An Online Aircraft Icing Detection Method Based on Statistical Test and Filtering

A detection method and statistical testing technology, applied in the field of online detection of aircraft icing, can solve problems such as less research on specific problems, and achieve the effects of strengthening online detection of aircraft icing, reducing interference, and avoiding input disturbance.

Active Publication Date: 2021-10-15
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

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  • An Online Aircraft Icing Detection Method Based on Statistical Test and Filtering
  • An Online Aircraft Icing Detection Method Based on Statistical Test and Filtering

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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 online detection method for aircraft icing based on statistical inspection and filtering. The online detection method for aircraft icing at least includes the following steps: S1: collecting flight state measurement data, engine thrust data and rudder deviation during flight Input data; S2: Use the generalized likelihood ratio test method to detect the beginning of icing; S3: Generate a disturbance signal and superimpose it on the rudder deviation input data, and use H ∞ The filtering method performs joint state estimation and icing-affected aerodynamic derivative identification on the flight state measurement data; S4: uses the generalized likelihood ratio test method to detect the end time of icing; S5: stops generating and superimposing the rudder deviation disturbance signal, and continues to use the H ∞ Filtering performs joint state estimation and identification of aerodynamic derivatives affected by icing on the measured data until the end of the flight. By combining the rapid detection of icing with the parameter estimation method, a more powerful aircraft icing detection algorithm 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 Patents(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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