Static load and dynamic load separation method for flight test of rotating component

A technology of rotating parts and flight testing, which is applied in the direction of aircraft component testing, machine/structural component testing, and application of repeated force/pulsation force to test material strength, etc. It can solve problems such as inability to effectively reflect changes in static loads

Active Publication Date: 2020-03-27
CHINA HELICOPTER RES & DEV INST
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  • Application Information

AI Technical Summary

Problems solved by technology

The traditional flight test load processing does not use the helicopter blade azimuth angle signal to separate the dynamic and static loads, which cannot effectively reflect the change of static loads in the flight test state

Method used

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  • Static load and dynamic load separation method for flight test of rotating component
  • Static load and dynamic load separation method for flight test of rotating component
  • Static load and dynamic load separation method for flight test of rotating component

Examples

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Embodiment

[0048] A method for separating the static and dynamic loads of a rotating part flight test, based on the helicopter blade azimuth signal and flight test data, characterized in that the steps for determining the static and dynamic load separation method for the rotating parts flight test are as follows:

[0049] [1] Determining the standard blade azimuth angle signal: According to the standardized processing of the blade azimuth angle data recorded in the flight test, the process of obtaining the standard blade azimuth angle signal is indicated figure 2 ;

[0050] [2] Determine the fundamental frequency period of the standard blade azimuth angle signal and the number of data points of the rotating component load in a single cycle: for example, the time corresponding to the first standard blade azimuth angle signal with a value of 1 is 0.231s, and the second The time corresponding to the standard blade azimuth angle signal with a value of 1 is 0.74s, then the fundamental freque...

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Abstract

The invention belongs to the field of helicopter structure fatigue design, and particularly relates to a static load and dynamic load separation method for a rotating component flight test. The methodcomprises the following steps: synchronously acquiring a helicopter blade azimuth angle Pj and a rotating part load; standardizing the helicopter blade azimuth angle Pj to obtain a standard blade azimuth angle signal; calculating according to the standard blade azimuth angle signal to obtain a fundamental frequency period of the standard blade azimuth angle signal and a data point number of the rotating part load in a single period; determining a static load in the load of the rotating part in the ith fundamental frequency period; determining a dynamic load in the load of the rotating part inthe ith fundamental frequency period; and determining a rotating component flight test static load and a rotating component flight test dynamic load according to the flight test state of the helicopter. According to the method, helicopter flight test data can be separated based on helicopter blade azimuth signals, and static and dynamic loads of part flight test are obtained.

Description

technical field [0001] The invention belongs to the field of helicopter structural fatigue design, and in particular relates to a method for separating static loads and dynamic loads in flight tests of rotating components. Background technique [0002] Flight load test is an important basis for structural fatigue assessment of helicopters. Separating dynamic and static loads is an important part of flight load test data processing, which can provide effective measured loads for structural fatigue assessment. The traditional flight test load processing does not use the helicopter blade azimuth angle signal to separate the dynamic and static loads, which cannot effectively reflect the change of static loads in the flight test state. Contents of the invention [0003] Purpose of the present invention: provide a kind of rotating component flight test static load, dynamic load separation method, this method can be based on helicopter blade azimuth angle signal, separate helicop...

Claims

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Application Information

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IPC IPC(8): B64F5/60G01M99/00G01N3/32
CPCB64F5/60G01M99/007G01N3/32
Inventor 陈亚萍曾玖海喻溅鉴汪洋陶宪斌杨昌付裕曾本银
Owner CHINA HELICOPTER RES & DEV INST
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