Anti-icing and deicing method for civil aircraft adopting loop heat pipes

A loop heat pipe and anti-icing technology, which is applied in the direction of deicing devices, aircraft parts, indirect heat exchangers, etc., can solve the problems of reducing aircraft flight performance, low heat utilization rate, and reduced available engine thrust, so as to increase heat Utilization rate, effect of improving flight performance

Inactive Publication Date: 2009-12-02
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the used hot air of this anti-icing and deicing method is discharged into the atmosphere, causing a large amount of waste of heat, and the heat utilization rat...

Method used

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  • Anti-icing and deicing method for civil aircraft adopting loop heat pipes
  • Anti-icing and deicing method for civil aircraft adopting loop heat pipes
  • Anti-icing and deicing method for civil aircraft adopting loop heat pipes

Examples

Experimental program
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Embodiment

[0054] Embodiment: When the anti-icing and de-icing component of civil aircraft is the leading edge of the engine inlet:

[0055] The present invention specifically comprises the following steps:

[0056] Step 1: Determine the icing protection range and the required thermal load Q of the leading edge of the civil aircraft engine intake under the most severe icing conditions;

[0057] Step 2: Install the heat exchange device to determine the heat source for anti-icing and deicing;

[0058] The heat source for anti-icing at the leading edge of the engine intake is the high-temperature engine bleed air sent to the air-conditioning system, so the heat exchange device should be installed before the bleed air reaches the air-conditioning system. It can be considered to install the heat exchange device in the engine nacelle, or it can be It is installed in the fuselage. The specific installation location is mainly affected by the development and manufacturing level of the loop heat...

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PUM

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Abstract

The invention discloses an anti-icing and deicing method for a civil aircraft adopting loop heat pipes, which comprises the following steps: 1, determining an icing protection range for parts of the civil aircraft needing anti-icing and deicing, and calculating the maximum anti-icing and deicing heat load Q required by the anti-icing and deicing parts; 2, arranging a heat exchange device to determine a heat source for anti-icing and deicing; 3, selecting loop heat pipes to determine the number of the loop heat pipes; and 4, arranging condensers and evaporators of the loop heat pipes on the civil aircraft. The method improves the heat utilization rate of the civil aircraft, reduces the bleed air from a compressor of an engine, improves the available thrust of the engine, reduces the weight of some structural parts used for anti-icing, deicing and bleed air cooling of the civil aircraft, and improves the flight performance of the civil aircraft and the economical efficiency focused by the civil aircraft.

Description

technical field [0001] The invention belongs to the technical field of anti-icing and deicing of civil aircraft, and in particular relates to a method for anti-icing and deicing of civil aircraft using a loop heat pipe. Background technique [0002] When an aircraft flies under icy weather conditions, icing is prone to occur, and icing has always been one of the main causes of aircraft crashes. Common aircraft parts that require anti-icing and de-icing technologies mainly include windshields, pitot tubes, propellers, helicopter rotors, wings, empennages, leading edges of engine inlets and air intake components. [0003] Generally speaking, for parts such as wings with large surface area to be protected and high anti-icing requirements, and the leading edge of the engine intake, gas thermal anti-icing technology is often used; for empennage with small surface area to be protected and low anti-icing requirements For components such as propellers and propellers, the electric h...

Claims

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Application Information

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IPC IPC(8): B64D15/04F28D15/02
CPCF28D15/0266F28D15/043B64D15/02F28D2021/0021
Inventor 刘猛杨鹏王浚崔坤叶明伟
Owner BEIHANG UNIV
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