CN114030619A - Modular helicopter air conditioning system - Google Patents
Modular helicopter air conditioning system Download PDFInfo
- Publication number
- CN114030619A CN114030619A CN202111382127.0A CN202111382127A CN114030619A CN 114030619 A CN114030619 A CN 114030619A CN 202111382127 A CN202111382127 A CN 202111382127A CN 114030619 A CN114030619 A CN 114030619A
- Authority
- CN
- China
- Prior art keywords
- air
- module
- helicopter
- cabin
- ventilation
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000004378 air conditioning Methods 0.000 title claims abstract description 31
- 210000001503 joint Anatomy 0.000 claims abstract description 29
- 238000005057 refrigeration Methods 0.000 claims abstract description 27
- 238000009423 ventilation Methods 0.000 claims abstract description 26
- 238000010438 heat treatment Methods 0.000 claims abstract description 25
- 238000010792 warming Methods 0.000 claims abstract description 9
- 230000005540 biological transmission Effects 0.000 claims abstract description 5
- 239000000853 adhesive Substances 0.000 claims description 2
- 230000001070 adhesive effect Effects 0.000 claims description 2
- 239000000565 sealant Substances 0.000 claims description 2
- 238000001816 cooling Methods 0.000 claims 3
- 238000003032 molecular docking Methods 0.000 claims 1
- 238000007789 sealing Methods 0.000 claims 1
- 108010066057 cabin-1 Proteins 0.000 description 9
- 238000009434 installation Methods 0.000 description 6
- 239000003507 refrigerant Substances 0.000 description 4
- 230000000903 blocking effect Effects 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 3
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000001704 evaporation Methods 0.000 description 2
- 230000008020 evaporation Effects 0.000 description 2
- 210000001015 abdomen Anatomy 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- 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
-
- 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
-
- 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
- B64D2013/0603—Environmental Control Systems
-
- 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
Landscapes
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Central Air Conditioning (AREA)
Abstract
The invention provides a modular helicopter air conditioning system comprising: the air distribution pipeline (2), the ventilation module, the warming module and the refrigeration module are arranged in the cabin (1); the air distribution pipeline (2) is provided with an air inlet butt joint surface (3), and the air return pipeline of the cabin is provided with an air return butt joint surface (4); the air inlet butt joint surface (3) and the air return butt joint surface (4) are detachably connected with one of the ventilation module, the heating module and the refrigeration module; the helicopter is characterized in that the ventilation module, the heating module or the refrigeration module are provided with the same mechanical interface and electrical interface, and the transmission platform or the air-conditioning cabin on the helicopter is internally provided with fixed interfaces corresponding to the mechanical interface and the electrical interface. When the helicopter is used, different modules are selected according to the ambient temperature, no ineffective load exists, and the weight of the helicopter can be greatly reduced.
Description
Technical Field
The invention belongs to the field of design of helicopter air-conditioning systems, and relates to a modularized helicopter air-conditioning system.
Background
At present, the helicopter is generally used in an environment of-40 ℃ to 50 ℃, and is generally realized by a heating system and a refrigerating system in order to keep a comfortable environment in a cabin. The heating system generally takes hot air in the compression section of the engine as a heat source, mixes the hot air with external cold air to a proper temperature, and then enters a cabin, and comprises a shut-off valve, an electric valve, a fan, an ejector, a mixing chamber and the like. The refrigeration system generally adopts the principle of an evaporation cycle to carry heat in a cabin to the outside of the cabin, and comprises a compressor, a condenser, an evaporator, a refrigerant pipeline and the like.
The heating system and the refrigerating system on the helicopter are generally independent from each other, and all the components are dispersedly arranged on different positions of the helicopter, for example, the shutoff valve is generally arranged on a transmission platform, the evaporator is generally arranged in a cabin, the occupied space is large, and the disassembly and the assembly are difficult.
In the using process of the helicopter, the heating system and the refrigerating system do not work simultaneously, the heating system does not work in a high-temperature environment, the refrigerating system does not work in a low-temperature environment, but the helicopter always bears the weight of the two systems, so that the problem of large ineffective load exists.
Disclosure of Invention
The invention provides a modularized helicopter air conditioning system, which solves the problems of large occupied space, difficulty in disassembly and assembly and large ineffective load of the conventional helicopter air conditioning equipment.
The invention provides a modular helicopter air conditioning system comprising: the air distribution pipeline 2, the ventilation module, the warming module and the refrigeration module are arranged in the cabin 1;
the air distribution pipeline 2 is provided with an air inlet butt joint surface 3, and the air return pipeline of the cabin is provided with an air return butt joint surface 4;
the air inlet butt joint surface 3 and the air return butt joint surface 4 are detachably connected with one of the ventilation module, the heating module and the refrigeration module;
the helicopter is characterized in that the ventilation module, the heating module or the refrigeration module are provided with the same mechanical interface and electrical interface, and the transmission platform or the air-conditioning cabin on the helicopter is internally provided with fixed interfaces corresponding to the mechanical interface and the electrical interface.
Optionally, each component in the ventilation module, the heating module or the refrigeration module is fixed on the respective air conditioning system bracket 8 by using a rivet, a bolt, an adhesive, a sealant or a fuse fastening connection mode, and an air pipeline between each component is connected by using a hard pipe.
Optionally, the ventilation module, the heating module or the refrigeration module are mechanically connected with the helicopter through respective air conditioning system brackets 8 in a detachable connection mode through quick-release locks, slide rails, limiting blocks or snap rings.
Optionally, the air conditioning system support 8 is provided with separate sockets 9 of the same specification, and power lines and control lines of all the electric devices in the ventilation module, the heating module or the refrigeration module are connected to the separate sockets 9.
Optionally, when the ventilation module or the refrigeration module is connected to the air inlet butt-joint surface 3 and the air return butt-joint surface 4, a blocking sleeve 11 is arranged on a port of the engine bleed air pipeline 10.
Optionally, the heating module with air inlet butt joint face 3 with when return air butt joint face 4 is connected, the hot air pipeline 13 of the heating module can be dismantled with engine bleed air pipeline 10 through high temperature resistant quick-release clamp or flaring type cap nut and be connected.
Optionally, the air inlet butt joint face 3 with the return air butt joint face 4 adopt sleeve pipe, spiral clamp or sealed flange with one of ventilation module, the module of heating and the refrigeration module can be dismantled and be connected.
Optionally, the refrigeration module includes a four-way valve 18, and inputs hot air into the cabin 1 in an environment of 30 ℃ or higher, and inputs cold air into the cabin 1 in a low-temperature environment of 0 ℃ to 20 ℃.
The invention provides a modularized helicopter air conditioning system which comprises a ventilation module, a heating module and a refrigeration module, wherein the three modules are installed at the same position on a helicopter by using the same installation interface, pipeline interface and electrical interface, and are in mutual substitution relationship, and different modules are crosslinked with various systems of the helicopter through a sleeve, a slide rail, a separation socket and the like, so that the quick disassembly and installation can be realized. When the helicopter is used, different modules are selected according to the ambient temperature, no ineffective load exists, and the weight of the helicopter can be greatly reduced.
Drawings
FIG. 1 is a schematic view of the installation of a ventilation module of a modular helicopter air conditioning system provided in accordance with the present invention;
FIG. 2 is a schematic view of the installation of a warming module of the modular helicopter air conditioning system provided in the present invention;
FIG. 3 is a schematic view of the installation of the refrigeration module of the modular helicopter air conditioning system provided in accordance with the present invention;
description of reference numerals:
1-cabin; 2-air distribution line; 3-air intake butt joint surface;
4-air return butt joint surface; 5, a fan; 6-air switching valve;
7-fresh air port; 8, an air conditioning system bracket; 9-a separate socket;
10-engine bleed air line; 11-blocking the sleeve; 12-a mixing chamber;
13-hot air line; 14-shutoff valve; 15-electric valve;
16-an ejector; 17-an evaporator; 18-a four-way valve;
19-a compressor; and 20, a condenser.
Detailed Description
The modular helicopter air conditioning system provided by the present invention is described in detail below with reference to the accompanying drawings.
As shown in fig. 1-3, the present invention provides a modular helicopter air conditioning system comprising: the air distribution pipeline 2, the ventilation module, the warming module and the refrigeration module are arranged in the cabin 1;
the air distribution pipeline 2 is provided with an air inlet butt joint surface 3, and a return air pipe of the cabin 1 is provided with a return air butt joint surface 4;
the air inlet butt joint surface 3 and the air return butt joint surface 4 are connected with the ventilation module, the heating module or the refrigeration module through butt joint sleeves, so that quick disassembly and assembly can be realized;
the ventilation module, the heating module or the refrigeration module are provided with the same mounting interfaces and are all mounted on a transmission platform of the helicopter or in an air-conditioning cabin at the belly of the helicopter body;
separate sockets are arranged on the ventilation module, the heating module or the refrigeration module, and the internal wiring of each module is different, but the same plug is adopted as an electrical system and a control system on the machine.
According to the air conditioning system provided by the invention, through modular design, the modules can be quickly replaced by the helicopter according to the environment temperature and the task requirement, the installation space and the weight on the helicopter are saved, taking a certain type of helicopter as an example, the weight of the traditional air conditioning system is 80kg, and the weight of the air conditioning system provided by the invention can be controlled within the range of 15-50 kg under different modules.
The ventilation module comprises a fan 5, an air conversion valve 6, a fresh air port 7, an air conditioning system bracket 8 and the like, is connected with the air distribution pipeline 2 through an air inlet butt joint surface 3, is connected with the cabin 1 through an air return butt joint surface 4, and an engine air guide pipeline 10 is blocked by a blocking sleeve 11 and is used for inputting air to the cabin, and is mainly used for the conditions of moderate temperature and low-altitude flight, and the weight of the system is about 15 kg.
Illustratively, the heating module comprises an air conversion valve 6, a fresh air port 7, an air conditioning system support 8, a mixing chamber 12, a shut-off valve 14, an electric valve 15, an ejector 16 and the like, is connected with the air distribution pipeline 2 through an air inlet butt joint surface 3, is connected with the cabin 1 through an air return butt joint surface 4, is connected with the engine air guide pipeline 10 through a high-temperature hoop or a flared type outer sleeve nut which can be quickly detached, guides hot air from an engine compression section, ejects cold air through the ejector 16, mixes the cold air with the hot air in the mixing chamber 12 to a proper temperature and then enters the cabin 1, and is suitable for a flight environment at-40-20 ℃, and the weight of the system is about 35 kg.
Illustratively, the refrigeration module comprises a compressor 19, a condenser 20, an evaporator 17, a four-way valve 18, an air conversion valve 6, a fresh air inlet 7 and the like, is connected with the air distribution pipeline 2 through an air inlet butt joint surface 3, is connected with the cabin 1 through an air return butt joint surface 4, an engine air guide pipeline 10 is blocked by a blocking sleeve 11, and the circulation flow direction of a refrigerant in a high-temperature environment (above 30 ℃) is as follows by using the working principle of an evaporation cycle: evaporator → compressor → condenser → evaporator, the refrigeration system delivers cold air to the cabin; in a low-temperature environment (0 ℃ to 20 ℃), the flow direction of the refrigerant is reversed by the four-way valve 18, and the circulating flow direction of the refrigerant is as follows: condenser → compressor → evaporator → condenser, which is used to transport hot air to cabin, with certain heating ability, and is suitable for 0-50 deg.C flying environment, and the weight of the system is about 50 kg.
Claims (8)
1. A modular helicopter air conditioning system comprising: the air distribution pipeline (2), the ventilation module, the warming module and the refrigeration module are arranged in the cabin (1);
the air distribution pipeline (2) is provided with an air inlet butt joint surface (3), and the air return pipeline of the cabin is provided with an air return butt joint surface (4);
the air inlet butt joint surface (3) and the air return butt joint surface (4) are detachably connected with one of the ventilation module, the heating module and the refrigeration module;
the helicopter is characterized in that the ventilation module, the heating module or the refrigeration module are provided with the same mechanical interface and electrical interface, and the transmission platform or the air-conditioning cabin on the helicopter is internally provided with fixed interfaces corresponding to the mechanical interface and the electrical interface.
2. The system according to claim 1, characterized in that the individual components in the ventilation, heating or cooling module are fastened to the respective air conditioning system support (8) using rivets, bolts, adhesives, sealants or fuse fastening, and the air lines between the individual components are hard-piped.
3. The system according to claim 2, characterized in that the ventilation module, the warming module or the cooling module are mechanically connected to the helicopter through respective air conditioning system brackets (8) by means of quick release locks, slide rails, stop blocks or snap rings, respectively.
4. The system according to claim 3, characterized in that the air conditioning system support (8) is provided with separate sockets (9) of the same size, and the power lines and control lines of all the electric devices in the ventilation module, the heating module or the cooling module are connected to the separate sockets (9).
5. The system according to claim 1, characterized in that a plug sleeve (11) is provided on the port of the engine bleed air line (10) when the ventilation or refrigeration module is connected to the intake (3) and return (4) docking surfaces.
6. The system according to claim 1, characterized in that the hot air line (13) of the warming module is detachably connected to the engine bleed air line (10) by means of a high temperature resistant quick release clip or flared cap nut when the warming module is connected to the intake air interface (3) and the return air interface (4).
7. The system of claim 1, wherein the air intake interface (3) and the air return interface (4) are removably connected to one of the ventilation module, the warming module, and the refrigeration module using a sleeve, a spiral clamp, or a sealing flange.
8. System according to claim 1, characterized in that the refrigeration module comprises a four-way valve (18) for feeding hot air into the cabin (1) in an environment above 30 ℃ and cold air into the cabin (1) in a low temperature environment between 0 ℃ and 20 ℃.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111382127.0A CN114030619B (en) | 2021-11-19 | 2021-11-19 | Modularized helicopter air conditioning system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111382127.0A CN114030619B (en) | 2021-11-19 | 2021-11-19 | Modularized helicopter air conditioning system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114030619A true CN114030619A (en) | 2022-02-11 |
| CN114030619B CN114030619B (en) | 2023-10-27 |
Family
ID=80145060
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111382127.0A Active CN114030619B (en) | 2021-11-19 | 2021-11-19 | Modularized helicopter air conditioning system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114030619B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101148197A (en) * | 2007-10-26 | 2008-03-26 | 北京航空航天大学 | Cabin circumstance control system used for passenger plane |
| US20120067965A1 (en) * | 2010-09-17 | 2012-03-22 | Hobart Brothers Company | Control systems and methods for modular heating, ventilating, air conditioning, and refrigeration systems |
| CN102713448A (en) * | 2009-11-19 | 2012-10-03 | 伊利诺斯工具制品有限公司 | Modular heating, ventilating, air conditioning, and refrigeration systems and methods |
| CN108100263A (en) * | 2017-12-03 | 2018-06-01 | 中国直升机设计研究所 | A kind of helicopter integrates environmental control system |
| CN110816851A (en) * | 2019-10-11 | 2020-02-21 | 中国直升机设计研究所 | Helicopter environmental control integrated control system |
| CN111268140A (en) * | 2020-02-10 | 2020-06-12 | 南京航空航天大学 | Green environmental control system of aircraft |
-
2021
- 2021-11-19 CN CN202111382127.0A patent/CN114030619B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101148197A (en) * | 2007-10-26 | 2008-03-26 | 北京航空航天大学 | Cabin circumstance control system used for passenger plane |
| CN102713448A (en) * | 2009-11-19 | 2012-10-03 | 伊利诺斯工具制品有限公司 | Modular heating, ventilating, air conditioning, and refrigeration systems and methods |
| US20120067965A1 (en) * | 2010-09-17 | 2012-03-22 | Hobart Brothers Company | Control systems and methods for modular heating, ventilating, air conditioning, and refrigeration systems |
| CN108100263A (en) * | 2017-12-03 | 2018-06-01 | 中国直升机设计研究所 | A kind of helicopter integrates environmental control system |
| CN110816851A (en) * | 2019-10-11 | 2020-02-21 | 中国直升机设计研究所 | Helicopter environmental control integrated control system |
| CN111268140A (en) * | 2020-02-10 | 2020-06-12 | 南京航空航天大学 | Green environmental control system of aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114030619B (en) | 2023-10-27 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| RU2608195C2 (en) | Method and system of energy recovery in aircraft | |
| EP1979232B1 (en) | Air conditioning arrangement for an aircraft with a plurality of climate zones that may be individually temperature-controlled | |
| US10858113B2 (en) | Aircraft air conditioning system and method for operating such an aircraft air conditioning system | |
| CN102596719B (en) | For aerocraft system and the method for improved cooling efficiency | |
| US10245918B2 (en) | Heating system for a vehicle and method for air-conditioning a vehicle | |
| US20170268810A1 (en) | Heat Exchanger with Integral Bypass Valve | |
| US9090350B2 (en) | System for cooling an aircraft zone, to be connected to an aircraft-external air unit | |
| CN102076562A (en) | System for ventilating an aircraft area | |
| CN102917950A (en) | Air conditioning system with hybrid operation for an aircraft | |
| US10507928B2 (en) | High efficiency electrically driven environmental control system | |
| US20140150988A1 (en) | Conduit module coupled with heating or cooling module | |
| CN102390538A (en) | Comprehensive environmental control/liquid cooling heat energy management system without ramjet inlet | |
| CN101385175B (en) | A combination of a heat generating system with a fuel cell system | |
| CN106697297A (en) | Environmental control system capable of simultaneously providing liquid cooling and air cooling | |
| CN105882353A (en) | Electricity-saving air conditioner for vehicle | |
| CN114030619A (en) | Modular helicopter air conditioning system | |
| CN103612760B (en) | A kind of closed air refrigerating circulatory device actively reclaiming cold | |
| CN208653007U (en) | Refrigeration equipment | |
| CN111137102A (en) | Passenger train overhead air conditioning unit of modular design | |
| CN208238297U (en) | Four-pipe system air-cooled unit | |
| US10472073B2 (en) | Air conditioning system | |
| CN202770042U (en) | Whole sealing air circulation refrigerating system driven by power turbine | |
| CN203687263U (en) | Aviation air conditioning vehicle system for ships | |
| CN219706614U (en) | Refrigerating and heating device for new energy commercial vehicle | |
| US20140047856A1 (en) | Forward manifold |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |