a base, a support, a power part, a transmission part, a tail rotor part, a control part and a data acquisition part, wherein the data acquisition part is installed on the base, and the support is installed on the data acquisition part; and the power part, the transmission part and the control part are installed on the support. The transmission part comprises a gear pair and a main shaft, wherein a driving wheel of the gear pairis connected with the power part, and the power part drives the driving gear to rotate; a driven wheel of the gear pair is connected with the first end of the main shaft and drives the main shaft torotate; the second end of the main shaft is connected with the tail rotor part; the main shaft drives the tail rotor part to rotate; the tail rotor part is connected with the control part; and the control part drives the tail rotor part to adjust the total pitch of the tail rotor. Therefore, the operation state of the helicopter tail rotor is simulated, and the vortex ring state of the helicoptertail rotor is simply, conveniently and controllably verified and tested.

Description

technical field [0001] The embodiment of the present application relates to the technical field of helicopter power testing, and in particular to a helicopter tail rotor simulation test device and a method for verifying a vortex ring. Background technique [0002] If the helicopter tail rotor fails when the helicopter is hovering or flying forward, the helicopter heading control will be out of control, resulting in serious flight accidents. The tail rotor vortex ring state is an important aerodynamic factor causing tail rotor failure. The cause of the vortex ring state of the tail rotor is roughly that the tail rotor encounters the relative airflow in the same direction as the tail rotor’s pulling force. After the relative airflow meets the airflow on the opposite side of the pulling force direction, a part of the air flows around the edge of the tail rotor in the direction of the pulling force. The air pressure on the side of the pulling force direction is low, and this pa...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/00G01M9/06B64F5/60
CPCG01M9/00G01M9/06B64F5/60
Inventor 徐冠峰侯波陈浩叶永林徐松华李京峰宋宴
Owner 中国人民解放军陆军航空兵学院陆军航空兵研究所