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Wing ice preventing and removing device based on nano composite phase change material and working method thereof

A nano-composite, phase-change material technology, applied in de-icing devices, aircraft parts, transportation and packaging, etc., can solve the problems of low thermal conductivity and limited heat transfer efficiency, so as to improve heat conduction, reduce energy consumption, and prevent icing Effect

Pending Publication Date: 2020-04-07
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, most phase change materials have low thermal conductivity, which limits their heat transfer efficiency in the ground and space phase change process.

Method used

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  • Wing ice preventing and removing device based on nano composite phase change material and working method thereof

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Embodiment Construction

[0027] Below in conjunction with accompanying drawing, technical scheme of the present invention is described in further detail:

[0028] This invention may be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. In the drawings, components are exaggerated for clarity.

[0029] Such as figure 1 As shown, the present invention discloses a wing anti-icing device based on nanocomposite phase change materials, including a compressor 1, a shut-off valve 2, a filter 3, a dryer 4, a wing inner flow channel 7, and an electric heating deicing assembly 9. The first temperature sensor 10, the freezing detector 11, the metal fin 12, the second temperature sensor 13, the water separator 14, the flow valve 15 and the controller 16;

[0030] The outlet of the compr...

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Abstract

The invention discloses a wing ice preventing and removing device based on a nano composite phase-change material and a working method thereof. The wing ice preventing and removing device comprises anair compressor, a stop valve, a filter, a dryer, a wing inner flow channel, an electric heating ice removing assembly, a first temperature sensor, an icing detector, a metal fin, a second temperaturesensor, a water separator, a flow valve and a controller. An engine is adopted to introduce air, the air is filtered and dried and then is introduced into the inner flow channel of a wing, the air exchanges heat with the closed cavity layer through heat convection, and the nano composite phase-change material in the closed cavity layer is heated, so that redundant heat can be more quickly storedin the wing, and the surface of the wing is effectively prevented from icing. The electric heating deicing assembly is adopted to work when latent heat is insufficient, so that the device has the characteristics of high reliability, high anti-icing and deicing efficiency, low energy consumption and the like.

Description

technical field [0001] The invention relates to the technical field of aircraft anti-icing and deicing, in particular to a wing anti-icing device based on nanocomposite phase change materials and a working method thereof. Background technique [0002] Flying wing icing is a serious hazard. It destroys the aerodynamic flow field on the surface of the aircraft wing, increases flight resistance, and reduces wing lift. Due to the increase of the flight angle of attack caused by the nose lift, the critical angle of attack decreases, the aircraft will stall at a higher speed or lower angle of attack than normal, and the controllability and stability will deteriorate. cause serious flight accidents. [0003] The current common anti-icing technology can be divided into gas thermal anti-icing and electric thermal anti-icing according to the working mode. Air heat anti-icing refers to the high-temperature and high-pressure gas extracted from the aero-engine. The high-temperature and...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D15/04B64D15/12B64D15/20
CPCB64D15/04B64D15/12B64D15/20
Inventor 陈晨冯诗愚彭浩江荣杰刘卫华
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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