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A Method for Detecting Icing Thickness

A detection method and electrothermal deicing technology, applied in deicing devices, transportation and packaging, aircraft parts, etc., can solve problems such as weak anti-environmental interference ability, difficult detection of thicker ice layers, and false alarms.

Active Publication Date: 2022-04-12
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For example, the fiber-optic icing sensor has high sensitivity, but it is sensitive to water, oil, and dust, and there are false alarms. The ability to resist environmental interference is not strong, and the maximum ice thickness detected is usually less than 2mm. ice detection

Method used

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  • A Method for Detecting Icing Thickness
  • A Method for Detecting Icing Thickness
  • A Method for Detecting Icing Thickness

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Embodiment Construction

[0047] The following description provides many different embodiments, or examples, for implementing various features of the invention. The elements and arrangements described in the following specific examples are only used to express the present invention in a concise manner, and are only used as examples rather than limiting the present invention.

[0048] The present invention adopts an icing detection device based on an electrothermal deicing unit, and several electrothermal deicing units are arranged on the skin surface of an aircraft. Outer insulation layer 12, wear layer 13, layer to be measured 14, processor, and first temperature sensor 17 and or second temperature sensor 16; please combine figure 1As shown, the base layer 10, the inner heat insulating layer 11, the heating layer 15, the outer insulating layer 12, the wear layer 13, and the layer to be measured 14 are arranged in sequence from bottom to top, wherein the first temperature sensor 17 is arranged on the h...

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Abstract

The present invention is applicable to the technical field of aircraft anti-icing, and provides a method for detecting the thickness of icing. Several electrothermal deicing units are arranged on the skin surface of the aircraft, and the electrothermal deicing units include a heating layer, a first temperature sensor or The second temperature sensor, the first temperature sensor is arranged above the heating layer, and the second temperature sensor is arranged on the interface between the adjacent electric deicing units, wherein the adjacent electric deicing units There are gaps between the heating layers of the ice unit. In the present invention, the icing situation of the layer to be measured can be reversely estimated only by whether there is a phase change step in the temperature-time curve of the first temperature sensor and the second temperature sensor test point; and under the premise of maintaining the same heating power , the heating mode of intermittent heating is more sensitive to icing detection than the continuous heating mode; this is especially suitable for the aircraft environment with high icing detection sensitivity.

Description

technical field [0001] The invention belongs to the field of anti-icing and deicing of aircraft, and relates to a method for detecting the thickness of icing. Background technique [0002] Electrothermal deicing is one of the most commonly used deicing methods for aircraft at present. Due to its advantages of clean energy and good maintainability, it represents the development trend of aircraft anti-icing. At present, the Boeing 787 large-scale passenger aircraft adopts the electric heating deicing system to replace the hot air anti-icing system, and realizes the full electricization of the deicing system. [0003] Aircraft electrothermal deicing is a multilayer electrothermal deicing structure with electric heating unit installed on the leading edge of the aircraft wing and empennage. The heating unit converts electrical energy into heat energy, and the heat is transferred to the icing surface through the multilayer structure, and the ice that adheres to the interface Melt...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D15/20B64D15/12
CPCB64D15/20B64D15/12
Inventor 肖春华马帅畅舒羽
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT