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Aircraft skin heat exchanger

A heat exchanger and aircraft skin technology, applied in heat exchange equipment, aircraft parts, fuselage, etc., to achieve the effects of reducing concentrated heat radiation and radar heat reflection area, high heat exchange efficiency, and reducing fuel compensation loss

Inactive Publication Date: 2016-03-02
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The object of the present invention is to provide an aircraft skin heat exchanger to solve or at least alleviate at least one of the problems in the background art

Method used

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Embodiment Construction

[0028] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...

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Abstract

The invention discloses an aircraft skin heat exchanger. The aircraft skin heat exchanger comprises a shell, a liquid inlet cavity, a liquid collecting cavity and multiple liquid microchannels. The shell contains an outer surface and an inner surface which are fixedly connected to form a sealed cavity. The shell is arranged on the outer surface of the outer skin of a fuselage and is fixedly connected to the fuselage. The multiple liquid microchannels are arranged inside the sealed cavity. One end of the each liquid microchannel is provided with the liquid inlet cavity communicated with the liquid microchannel, and the other end of the liquid microchannel is provided with the liquid collecting cavity communicated with the liquid microchannel. A liquid flows in through the liquid inlet cavity and flows to the liquid collecting cavity through the multiple liquid microchannels and flows out of the liquid collecting cavity. the invention has the following beneficial effects: heat of a liquid is taken away by the air so as to minimize aircraft fuel penalty by the system, heat exchange efficiency is high, concentrated thermal radiation and radar heat reflection area can be reduced, and aircraft stealth performance requirement can be met.

Description

technical field [0001] The invention relates to the technical field of aircraft heat exchangers, in particular to an aircraft skin heat exchanger. Background technique [0002] At present, there are two kinds of technologies close to this patent in the environmental control system at home and abroad: [0003] 1) Air-liquid heat exchanger (abbreviation: air-liquid heat exchanger) - use ram air inlet to cool the thermal fluid from electronic equipment. At present, most aircrafts at home and abroad adopt this form . [0004] Disadvantages: The air-liquid heat exchanger has a large volume and a high height (usually greater than 100㎜), the ram inlet and the ram air have a large aerodynamic resistance on the aircraft, and the air in the ram inlet has a greater impact on the aircraft. Fuel compensation loss. [0005] 2) Air-air skin heat exchanger (abbreviation: air skin heat exchanger) - when hot air flows in the interlayer between the outer skin of the aircraft and the fuselag...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/38B64C1/12B64D13/00F28F13/06
CPCB64C1/12B64C1/38B64D13/00F28F13/06Y02T50/50
Inventor 齐社红马兰何舟东李荣军李艳娜张秋
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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