Unmanned helicopter blade load flight actual measurement system and actual measurement method thereof

An unmanned helicopter and measurement system technology, which is applied to the unmanned helicopter blade load flight measurement system and its measurement field, can solve the instability of aircraft dynamics, metal blade waving, sway and torsion complex motion structure and aerodynamic coupling and other problems, to achieve the effect of light weight, small impact on blade dynamics, and reliable fixation

Pending Publication Date: 2018-04-20
NO 60 RES INST OF GENERAL STAFF DEPT PLA
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Problems solved by technology

[0005] Unmanned helicopters have a great influence on the dynamics of the entire helicopter due to their light weight and a small additional mass, which may even lead to the instability of aircraft dynamics; moreover, most of the rotor blades of unmanned helicopters are composite materials, not only have metal The complex motion o

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  • Unmanned helicopter blade load flight actual measurement system and actual measurement method thereof

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Embodiment 1

[0032] This embodiment provides an unmanned helicopter blade load flight measurement system, such as figure 1As shown, it includes blade strain acquisition system, unmanned helicopter flight state measurement system, data transmission and transmission system, ground receiving and data processing system. The blade strain acquisition system is installed on the unmanned helicopter rotor hub through a fixed tooling disc , rotate synchronously with the rotor, record and send the strain of the rotor blade; the blade strain acquisition system is composed of a dynamic strain acquisition device, a fixing mechanism and a battery, the dynamic strain acquisition device is installed on the battery through the fixing mechanism, and the dynamic strain acquisition device Consisting of 1 main control module, 3 bridge acquisition modules and stacked control software, the dynamic strain acquisition equipment mainly collects the strain data of rotor blades, and sends the strain data to the ground ...

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Abstract

The invention discloses an unmanned helicopter blade load flight actual measurement system which comprises a blade strain acquisition system, an unmanned helicopter flight state measurement system, adata sending and transmitting system, a ground receiving system and a data processing system. The blade strain acquisition system is mounted on an unmanned helicopter rotor hub through a fixture discand synchronously rotates along with a rotor to record and send rotor blade strain parameters. The unmanned helicopter flight state measurement system is mounted in a mission cabin of an unmanned helicopter to acquire, record and send measured flight state parameters of the unmanned helicopter. The ground receiving and data processing system receives the flight state parameters and the rotor bladestrain parameters sent by the data sending and transmitting system and analyzes and processes to obtain blade load and flight state parameters. The unmanned helicopter blade load flight actual measurement system is small in size, light in weight and high in precision.

Description

technical field [0001] The invention relates to a system for actually measuring the load of a helicopter moving part, in particular to a system for actually measuring the load of an unmanned helicopter blade and a measuring method thereof. Background technique [0002] Load is the key data for helicopter structure design and life determination. In the helicopter fatigue life assessment, the measured load reflects the fatigue load of the helicopter's moving parts in actual use, and is the main input data for fatigue damage calculation and life assessment. The development of the rotor blade load measurement technology is the premise of the fatigue test of the typical moving parts of the helicopter, and provides input and evaluation for comprehensively improving the anti-fatigue, anti-vibration, anti-overload, service life and other capabilities of the key moving parts such as the rotor hub of the unmanned helicopter condition. Therefore, accurate acquisition of the load on t...

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Application Information

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IPC IPC(8): B64F5/60B64C27/46
CPCB64C27/46B64F5/60Y02T90/00
Inventor 张逊姜年朝王克选宋军焦志文唐军军路林华王德鑫陶然邵松
Owner NO 60 RES INST OF GENERAL STAFF DEPT PLA
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