Composite aircraft icing detector and icing thickness measuring method

Abstract

The invention discloses a composite aircraft icing detector and an icing detection method, and belongs to the technical field of aviation detection. The composite aircraft icing detector comprises a double-electrode complex impedance sensing mechanism, a multispectral optical fiber sensing mechanism and a composite probe outer frame, wherein the double-electrode complex impedance sensing mechanism and the detection end surface of the multispectral optical fiber sensing mechanism form a sensitive surface and are positioned on the inclined end surface; the double-electrode complex impedance sensing mechanism collects complex impedance frequency characteristic data in a to-be-detected environment; the multispectral optical fiber sensing mechanism collects spectral response data in the to-be-detected environment, recognizes an ice layer and a water film on a sensitive surface in combination with complex impedance frequency characteristic data, and meanwhile, monitors the dynamic process of water film freezing and ice layer melting in an ice-water mixed phase state, so that icing detection is achieved. The problem that a single principle type sensor fails in a complex icing environment is effectively avoided, the reliability and accuracy of the aircraft icing detector are greatly improved, and the aircraft icing detector has practical significance in guaranteeing efficient and reliable operation of an aircraft anti-icing and deicing system.

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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