A composite aircraft icing detector and method for measuring icing thickness

Abstract

The invention discloses a composite aircraft icing detector and an icing detection method, belonging to the technical field of aviation detection, comprising a dual-electrode complex impedance sensing mechanism, a multi-spectral optical fiber sensing mechanism and a composite probe outer frame; the dual-electrode complex The detection end face of the impedance sensing mechanism and the multispectral optical fiber sensing mechanism constitutes a sensitive surface and is located on the inclined end face; the dual-electrode complex impedance sensing mechanism collects the complex impedance frequency characteristic data in the environment to be tested; the multispectral optical fiber sensing mechanism collects the The spectral response data in the environment, combined with the complex impedance frequency characteristic data to identify the ice layer and water film on the sensitive surface, and at the same time monitor the dynamic process of water film freezing and ice melting in the ice-water mixed phase state, so as to achieve icing probing. The invention effectively avoids the failure of single-principle sensors in complex icing environments, greatly improves the reliability and accuracy of aircraft icing detectors, and has practical significance for ensuring efficient and reliable operation of aircraft anti-icing systems.

Description

technical field [0001] The invention belongs to the technical field of aviation detection, and more specifically relates to a composite aircraft icing detector and a method for measuring icing thickness. Background technique [0002] Aircraft icing mainly occurs on subsonic civil aircraft and military aircraft, and today, a large number of aviation accidents have been caused by aircraft icing. According to statistics, the icing-prone parts are the windshield, the leading edge of the wing and empennage, and the engine inlet. However, the existing aircraft icing sensors are mainly extended-type resonant cylinders, which are difficult to be installed flush and conformal on parts with small curvature radii such as leading edges and lips. At the same time, it is difficult for existing sensors to work reliably in the mixed phase of ice and water, and cannot cope with the freezing environment of supercooled large water droplets with severe overflow. [0003] Patent application CN...

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Problems solved by technology

[0005] In view of the above defects or improvement needs of the prior art, the present invention provides a composite aircraft icing detector and a method for measuring icing thickness, the purpose of which is to integrate a dual-electrode complex impedance sensor and a multi-spectral optical fiber in an integrated probe structure The sensor can identify the ice layer and water film on the sensitive surface by collecting the complex impedance frequency characteristic data and spectral response data of the sensitive surface respectively, so as to realize the high-reliability and precise icing detection function, thus solving the problem that the existing detectors cannot mix ice and water. Technical Problems of Detection and Identification in Phase State

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