Civil aircraft test flight vibration fault prediction model and prediction system

A technology for fault prediction and civil aircraft, applied in computer parts, character and pattern recognition, pattern recognition in signals, etc., can solve problems such as long analysis period, single analysis method, and huge vibration data

Inactive Publication Date: 2019-11-05
COMAC +1
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  • Summary
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  • Claims
  • Application Information

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Problems solved by technology

[0008] (1) The analysis method is relatively simple: the vibration phenomenon analysis method adopted is only the correlation analysis between parameters, so it is difficult to locate the vibration source;
[0009] (2) The analysis method is relatively lagging: only when vibration faults or vibration phenomena occur (such as structural damage to the body), sensors will be installed for

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  • Civil aircraft test flight vibration fault prediction model and prediction system
  • Civil aircraft test flight vibration fault prediction model and prediction system
  • Civil aircraft test flight vibration fault prediction model and prediction system

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Embodiment 1

[0048] This embodiment takes horizontal tail vibration as an example to illustrate the establishment method of the civil aircraft flight test vibration fault prediction model, and the principles of other vibrations such as landing gear and wings are the same.

[0049] The establishment method of the civil aircraft test flight vibration fault prediction model is as follows:

[0050] Step 1: Create a database

[0051] Through the analysis and summary of nearly 10TB of massive historical vibration data, the vibration parameters with evaluation value for the horizontal tail vibration phenomenon are shown in Table 1:

[0052] Table 1 Acceleration sensor parameters used for horizontal tail vibration analysis

[0053]

[0054]

[0055] Under normal conditions, the time domain trend of the vibration acceleration sensor is as follows: figure 1 , 2 As shown, when the horizontal tail vibrates or even the body is damaged, the time domain trend of the vibration acceleration sensor...

Embodiment 2

[0088] This embodiment provides a civil aircraft flight test vibration fault prediction system. The civil aircraft flight test vibration fault prediction system is a high concurrent real-time processing system built based on the Golang platform. The civil aircraft flight test vibration fault prediction model trained in Embodiment 1 is implemented. Transplanting, real-time processing of vibration parameters with a frequency up to 8192 in the airborne real-time environment, identification and classification of symptoms, and early warning of potential vibration failures.

[0089] Civil aircraft flight test vibration fault prediction system is divided into three modules: flight test parameter real-time analysis module, civil aircraft flight test vibration fault prediction model and result distribution module.

[0090] The core of the real-time analysis module of flight test parameters is Golang's high concurrency model, which is implemented through goroutines. Goroutines are simila...

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Abstract

The invention discloses a civil aircraft test flight vibration fault prediction model which is established through the following steps: 1, establishing a database which is composed of a characteristicparameter set and states corresponding to characteristics; wherein the characteristic parameter set comprises time domain characteristics extracted from the vibration parameters of each part of the civil aircraft, frequency domain characteristics extracted from the vibration parameters of each part of the civil aircraft, and flight parameters of which the correlation with the vibration parametersis greater than 0.6; wherein the time domain characteristics comprise the maximum value, the minimum value, the peak-to-peak value and the amplitude change rate of the vibration amplitude; wherein the frequency domain characteristics comprise frequency composition, frequency size and a change trend of the frequency along with time; and 2, establishing a civil aircraft test flight vibration faultprediction model by using the binary support vector machine model to obtain the binary support vector machine model so as to determine the early warning boundary of the test flight data, and taking the early warning boundary as the basis for judging the normal and abnormal single states of the data. The invention also discloses a civil aircraft test flight vibration fault prediction system.

Description

technical field [0001] The invention relates to a model and system for identifying aircraft vibration faults. The main function is to use collected high-frequency vibration data as input during the real-time monitoring of flight tests to complete the identification and alarm of vibration fault risks. Background technique [0002] Aircraft, especially large civil aircraft, will vibrate due to factors such as airflow, engine, flight attitude, and dynamic mass changes during flight or test flight, and its landing gear, wings, and horizontal tail will vibrate, which will cause damage to the airframe in severe cases and affect Airplane flight safety. At present, the vibration failures in civil aircraft test flights are analyzed after the event, that is, only known vibration damage phenomena can be improved or optimized. For vibration, the traditional analysis process is as follows: [0003] (1) Time-domain analysis: draw the trend curve of the collected vibration parameters for...

Claims

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Application Information

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IPC IPC(8): G06F17/50G06K9/00G06K9/62
CPCG06F2218/10G06F18/2411Y02T90/00
Inventor 毛为冯灿刘涛查晓文陈家益梁嘉羿汪峰虞一帆
Owner COMAC
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