Device and method for measuring dynamic load of helicopter main rotor

A measuring device and dynamic load technology, applied in the aviation field, can solve the problem of inability to directly measure the dynamic load value of the blade, and achieve the effect of simple structure, wide application range, and filling dynamic load changes.

Active Publication Date: 2021-12-07
中航电测仪器(西安)有限公司
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide a helicopter main rotor dynamic load measuring device and method to solve the problem in the prior art that the dynamic load value of the blades during helicopter flight cannot be directly measured

Method used

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  • Device and method for measuring dynamic load of helicopter main rotor
  • Device and method for measuring dynamic load of helicopter main rotor
  • Device and method for measuring dynamic load of helicopter main rotor

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Embodiment approach

[0030] Such as figure 1 , 2 Shown in and 3, a kind of helicopter main rotor dynamic load measuring device comprises dynamic load sensor and dynamic load signal processor; Described dynamic load sensor comprises the elastic body 1 that is installed in main rotor below, and sticks on the elastic body 1 A plurality of resistance strain gauges 8, the resistance strain gauges 8 are used to output corresponding electrical signals according to the micro-strain of the elastic body, and respond to the change of the dynamic load felt by the elastic body, and the resistance strain gauges 8 form a Wheatstone bridge; the main The dynamic load on the rotor blade is transmitted to the dynamic load sensor through the actuator, and the elastic body of the dynamic load sensor is pasted with a Wheatstone bridge composed of a resistance strain gauge, and outputs a corresponding millivolt level voltage according to the change of the dynamic load felt. signal to the dynamic load signal processor; ...

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Abstract

The invention discloses a helicopter main rotor dynamic load measuring device and method. The dynamic load measuring device includes a dynamic load sensor and a dynamic load signal processor; the dynamic load sensor includes an elastic body and a resistance strain gauge pasted on the elastic body. The resistance strain gauge forms a Wheatstone bridge and is connected to the dynamic load signal processor; the dynamic load signal processor performs filtering, shaping and pre-amplification after receiving the signal, and then one signal is filtered and amplified and sent to the observation end, and the other signal is passed through Filtering again, AC / DC conversion and amplification are respectively sent to the electromechanical management system and the flight parameter recording system. The device of the present invention has high safety and reliability, and the signal processing circuit is an analog circuit, which can respond immediately, realizes the real-time detection of the change of the dynamic load value borne by the blade during the flight of the helicopter, and timely feeds back to the flight parameter recording system and the electromechanical The management system provides reference for the pilot's operation and ensures flight safety.

Description

technical field [0001] The invention belongs to the field of aviation technology, and in particular relates to a device and method for measuring the dynamic load of a helicopter main rotor. Background technique [0002] The measurement of dynamic loads on the rotor during helicopter flight is crucial to flight safety. Since the helicopter has performance characteristics such as hovering, vertical flight, backward flight, and no need for a runway, it can be used in a wide range of aerial three-dimensional operations, and it is an ideal means for special tasks such as earthquake relief. However, the flight of a helicopter has strict restrictions on the environmental conditions. High temperatures will reduce the power of the engine and the pull of the rotor. Hovering flight and low-speed flight have strict requirements on the wind direction and speed. The safe flight of helicopters, and the environment of mission sites such as earthquake relief and disaster relief are often in...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D45/00
CPCB64D45/00
Inventor 李少龙孙敬先贺俊乔江华徐瑞利赵晓峰介鹏
Owner 中航电测仪器(西安)有限公司
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