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Airplane icing on-line detection method based on statistical test and filtering

A detection method and statistical inspection technology, which is applied in the field of online detection of aircraft icing, can solve the problems of less research on specific problems, achieve the effect of strong online detection ability of aircraft icing, avoid input disturbance, and reduce interference

Active Publication Date: 2020-12-08
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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AI Technical Summary

Problems solved by technology

[0004] Aircraft icing algorithm detection usually focuses on the research on the detection algorithm, and there is less research on some specific issues applied to the flight process

Method used

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Embodiment 1

[0034] refer to figure 1As shown, the present invention discloses an aircraft icing online detection method based on statistical inspection and filtering, characterized in that the aircraft icing online detection method at least includes the following steps:

[0035] Step S1: Collect flight state measurement data, engine thrust data and rudder deviation input data during flight.

[0036] Preferably, in the step S1, the flight state measurement data includes at least the position, speed, overload, angular velocity, attitude angle and dynamic pressure data of the aircraft.

[0037] Step S2: Use the generalized likelihood ratio test method to detect the start time of icing.

[0038] Preferably, the step S2 includes: sequentially extracting data segments from the flight state measurement data to calculate the overload margin, and using the generalized likelihood ratio test method to judge whether the statistical characteristics of each segment of the overload margin exceed a give...

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Abstract

The invention discloses an airplane icing on-line detection method based on statistical test and filtering. The airplane icing on-line detection method at least comprises the following steps that S1,flight state measurement data, engine thrust data and rudder deviation input data in the flight process are collected; S2, an icing starting moment is detected by utilizing a generalized likelihood ratio test method; S3, a disturbance signal is generated to be superposed on the rudder deviation input data, and joint state estimation and aerodynamic derivative identification influenced by icing areconducted on the flight state measurement data by utilizing an H-infinity filtering method; S4, an icing end moment is detected by utilizing the generalized likelihood ratio test method; and S5, generating and superposing of the rudder deflection disturbance signal are stopped, and joint state estimation and aerodynamic derivative identification influenced by icing continue to be conducted on themeasurement data by utilizing H-infinity filtering until the flight is finished. By combining quick icing detection and a parameter estimation method, an airplane icing detection algorithm with stronger functions is obtained.

Description

technical field [0001] The invention belongs to the technical field of online detection of aircraft icing, and in particular relates to an online detection method of aircraft icing based on statistical inspection and filtering. Background technique [0002] Aircraft icing online detection refers to the detection of icing phenomena that occur during aircraft flight through detection devices or methods, and gives an icing alarm to activate the aircraft anti-icing device, so as to avoid the harm caused by icing during flight to aircraft safety. [0003] On-line detection of icing usually has two classifications: hardware detection and algorithm detection. Hardware detection is to detect the icing position and ice type parameters through hardware devices such as sensors arranged on the surface of the body. Algorithm detection refers to the use of mathematical methods and physical models. The flight measurement data are used to estimate the aerodynamic parameters of the aircraft ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D15/20
CPCB64D15/20
Inventor 丁娣何开锋汪清钱炜祺
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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