Device for calibrating dynamic balance parameter of helicopter rotor blade

A technology for helicopter rotor and parameter calibration, which is applied in static/dynamic balance testing, measuring device, machine/structural component testing, etc., and can solve problems such as poor reliability and measurement result error.

Inactive Publication Date: 2013-02-27
HARBIN INST OF TECH
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  • Abstract
  • Description
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AI Technical Summary

Problems solved by technology

[0007] In order to solve the problem that the calibration of the helicopter rotor blade dynamic balance test in the background technology has large errors of measurement results and poor reliability, the present invention aims at the calibration problem of the light helicopter rotor blade dynamic balance test and the problems existing in the above-mentioned existing calibration technology. Insufficient, a helicopter rotor blade dynamic balance parameter calibration device is provided

Method used

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  • Device for calibrating dynamic balance parameter of helicopter rotor blade
  • Device for calibrating dynamic balance parameter of helicopter rotor blade
  • Device for calibrating dynamic balance parameter of helicopter rotor blade

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specific Embodiment approach 1

[0015] Specific implementation mode one: as Figure 1~6 As shown, the helicopter rotor blade dynamic balance parameter calibration device described in this embodiment includes two parts: the rotor blade measurement subsystem and the simulation blade calibration subsystem;

[0016] The rotor blade measurement subsystem 1 includes a helicopter rotor dynamic balance test bench 1-1, three lasers 1-2 and a signal conditioning circuit 1-3, a high-speed CPLD logic array device 1-4, and a high-speed DSP embedded data processor 1-5 and PC104 micro-control computer 1-6; the helicopter rotor dynamic balance test bench 1-1 is used to drive the three blades (reference blades) on the rotor to rotate, so that the three blades on the rotor are in the rotating state It can sequentially cut the laser optical path emitted by three lasers 1-2, and the rotor will generate 9 laser timing pulse signals every time it rotates. After the signal conditioning circuit 1-3 (photoelectric isolator) is used ...

specific Embodiment approach 2

[0021] Specific implementation mode two: as Figure 1~6 As shown, the high-speed CPLD logic array device 1-4 described in this embodiment is designed with three 32-bit counters to measure the time interval of the sequential pulse signal, the time measurement accuracy is 0.05 μs, and the maximum counting time is 214.75s. The timing algorithm of rotor blade flapping parameters, according to Figure 9 , Figure 10 It can be concluded that:

[0022] h 1 =H*t 12 / (t 11 +t 12 )

[0023] h 2 =H*t 22 / (t 21 +t 22 )

[0024] h 3 =H*t 32 / (t 31 +t 32 )

[0025] h 1 -h 2 =H*[t 12 / (t 11 +t 12 )-t 22 / (t 21 +t 22 )]

[0026] h 1 -h 3 =H*[t 12 / (t 11 +t 12 )-t 32 / (t 31 +t 32 )]

[0027] where h 1 -h 2 and h 1 -h 3 are the height difference between the first blade and the second and third blades, respectively.

[0028] For the rotor blade shimmy angle parameter, the average time T taken by a certain blade to rotate through 120° 120 ,but:

[0029] T ...

specific Embodiment approach 3

[0036] Specific implementation mode three: as Figure 1~6 As shown, the simulated blade 2-2 in the simulated blade calibration subsystem 2 in this embodiment adopts a detachable structure. Other compositions and connections are the same as those in Embodiment 1 or 2.

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Abstract

The invention discloses a device for calibrating a dynamic balance parameter of a helicopter rotor blade and relates to a test and calibration technology of a helicopter rotor blade, and the device is used for solving the problems such as big error in measurement result and poor reliability in the dynamic balance test calibration of the helicopter rotor blade in the prior background art. A laser measurement platform is formed by a three-beam laser device of a dynamic balance test table; the flapping parameter of the rotor blade is measured in a non-contact way through a method of cutting laser beams by the blade; a pulse time sequence measuring and controlling system is designed by taking a CPLD (Complex Programmable Logic Device) and a DSP (Digital Signal Processor) as cores; and the flapping and shimmy characteristic parameters of the rotor blade are measured. A simulated blade with fixed height difference is adopted in a calibration device and rotated at a stable rotation speed through a servo motor, the dynamic balance test platform of the rotor blade is calibrated on site through a method of cutting the laser beams by the simulated blade, the calibration result is traced to national length standard, the accuracy and traceability of the measurement result are ensured, and a quality guarantee is provided for the development and test of the helicopter rotor blade.

Description

technical field [0001] The invention relates to a helicopter rotor blade dynamic balance parameter calibration device, and relates to the testing and calibration technology of the helicopter rotor blade. Background technique [0002] The blade flapping parameter is the ultimate embodiment of the comprehensive effect of helicopter blade aerodynamics and flight control, and is the main parameter to finally verify the design parameters, manufacturing process, aerodynamic theory, and flight control method of the helicopter rotor blade. Since the dynamic balance test of the helicopter rotor blades is carried out under the high-speed rotation of the rotor, there have always been problems of difficult measurement and poor measurement accuracy. The measurement technology of blade flapping parameters has always been concerned at home and abroad. my country's dynamic balance test technology for helicopter blades originated from France, and the rotor blade dynamic balance test bench im...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M1/16
Inventor 梁廷伟于金涛宋凯梁韵丁明理邵崇辉
Owner HARBIN INST OF TECH
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