CN114435582A - Nearby-exhausting aircraft skin cooling system based on wind-liquid comprehensive cooling structure - Google Patents
Nearby-exhausting aircraft skin cooling system based on wind-liquid comprehensive cooling structure Download PDFInfo
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- CN114435582A CN114435582A CN202210018937.6A CN202210018937A CN114435582A CN 114435582 A CN114435582 A CN 114435582A CN 202210018937 A CN202210018937 A CN 202210018937A CN 114435582 A CN114435582 A CN 114435582A
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- air
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- liquid
- cooling
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- 239000007788 liquid Substances 0.000 title claims abstract description 75
- 238000001816 cooling Methods 0.000 title claims abstract description 66
- 230000017525 heat dissipation Effects 0.000 claims abstract description 45
- 238000006243 chemical reaction Methods 0.000 claims abstract description 19
- 230000008929 regeneration Effects 0.000 claims abstract description 10
- 238000011069 regeneration method Methods 0.000 claims abstract description 10
- 239000012530 fluid Substances 0.000 claims description 4
- 230000005855 radiation Effects 0.000 claims description 2
- VRAIHTAYLFXSJJ-UHFFFAOYSA-N alumane Chemical compound [AlH3].[AlH3] VRAIHTAYLFXSJJ-UHFFFAOYSA-N 0.000 claims 1
- 239000003570 air Substances 0.000 abstract description 92
- 239000012080 ambient air Substances 0.000 abstract description 4
- 239000002918 waste heat Substances 0.000 abstract description 2
- 230000004907 flux Effects 0.000 abstract 1
- 239000007791 liquid phase Substances 0.000 abstract 1
- 239000003507 refrigerant Substances 0.000 abstract 1
- 238000000034 method Methods 0.000 description 11
- 230000008569 process Effects 0.000 description 11
- 238000010586 diagram Methods 0.000 description 7
- 239000000446 fuel Substances 0.000 description 3
- 239000000295 fuel oil Substances 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- 239000002131 composite material Substances 0.000 description 2
- 230000007613 environmental effect Effects 0.000 description 2
- 239000000284 extract Substances 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 238000005057 refrigeration Methods 0.000 description 2
- 238000005482 strain hardening Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000011065 in-situ storage Methods 0.000 description 1
- 230000001172 regenerating effect Effects 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/38—Constructions adapted to reduce effects of aerodynamic or other external heating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D13/08—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned the air being heated or cooled
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Cooling Or The Like Of Electrical Apparatus (AREA)
Abstract
The invention discloses a nearby radiating aircraft skin radiator based on an air-liquid comprehensive radiating structure. Waste heat generated in the operation of the airborne equipment is absorbed by a liquid-phase refrigerant in a liquid cooling pipeline of the airborne equipment, is transferred to air in the cabin through an air-liquid comprehensive heat dissipation conversion pipeline, is transferred to the skin of the airplane through an air cooling regeneration pipeline in the cabin, and is finally dissipated to ambient air. The aircraft skin radiator has two radiating modes of liquid cooling radiating and air cooling radiating, can meet the requirement of high radiating heat flux density on the surface of airborne equipment under lower power consumption, and obviously improves the reliability of the aircraft skin radiator.
Description
Technical Field
The invention belongs to the technical field of airplane flight environment control, and particularly relates to a nearby radiating airplane skin radiating system based on a wind-liquid comprehensive radiating structure.
Background
The heat dissipation cold source of the airplane in the high-altitude high-speed flying environment mainly comprises: the aircraft comprises airborne low-temperature fuel oil, low-temperature ram air introduced from the environment, a low-temperature cold source carried before takeoff, low-temperature ducted air led out from an aircraft engine and low-temperature air outside an aircraft skin. With the increase of airborne equipment on the airplane and the increase of heat consumption of single airborne equipment, the total heat dissipation load of the airplane is remarkably increased, an airplane environment control system maintained by airborne low-temperature fuel oil is not used, and the airplane heat dissipation system needs to be further developed to get rid of the difficulty that the airplane environment control system has insufficient heat dissipation capacity and limits the use of the airborne equipment. Compared with low-temperature ram air, a low-temperature carrying cold source and low-temperature ducted air, the low-temperature air outside the airplane skin has better economical efficiency, the influence of the heat dissipation process on the whole structure of the airplane is small, and the airplane cold source is an ideal airplane cold source.
However, most of the existing aircraft skin radiators adopt a liquid-cooled structure, such as the aircraft skin liquid-cooled radiator of patent No. CN 214930566U; the refrigeration process is often supplemented by aircraft environmental control systems, such as an aircraft skin radiator that combines fuel circulation with an engine duct radiator, as disclosed in patent No. CN 109515728A. The aircraft skin radiators are complex in structure and long in refrigerating capacity transport distance, and need to be designed in a composite mode with the whole aircraft environmental control system, and the liquid cooling heat dissipation process of the aircraft skin radiators is not beneficial to operation, maintenance and repair of the aircraft skin radiators. Currently, aircraft skin radiators are not yet widely used.
Disclosure of Invention
The invention aims to provide a nearby radiating aircraft skin radiating system based on a wind-liquid comprehensive radiating structure. The hot air generated in the air cooling method is cooled by the aircraft skin radiator, and the heat is finally dissipated into the ambient air outside the aircraft skin radiator.
The technical solution for realizing the purpose of the invention is as follows:
an aircraft skin cooling system is dispelled nearby based on heat radiation structure is synthesized to geomantic omen, includes:
the airborne equipment liquid cooling pipeline is used for inputting liquid cooling working media to airborne equipment needing heat dissipation;
the air-liquid comprehensive heat dissipation conversion pipeline is connected with the liquid cooling pipeline of the airborne equipment and used for cooling the heated liquid cooling working medium and conveying the cooled liquid cooling working medium to the liquid cooling pipeline of the airborne equipment; further comprising:
the air cooling regeneration loop in the cabin comprises a skin air inlet channel, a skin radiator, an air pump and a skin air outlet channel; the skin radiator is arranged on a cabin at the rear part of the air cooling cabin, replaces the original aircraft skin structure and is used for carrying out convective heat exchange with the air environment atmosphere; the air inlet pipeline and the air outlet pipeline are arranged, and a plurality of arc-shaped pipelines are arranged between the air inlet pipeline and the air outlet pipeline; the skin air inlet channel is connected with the air inlet pipeline and used for sucking hot air emitted by the air-liquid comprehensive heat dissipation conversion pipeline, and the skin air outlet channel is connected with the air outlet pipeline and used for conveying cooled air to the air-liquid comprehensive heat dissipation conversion pipeline; the air pump is used for adjusting the air flow rate in the cabin according to the flying height and the air flow rate so as to adjust the heat dissipation efficiency.
Compared with the prior art, the invention has the remarkable advantages that:
(1) the liquid cooling and air cooling method is used in series between the heating surface of the airborne equipment and the low-temperature air outside the airplane cabin, so that the weight and the power consumption of the airplane skin radiator are reduced, the reliability of the airplane skin radiator is improved, and the maintenance is facilitated on the premise that the heat dissipation heat flow density requirement of the airborne equipment is met.
(2) The aircraft skin radiator can be used for nearby discharging waste heat generated by the onboard equipment to the outside of the cabin of the onboard equipment. The heat dissipation process of the near-emission does not need onboard fuel oil circulation, does not consume the air in the engine, does not have a long gas-liquid conveying pipeline, and has small refrigeration loss of the radiator; the whole heat dissipation process is relatively independent, the fuel circulation of the airplane, the air circulation in the cabin and the aerodynamic appearance of the airplane are not affected, and the design of the airplane and airborne equipment is facilitated.
(3) The working process of the aircraft skin radiator only consumes electric power and in-situ resources (low-temperature air outside the aircraft skin) in the flight environment, can continuously work for a long time, and is suitable for various flight states. By adjusting the power of the air pump, the aircraft skin radiator can provide relatively stable heat dissipation capacity at different flight heights and different flight speeds.
Drawings
Fig. 1 is a liquid cooling loop diagram of an onboard heating device.
Fig. 2 is a diagram of a wind-liquid comprehensive heat dissipation conversion pipeline.
FIG. 3 is a diagram of an in-cabin air cooling regeneration circuit.
Fig. 4 is a diagram of a liquid cooling loop and air-liquid integrated heat dissipation conversion pipeline of the airborne heating equipment.
Fig. 5 is a diagram of an air-liquid comprehensive heat dissipation conversion pipeline and an in-cabin air cooling regeneration loop.
FIG. 6 is a diagram of a nearby disbursed aircraft skin heat sink.
Fig. 7 is a structural view of an aircraft cabin.
FIG. 8 is a temperature distribution diagram of an aircraft skin radiator under an operating condition according to an embodiment.
FIG. 9 is a graph of the cyclic power consumption of an aircraft skin heatsink at different flying speeds and at different flying altitudes according to an embodiment.
Detailed Description
The invention is further described with reference to the following figures and embodiments.
With reference to fig. 1 to 7, the nearby-exhausting aircraft skin radiator based on the comprehensive air-liquid heat dissipation structure of the present embodiment includes an airborne equipment liquid cooling pipeline 1, an integrated air-liquid heat dissipation conversion pipeline 2, and an air cooling regeneration loop 3 in the cabin.
The airborne equipment liquid cooling pipeline 1 comprises a liquid supply pipeline 4, airborne equipment branch pipelines 5 and a liquid discharge pipeline 6, liquid cooling working media are parallelly input into the airborne equipment branch pipelines 5 from the liquid supply pipeline 4, and the liquid cooling working media are collected to the liquid discharge pipeline 6 to be output after absorbing heat.
The air-liquid comprehensive heat dissipation conversion pipeline 2 comprises a heat exchange pipe 7 with a fin structure and a fluid circulating pump 8 arranged on the heat exchange pipe. Two ends of the heat exchange tube 7 are respectively connected with a liquid supply pipeline 4 and a liquid discharge pipeline 6 of the airborne equipment liquid cooling pipeline 1, and hot liquid and cold working medium input into the air-liquid comprehensive heat dissipation conversion pipeline 2 from the liquid discharge pipeline 6 is pressurized by the fluid pump 8, is cooled and regenerated into cold liquid and cold working medium in the heat exchange tube 7 and is conveyed back to the airborne equipment liquid cooling pipeline 1.
The in-cabin air cooling and regenerating loop 3 comprises a skin air inlet channel 9, a skin radiator 10, an air pump 11 and a skin air outlet channel 12. The skin air inlet channel 9 and the skin air outlet channel 12 both adopt funnel-shaped air flow channels, have a certain compression effect on hot air entering the skin air inlet channel 9, and then flow into the skin radiator 10; the skin radiator 10 is of an arch structure and is processed on the basis of an aircraft skin with a three-layer composite structure of an outer skin, a middle-layer honeycomb skeleton and an inner skin, wherein the bottom of the middle-layer honeycomb skeleton is provided with an air inlet pipeline 101 and an air outlet pipeline 102, a plurality of arc pipelines 103 are arranged between the air inlet pipeline 101 and the air outlet pipeline 102 to form a hollow arc air flow channel, and air flows through the hollow annular air flow channel and is subjected to heat convection and cooling with low-temperature air in a high-altitude environment outside the outer skin; the skin air inlet channel 9 is connected with the air inlet pipeline 101, the inlet end is large, the skin air inlet channel is used for sucking hot air diffused by the air-liquid comprehensive heat dissipation conversion pipeline 2, the hot air entering the skin air inlet channel is compressed through a horn mouth, then the hot air is cooled through an arc air flow channel in the middle-layer honeycomb framework, the skin air exhaust channel 12 is connected with the air exhaust pipeline 102, the outlet end is large, and the cooled air is exhausted. The air pump 11 is arranged on the skin exhaust passage 12, and the air pump 11 pressurizes and extracts low-temperature air in the skin radiator 10 and inputs the low-temperature air into the cabin through the skin exhaust passage 12.
The air cooling regeneration pipeline in the cabin extracts air outside the fin heat dissipation pipe bundle in the air-liquid comprehensive heat dissipation conversion pipeline and conveys the air to the aircraft skin radiator for cooling. The low-temperature air output from the aircraft skin radiator is conveyed back to the outside of the fin radiating tube bundle in the comprehensive radiating and converting pipeline of the air liquid again.
Further, the onboard equipment liquid cooling pipeline 1, the air-liquid comprehensive heat dissipation conversion pipeline 2 and the in-cabin air cooling regeneration loop 3 are installed at the tail of the onboard equipment cabin 13. The front of the liquid cooling pipeline 1 of the airborne equipment is the airborne equipment 14 which needs heat dissipation, the air-liquid comprehensive heat dissipation conversion pipeline 2 and the air cooling regeneration loop 3 in the cabin are sealed in the air cooling cabin 15, and the air pump 11 in the air cooling regeneration loop 3 in the cabin is arranged in the air cooling bottom cabin 16; the skin radiator 10 is arranged on a cabin 17 at the rear part of the air cooling cabin 15 and replaces the original aircraft skin structure, and the appearance size of the skin radiator 10 is consistent with that of the original aircraft skin structure.
Further, the aircraft skin radiator controls the heat dissipation efficiency by adjusting the power consumption of the air pump 11. Under the low-altitude and low-speed flight condition (the position and the flight speed can be acquired through a flight control system), the power consumption of the air pump 11 is high, and the air flow rate in the aircraft skin radiator is high; under the condition of high-altitude and high-speed flight, the power consumption of the air pump 11 is low, and the air flow rate in the aircraft skin radiator is low. The heat dissipation efficiency of the aircraft skin radiator is kept relatively stable by adjusting the power consumption of the air pump 11. The aircraft skin near the airborne equipment is utilized to dissipate heat nearby, and the heat dissipation process is independent of the aircraft fuel circulation and the engine air supply circulation. The aircraft skin radiator mainly works in a high-altitude cruising state, the air flow rate in the cabin is adjusted along with the change of the flying speed and the flying height, and the heat dissipation capacity of the aircraft skin radiator is kept to be matched with the heat consumption of airborne equipment. In the normal working process of the radiator, air is not directly introduced into the ambient air to be mixed and cooled, and the heat transfer process between the radiator and the ambient air is a dividing wall heat transfer process, so that the aerodynamic performance of the airplane is not influenced.
The present embodiment is implemented on the premise of the technical solution of the present invention, and a detailed implementation manner and a specific operation process are given, but the scope of the present invention is not limited to the following embodiments.
The aircraft skin radiator in the embodiment provides cooling for the airborne equipment with the heat consumption of 10kW, the diameter of the aircraft skin cabin body is 2m, the length of the aircraft skin cabin body is 2m, and the area of the skin radiating surface is 2.11m2. The covering of the cabin body is a hard aluminum-honeycomb aluminum-hard aluminum three-layer covering structure, and the thickness of each layer is 5mm, 10mm and 5mm in sequence.
The design working conditions of the aircraft skin radiator are as follows: 6km and 0.7Ma cruise flight, and the maximum heat dissipation efficiency of the aircraft skin radiator is 5.61kW/m2The surface temperature of the skin is less than or equal to 48 ℃. In order to meet the 10kW heat dissipation requirement of airborne equipment, the circulating power consumption of the radiator is 1.16 kW. Under different flight speeds and flight heights, the aircraft skin radiator maintains the heat dissipation capacity of the aircraft skin radiator by adjusting the circulating power consumption, the working envelope line of the aircraft skin radiator is as shown in figure 9, and the heat dissipation efficiency of the aircraft skin radiator is improved along with the improvement of the flight height; along with the increase of the flight speed, the heat dissipation efficiency of the aircraft skin radiator is improved before the local sound velocity is reached; upon reaching the local speed of sound, the heat dissipation efficiency of the aircraft skin heat sink is reduced.
Claims (6)
1. An aircraft skin cooling system is dispelled nearby based on heat radiation structure is synthesized to geomantic omen, includes:
the airborne equipment liquid cooling pipeline is used for inputting liquid cooling working media to airborne equipment needing heat dissipation;
the air-liquid comprehensive heat dissipation conversion pipeline is connected with the liquid cooling pipeline of the airborne equipment and used for cooling the heated liquid cooling working medium and conveying the cooled liquid cooling working medium to the liquid cooling pipeline of the airborne equipment; it is characterized by also comprising:
the air cooling regeneration loop in the cabin comprises a skin air inlet channel, a skin radiator, an air pump and a skin air outlet channel; the skin radiator is arranged on a cabin at the rear part of the air cooling cabin, replaces the original aircraft skin structure and is used for carrying out convective heat exchange with the air ambient atmosphere; the air inlet pipeline and the air outlet pipeline are arranged, and a plurality of arc-shaped pipelines are arranged between the air inlet pipeline and the air outlet pipeline; the skin air inlet channel is connected with the air inlet pipeline and used for sucking hot air emitted by the air-liquid comprehensive heat dissipation conversion pipeline, and the skin air exhaust channel is connected with the air exhaust pipeline and used for conveying cooled air to the air-liquid comprehensive heat dissipation conversion pipeline; the air pump is used for adjusting the air flow rate in the cabin according to the flying height and the air flow rate so as to adjust the heat dissipation efficiency.
2. The system of claim 1, wherein the skin inlet channel and the skin outlet channel both use funnel-shaped air flow channels, and the inlet end of the skin inlet channel is larger and the outlet end of the skin outlet channel is larger.
3. The nearby dissipating aircraft skin cooling system based on the air-liquid comprehensive cooling structure according to claim 1, wherein the skin radiator has an outer skin, a middle honeycomb skeleton and an inner skin; the air inlet pipeline, the air exhaust pipeline and the arc-shaped pipeline are all arranged in the middle-layer honeycomb-shaped framework.
4. The system of claim 1, wherein the onboard equipment liquid cooling pipeline comprises a liquid supply pipeline, onboard equipment branch pipelines and a liquid discharge pipeline, and liquid cooling working media are parallelly input into the onboard equipment branch pipelines from the liquid supply pipeline and are collected to the liquid discharge pipeline for output after absorbing heat.
5. The nearby dissipation aircraft skin cooling system based on the comprehensive wind-liquid cooling structure is characterized in that the comprehensive wind-liquid cooling conversion pipeline comprises a heat exchange pipe with a fin structure and a fluid circulating pump mounted on the heat exchange pipe; and the two ends of the heat exchange tube are respectively connected with a liquid supply pipeline and a liquid discharge pipeline of the liquid cooling pipeline of the airborne equipment, and the liquid cooling working medium of the wind-liquid comprehensive heat dissipation conversion pipeline is pressurized by a fluid pump and then is air-cooled in the heat exchange tube and then is conveyed back to the liquid cooling pipeline of the airborne equipment.
6. The system as claimed in claim 1, wherein the skin radiator is an aluminum-honeycomb aluminum-aluminum tri-layer structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210018937.6A CN114435582A (en) | 2022-01-10 | 2022-01-10 | Nearby-exhausting aircraft skin cooling system based on wind-liquid comprehensive cooling structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210018937.6A CN114435582A (en) | 2022-01-10 | 2022-01-10 | Nearby-exhausting aircraft skin cooling system based on wind-liquid comprehensive cooling structure |
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| Publication Number | Publication Date |
|---|---|
| CN114435582A true CN114435582A (en) | 2022-05-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210018937.6A Pending CN114435582A (en) | 2022-01-10 | 2022-01-10 | Nearby-exhausting aircraft skin cooling system based on wind-liquid comprehensive cooling structure |
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| CN (1) | CN114435582A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5667168A (en) * | 1993-04-27 | 1997-09-16 | E-Systems, Inc. | Modular liquid skin heat exchanger |
| CN101405181A (en) * | 2006-03-21 | 2009-04-08 | 空中客车德国有限公司 | Drainage device, aircraft, and method for letting out a fluid that is present between the exterior skin and the interior lining of an aircraft |
| CN102295070A (en) * | 2011-05-04 | 2011-12-28 | 中国航空工业集团公司西安飞机设计研究所 | Double-layer air-liquid aircraft skin heat exchange method |
| CN102390538A (en) * | 2011-09-14 | 2012-03-28 | 中国航空工业集团公司西安飞机设计研究所 | Comprehensive environmental control/liquid cooling heat energy management system without ramjet inlet |
| US20160332724A1 (en) * | 2014-03-04 | 2016-11-17 | Parker-Hannifin Corporation | Heat exchanger for laminar-flow aircraft |
| CN109367801A (en) * | 2018-10-09 | 2019-02-22 | 北京航空航天大学 | A kind of distributed aircraft heat management system and method based on plane hydraulic system and miniature evaporation refrigeration circulation |
| CN109515728A (en) * | 2018-11-08 | 2019-03-26 | 北京航空航天大学 | Aircraft heat management system and method with auxiliary hot oil case circuit |
| US20210031937A1 (en) * | 2019-07-29 | 2021-02-04 | General Electric Company | Vehicle Heat Exchanger System |
-
2022
- 2022-01-10 CN CN202210018937.6A patent/CN114435582A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5667168A (en) * | 1993-04-27 | 1997-09-16 | E-Systems, Inc. | Modular liquid skin heat exchanger |
| CN101405181A (en) * | 2006-03-21 | 2009-04-08 | 空中客车德国有限公司 | Drainage device, aircraft, and method for letting out a fluid that is present between the exterior skin and the interior lining of an aircraft |
| CN102295070A (en) * | 2011-05-04 | 2011-12-28 | 中国航空工业集团公司西安飞机设计研究所 | Double-layer air-liquid aircraft skin heat exchange method |
| CN102390538A (en) * | 2011-09-14 | 2012-03-28 | 中国航空工业集团公司西安飞机设计研究所 | Comprehensive environmental control/liquid cooling heat energy management system without ramjet inlet |
| US20160332724A1 (en) * | 2014-03-04 | 2016-11-17 | Parker-Hannifin Corporation | Heat exchanger for laminar-flow aircraft |
| CN109367801A (en) * | 2018-10-09 | 2019-02-22 | 北京航空航天大学 | A kind of distributed aircraft heat management system and method based on plane hydraulic system and miniature evaporation refrigeration circulation |
| CN109515728A (en) * | 2018-11-08 | 2019-03-26 | 北京航空航天大学 | Aircraft heat management system and method with auxiliary hot oil case circuit |
| US20210031937A1 (en) * | 2019-07-29 | 2021-02-04 | General Electric Company | Vehicle Heat Exchanger System |
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Application publication date: 20220506 |