CN108100264B - Helicopter air conditioner refrigerating system - Google Patents
Helicopter air conditioner refrigerating system Download PDFInfo
- Publication number
- CN108100264B CN108100264B CN201711376104.2A CN201711376104A CN108100264B CN 108100264 B CN108100264 B CN 108100264B CN 201711376104 A CN201711376104 A CN 201711376104A CN 108100264 B CN108100264 B CN 108100264B
- Authority
- CN
- China
- Prior art keywords
- contactor
- compressor
- air
- helicopter
- power supply
- 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.)
- Active
Links
- 238000005057 refrigeration Methods 0.000 claims abstract description 21
- 238000009423 ventilation Methods 0.000 claims abstract description 15
- 238000004378 air conditioning Methods 0.000 claims abstract description 14
- 230000001133 acceleration Effects 0.000 claims abstract description 8
- 239000003507 refrigerant Substances 0.000 claims description 50
- 239000007788 liquid Substances 0.000 claims description 26
- 238000007599 discharging Methods 0.000 claims description 6
- 238000005516 engineering process Methods 0.000 abstract description 5
- 238000000034 method Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000005611 electricity Effects 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000008020 evaporation Effects 0.000 description 1
- 238000001704 evaporation Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 230000001788 irregular Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
- F25B49/00—Arrangement or mounting of control or safety devices
- F25B49/02—Arrangement or mounting of control or safety devices for compression type machines, plants or systems
- F25B49/025—Motor control arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
- F25B2600/00—Control issues
- F25B2600/02—Compressor control
- F25B2600/024—Compressor control by controlling the electric parameters, e.g. current or voltage
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
- F25B—REFRIGERATION MACHINES, PLANTS OR SYSTEMS; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS
- F25B2600/00—Control issues
- F25B2600/02—Compressor control
- F25B2600/025—Compressor control by controlling speed
- F25B2600/0251—Compressor control by controlling speed with on-off operation
Landscapes
- Engineering & Computer Science (AREA)
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Mechanical Engineering (AREA)
- Thermal Sciences (AREA)
- General Engineering & Computer Science (AREA)
- Air-Conditioning For Vehicles (AREA)
- Air Conditioning Control Device (AREA)
Abstract
The invention discloses a helicopter air-conditioning refrigeration system, which comprises: the soft start unit is used for controlling the working current and the rotating speed of the compressor when the compressor is started, reducing the acceleration of the working current when the compressor is started and reducing the acceleration of the rotating speed when the compressor is started; the interlocking unit is used for controlling the air conditioner and the airborne heavy load component to work in a staggered mode; and the circulating unit is used for arranging an air duct by utilizing the existing air supply device and ventilation duct of the helicopter to realize circulating refrigeration. The invention can reduce the impact of the air conditioner start on the airborne power supply by adopting the compressor soft start technology, solves the problem of insufficient power supply between the air conditioner power supply and the airborne heavy-load component power supply by adopting the interlocking scheme between the airborne heavy-load power supply component and the air conditioner power supply, and solves the problems of difficult arrangement of the helicopter air duct, insufficient air volume, insufficient refrigerating capacity and heavy weight by utilizing the original ventilation air duct, air outlet and air supply device according to the self characteristics of the helicopter.
Description
Technical Field
The invention relates to the technical field of airplane environment control, in particular to a helicopter air-conditioning refrigeration system.
Background
The existing helicopter air-conditioning refrigeration system mainly has the following problems: 1. the impact of the air conditioner starting current on the onboard power supply is too large, the stability of the onboard power supply is influenced, the power consumption of onboard equipment is threatened, and even partial equipment cannot work; 2. under a specific environment, an airborne heavy-load component and an air conditioner work simultaneously, so that the power supply of the helicopter is insufficient, and the normal work of main functional components is influenced; 3. the compact structure of the helicopter causes that the pipeline arrangement and the air port arrangement are difficult to realize, the problems of insufficient air quantity, incapability of meeting the requirement of refrigeration effect and the like exist after the air channel is arranged, but the total weight of the air conditioner still reaches 50-60 kg, and the effective load capacity of the helicopter is reduced.
Through the investigation of patents, products, documents and the like at home and abroad, no processing technology which is the same as or similar to the solution proposed for the three problems is found.
Disclosure of Invention
In view of this, the present invention aims to overcome the defects of the prior art, and provides a refrigeration system for a helicopter air conditioner, so as to solve the impact of the air conditioner start on an onboard power supply, solve the problem of insufficient power supply between the power consumption of the air conditioner and the power consumption of an onboard heavy load component, and solve the problems of difficult layout of an air duct, insufficient air volume, insufficient refrigeration capacity and heavy weight of the helicopter.
In order to achieve the purpose, the invention adopts the following technical scheme:
a helicopter air conditioning refrigeration system comprising:
the soft start unit is used for controlling the working current and the rotating speed of the compressor when the compressor is started, reducing the acceleration of the working current when the compressor is started and reducing the acceleration of the rotating speed when the compressor is started;
the interlocking unit is used for controlling the air conditioner and the airborne heavy load component to work in a staggered mode;
and the circulating unit is used for arranging an air duct by utilizing the existing air supply device and ventilation duct of the helicopter to realize circulating refrigeration.
Preferably, the soft start unit comprises a first contactor, a second contactor, a control panel and a soft start module, the first contactor is connected between an onboard direct-current power supply and the control panel, the second contactor and the soft start module are sequentially connected between an onboard three-phase alternating-current power supply and the compressor, and the soft start module is connected with the control panel;
the soft start module is used for acquiring state information of the compressor and sending the state information to the control panel, the control panel is used for sending a control signal according to the state information, and the soft start module drives the onboard three-phase alternating-current power supply to supply power to the compressor according to the control signal;
the state information includes an operating current and a rotational speed of the compressor.
Preferably, the interlock unit includes a first control switch, a second control switch, a third contactor and a fourth contactor, the third contactor is connected between the onboard direct-current power supply and the first onboard heavy load component, the fourth contactor is connected between the onboard three-phase alternating-current power supply and the second onboard heavy load component, the first control switch is respectively connected with the third contactor, the first contactor and the second contactor, and the second control switch is respectively connected with the fourth contactor, the first contactor and the second contactor;
the airborne direct-current power supply is used for supplying power to the first control switch and the second control switch, when the first control switch controls the third contactor to be switched on, the first contactor and the second contactor are controlled to be switched off simultaneously, and when the second control switch controls the fourth contactor to be switched on, the first contactor and the second contactor are controlled to be switched off simultaneously.
Preferably, the helicopter is provided with a first fan and a second fan, and the first contactor is further connected with the first fan and the second fan.
Preferably, the circulation unit comprises an evaporator assembly, a compressor, a condenser assembly, an expansion valve, an air supply device and a ventilation pipeline, wherein the evaporator assembly, the compressor, the condenser assembly and the expansion valve form a refrigerant circulation loop, and the air supply device, the evaporator assembly and a cabin of the helicopter are connected through the ventilation pipeline;
the compressor is used for sucking the low-temperature and low-pressure gaseous refrigerant at the outlet of the evaporator assembly and compressing the gaseous refrigerant into high-temperature and high-pressure liquid refrigerant for discharge;
the condenser assembly is used for gradually condensing the high-temperature high-pressure liquid refrigerant into a low-temperature high-pressure liquid refrigerant and discharging the dissipated heat to the external environment;
the expansion valve is used for throttling and depressurizing the low-temperature high-pressure liquid refrigerant and discharging the low-temperature high-pressure liquid refrigerant in a gas-liquid two-phase state;
the evaporator assembly is used for completely gasifying the refrigerant in a gas-liquid two-phase state to absorb heat in air, so as to form a low-temperature low-pressure gaseous refrigerant in an overheated state, and the low-temperature low-pressure gaseous refrigerant enters the compressor;
and the air supply device is used for sending the cooled air into a cabin of the helicopter for closed circulation.
Preferably, the onboard heavy load component comprises a hoisting heavy load and a lighting heavy load.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention adopts the soft start technology of the compressor, controls the slow increase of the working current and the slow rise of the rotating speed of the compressor, reduces the overlarge impact current when the compressor is started, and ensures the electricity utilization safety of the helicopter; the normal working current of the compressor is 20A, the starting impact current of the compressor is 80A-100A without a soft start scheme, and the starting current is not more than 50A after the soft start technology is added.
2. The invention adopts the interlocking scheme between the airborne heavy-load power utilization component and the air conditioner power utilization, the power supply capacity of the helicopter is limited, the scheme ensures that the air conditioner power utilization and the airborne heavy-load component power utilization work in a staggered mode, the risk of insufficient power supply of an airborne power supply is eliminated, and the power utilization safety of the helicopter is ensured.
3. According to the characteristics of the helicopter, the problems of difficult air duct arrangement, air outlet arrangement and wind resistance calculation are completely solved by utilizing the original ventilation air duct, air outlet and air supply device, the problems of air volume matching and air volume distribution of the front cabin and the rear cabin are solved by utilizing the original fan, the overall weight of the air conditioner is greatly reduced, and the effective load capacity is improved; according to the scheme, the overall weight of the air conditioner is reduced to 40kg from 50-60 kg, and the problem of insufficient air volume of the air conditioner caused by arrangement of irregular air channels is avoided.
Drawings
FIG. 1 is a block diagram of the helicopter air conditioning refrigeration system of the present invention;
FIG. 2 is a schematic structural diagram of the soft start unit according to the present invention;
FIG. 3 is a schematic structural view of an interlock unit according to the present invention;
FIG. 4 is a schematic view of the construction of the circulation unit according to the present invention;
FIG. 5 is a schematic view of a helicopter circulation circuit layout in an embodiment of the present invention.
In the figure: 1-a soft start unit, 101-a first contactor, 102-a second contactor, 103-a control panel, 104-a soft start module, 2-an interlocking unit, 201-a first control switch, 202-a second control switch, 203-a third contactor, 204-a fourth contactor, 3-a circulation unit, 4-an onboard direct current power supply, 5-an onboard three-phase alternating current power supply, 6-a compressor, 7-a first onboard heavy load part, 8-a second onboard heavy load part, 9-a first fan, 10-a second fan, 11-an evaporator component, 12-a condenser component, 13-an expansion valve, 14-an air supply device, 15-a ventilation pipeline, 16-a cabin, 17-a front air outlet and 18-a rear air outlet, 19-refrigerant pipe.
Detailed Description
The technical solution of the present invention is further described in detail by the accompanying drawings and embodiments.
The invention provides a helicopter air-conditioning refrigeration system, as shown in fig. 1, the helicopter air-conditioning refrigeration system comprises: the soft start unit 1 is used for controlling the working current and the rotating speed of the compressor during starting, reducing the acceleration of the working current during starting the compressor and reducing the acceleration of the rotating speed during starting the compressor; the interlocking unit 2 is used for controlling the air conditioner and the airborne heavy load component to work in a staggered mode; and the circulating unit 3 is used for arranging an air duct by utilizing the existing air supply device and ventilation duct of the helicopter to realize circulating refrigeration.
The soft start unit 1 controls the working current of the compressor to be slowly increased and the rotating speed to be slowly increased, so that overlarge impact current when the compressor is started is reduced, and the electricity utilization safety of the helicopter is ensured; the interlocking unit 2 ensures that the power consumption of the air conditioner and the power consumption of the airborne heavy-load component work in a staggered manner, and the risk of insufficient power supply of an airborne power supply is avoided; the circulating unit 3 utilizes the original ventilation air duct, air outlet and air supply device according to the characteristics of the helicopter, solves the problem of air duct arrangement, greatly reduces the overall weight of the air conditioner, and improves the effective load capacity.
Further, as shown in fig. 2, the soft start unit 1 includes a first contactor 101, a second contactor 102, a control panel 103, and a soft start module 104, the first contactor 101 is connected between the on-board dc power supply 4 and the control panel 103, the second contactor 102 and the soft start module 104 are sequentially connected between the on-board three-phase ac power supply 5 and the compressor 6, and the soft start module 104 is connected to the control panel 103;
the soft start module 104 is used for acquiring state information of the compressor 6 and sending the state information to the control panel 103, the control panel 103 is used for sending out a control signal according to the state information, and the soft start module 104 drives the airborne three-phase alternating-current power supply 5 to supply power to the compressor 6 according to the control signal;
the state information includes the working current and the rotating speed of the compressor 6, and the soft start module 104 controls the working current and the rotating speed of the motor of the compressor 6 to be slowly increased, so that the impact of large current on the airborne power supply is avoided. In the embodiment, the compressor 6 is driven by the three onboard alternating current power supplies 5, the normal starting current of the compressor 6 is 110A, and after the soft start technology is adopted for the compressor 6, the starting current can be reduced to 30A.
Further, as shown in fig. 3, the interlock unit 2 includes a first control switch 201, a second control switch 202, a third contactor 203 and a fourth contactor 204, the third contactor 203 is connected between the on-board dc power supply 4 and the first on-board heavy load component 7, the fourth contactor 204 is connected between the on-board three-phase ac power supply 5 and the second on-board heavy load component 8, the first control switch 201 is connected to the third contactor 203, the first contactor 101 and the second contactor 102, respectively, and the second control switch 202 is connected to the fourth contactor 204, the first contactor 101 and the second contactor 102, respectively;
the on-board dc power supply 4 is used for supplying power to the first control switch 201 and the second control switch 202, and simultaneously controls the first contactor 101 and the second contactor 102 to be disconnected when the first control switch 201 controls the third contactor 203 to be connected, and simultaneously controls the first contactor 101 and the second contactor 102 to be disconnected when the second control switch 202 controls the fourth contactor 204 to be connected.
The airborne heavy load component comprises a hoisting high-power load, a lighting high-power load and the like, for example, the first airborne heavy load component 7 and the second airborne heavy load component 8 can be hoisting high-power loads or lighting high-power loads.
Further, a first fan 9 and a second fan 10 are arranged on the helicopter, and the first contactor 101 is further connected with the first fan 9 and the second fan 10. The first fan 9 and the second fan 10 belong to a helicopter air supply device, and can be used in an air conditioning refrigeration system by matching with an existing ventilation pipeline of a helicopter.
When the first airborne heavy load component 7 or the second airborne heavy load component 8 is detected to be connected with the power supply and is in a power utilization state, the first contactor 101 and the second contactor 102 are automatically disconnected with the airborne direct-current power supply 4 and the airborne three-phase alternating-current power supply 5 respectively, so that the air-conditioning related equipment and the airborne heavy load component are prevented from working simultaneously, and the airborne heavy load component is ensured to be sufficiently supplied with power.
Further, as shown in fig. 4, the circulation unit 3 includes an evaporator assembly 11, a compressor 6, a condenser assembly 12, an expansion valve 13, an air supply device 14 and a ventilation duct 15, the evaporator assembly 11, the compressor 6, the condenser assembly 12 and the expansion valve 13 form a refrigerant circulation loop, and the air supply device 14, the evaporator assembly 11 and a cabin 16 of the helicopter are connected through the ventilation duct 15;
the compressor 6 is used for sucking low-temperature and low-pressure gaseous refrigerant at the outlet of the evaporator assembly 11 and compressing the gaseous refrigerant into high-temperature and high-pressure liquid refrigerant for discharge; the condenser assembly 12 is used for gradually condensing the high-temperature high-pressure liquid refrigerant into a high-temperature high-pressure liquid refrigerant, and discharging the dissipated heat to the external environment; the expansion valve 13 is used for throttling and depressurizing the low-temperature high-pressure liquid refrigerant and discharging the low-temperature high-pressure liquid refrigerant in a gas-liquid two-phase state; the evaporator assembly 11 is used for completely gasifying the refrigerant in a gas-liquid two-phase state to absorb heat in air, forming a low-temperature and low-pressure gaseous refrigerant in an overheated state, and entering the compressor 6; the air supply 14 is used to feed cooled air into the nacelle 16 of the helicopter for closed circulation.
Specifically, the helicopter adopts an evaporation cycle refrigeration principle and comprises four processes:
a) and (3) a compression process: the compressor 6 sucks the low-temperature and low-pressure gaseous refrigerant from the outlet of the evaporator unit 11, and compresses the refrigerant into a high-temperature and high-pressure liquid refrigerant, which is discharged from the compressor 6.
b) An exothermic process: the high-temperature high-pressure liquid refrigerant enters the condenser assembly 12, is gradually condensed into low-temperature high-pressure liquid refrigerant, emits a large amount of heat, and discharges the heat dissipated by the refrigerant to the external environment through the condensing fan.
c) And (3) throttling process: the high-temperature and high-pressure liquid refrigerant is throttled and depressurized by the expansion valve 13, the pressure and temperature are rapidly decreased, and the refrigerant is discharged out of the expansion valve 13 in a gas-liquid two-phase state.
d) And (3) heat absorption process: the refrigerant in the two-phase state enters the evaporator unit 11, the refrigerant is completely vaporized in the evaporator, the heat of the air in the cargo compartment is absorbed by the evaporator unit 11, and the refrigerant becomes a low-temperature and low-pressure gaseous refrigerant in a superheated state at the outlet and then enters the compressor 6.
Fig. 5 is a schematic diagram of a helicopter circulation circuit layout. The compressor 6 compresses the refrigerant to be liquefied, the refrigerant is cooled and cooled by the condenser assembly 12, the refrigerant flows to the evaporator assembly 11 along the refrigerant pipeline 19, the refrigerant is gasified and absorbs heat in the evaporator assembly 11 and finally returns to the compressor 6, air in the cabin is cooled by the evaporator 11 under the action of the fan, the air is conveyed to the cabin by the helicopter ventilating duct 15 and enters the cabin through the front air outlet 17 and the rear air outlet 18, the pipeline is prevented from being rearranged, and the whole weight of the air conditioner is reduced by about 15 kg.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are merely exemplary embodiments of the present invention, and are not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (5)
1. A helicopter air conditioning refrigeration system comprising:
the soft start unit is used for controlling the working current and the rotating speed of the compressor during starting, reducing the acceleration of the working current of the compressor during starting and reducing the acceleration of the rotating speed of the compressor during starting, and comprises a first contactor, a second contactor, a control panel and a soft start module, wherein the first contactor is connected between an airborne direct-current power supply and the control panel, the second contactor and the soft start module are sequentially connected between the airborne three-phase alternating-current power supply and the compressor, and the soft start module is connected with the control panel;
the soft start module is used for acquiring state information of the compressor and sending the state information to the control panel, the control panel is used for sending a control signal according to the state information, and the soft start module drives the onboard three-phase alternating-current power supply to supply power to the compressor according to the control signal;
the state information comprises the working current and the rotating speed of the compressor;
the interlocking unit is used for controlling the air conditioner and the airborne heavy load component to work in a staggered mode;
and the circulating unit is used for arranging an air duct by utilizing the existing air supply device and ventilation duct of the helicopter to realize circulating refrigeration.
2. A helicopter air conditioning refrigeration system as set forth in claim 1 wherein said interlock unit includes a first control switch, a second control switch, a third contactor, and a fourth contactor, said third contactor being connected between said on-board dc power source and a first on-board heavy load component, said fourth contactor being connected between said on-board three-phase ac power source and a second on-board heavy load component, said first control switch being connected to said third contactor, said first contactor, and said second contactor, respectively, and said second control switch being connected to said fourth contactor, said first contactor, and said second contactor, respectively;
the airborne direct-current power supply is used for supplying power to the first control switch and the second control switch, when the first control switch controls the third contactor to be switched on, the first contactor and the second contactor are controlled to be switched off simultaneously, and when the second control switch controls the fourth contactor to be switched on, the first contactor and the second contactor are controlled to be switched off simultaneously.
3. A helicopter air conditioning refrigeration system as claimed in claim 1 or claim 2 wherein said helicopter is provided with a first fan and a second fan, said first contactor being further connected to said first fan and said second fan.
4. A helicopter air conditioning refrigeration system as claimed in claim 1, wherein said circulation unit includes an evaporator assembly, a compressor, a condenser assembly, an expansion valve, an air supply device and a ventilation duct, said evaporator assembly, said compressor, said condenser assembly and said expansion valve constitute a refrigerant circulation loop, said air supply device, said evaporator assembly and said helicopter nacelle are connected by said ventilation duct;
the compressor is used for sucking the low-temperature and low-pressure gaseous refrigerant at the outlet of the evaporator assembly and compressing the gaseous refrigerant into high-temperature and high-pressure liquid refrigerant for discharge;
the condenser assembly is used for gradually condensing the high-temperature high-pressure liquid refrigerant into a low-temperature high-pressure liquid refrigerant and discharging the dissipated heat to the external environment;
the expansion valve is used for throttling and depressurizing the low-temperature high-pressure liquid refrigerant and discharging the low-temperature high-pressure liquid refrigerant in a gas-liquid two-phase state;
the evaporator assembly is used for completely gasifying the refrigerant in a gas-liquid two-phase state to absorb heat in air, so as to form a low-temperature low-pressure gaseous refrigerant in an overheated state, and the low-temperature low-pressure gaseous refrigerant enters the compressor;
and the air supply device is used for sending the cooled air into a cabin of the helicopter for closed circulation.
5. A helicopter air conditioning refrigeration system as claimed in claim 1 wherein said onboard high load components include both lifting high power loads and lighting high power loads.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711376104.2A CN108100264B (en) | 2017-12-19 | 2017-12-19 | Helicopter air conditioner refrigerating system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711376104.2A CN108100264B (en) | 2017-12-19 | 2017-12-19 | Helicopter air conditioner refrigerating system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108100264A CN108100264A (en) | 2018-06-01 |
| CN108100264B true CN108100264B (en) | 2020-04-24 |
Family
ID=62210348
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711376104.2A Active CN108100264B (en) | 2017-12-19 | 2017-12-19 | Helicopter air conditioner refrigerating system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108100264B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109353524A (en) * | 2018-09-29 | 2019-02-19 | 北京航空航天大学 | A kind of airborne heat management system and method |
| CN109334996A (en) * | 2018-11-06 | 2019-02-15 | 西安交通大学 | One kind going straight up to machine cooling system |
| CN109625286A (en) * | 2018-12-13 | 2019-04-16 | 石家庄飞机工业有限责任公司 | A kind of Small General Aircraft condenser exhaust gas device |
| CN113251682B (en) * | 2021-06-09 | 2023-05-05 | 依米康冷元节能科技（上海）有限公司 | Double-head compressor regulation and control method, device, equipment and storage medium |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004090778A (en) * | 2002-08-30 | 2004-03-25 | Shimadzu Corp | Air conditioner for aircraft |
| US6848652B2 (en) * | 2003-02-28 | 2005-02-01 | Sikorsky Aircraft Corporation | Aircraft heater |
| CN203172639U (en) * | 2013-02-01 | 2013-09-04 | 山东朗进科技股份有限公司 | Double-source system frequency-variable locomotive air conditioner controlling device |
| US9896216B2 (en) * | 2016-06-01 | 2018-02-20 | Honeywell Limited | ECO mode ECS logic |
| CN107196490A (en) * | 2017-06-12 | 2017-09-22 | 中车青岛四方车辆研究所有限公司 | The control method of power circuit, railway vehicle air conditioner and power circuit |
-
2017
- 2017-12-19 CN CN201711376104.2A patent/CN108100264B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN108100264A (en) | 2018-06-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108100264B (en) | Helicopter air conditioner refrigerating system | |
| US9169024B2 (en) | Environmental control system with closed loop pressure cycle | |
| US10569886B2 (en) | Operating-phase-dependently controllable aircraft air conditioning system and method for operating such an aircraft air conditioning system | |
| EP2897824B1 (en) | Electrical transport refrigeration system | |
| EP1670683B8 (en) | Aircraft galley chiller system | |
| CN102627064B (en) | Vehicle self-contained refrigeration machine set | |
| CN101148197A (en) | Cabin circumstance control system used for passenger plane | |
| US9897017B2 (en) | Efficient control algorithm for start-stop operation of a refrigeration unit powered by engine | |
| CN113864052B (en) | Engine waste heat recovery system, control method, engine assembly and aircraft | |
| CN205220274U (en) | Electric automobile's motor battery temperature integrated control system | |
| CN208751067U (en) | A kind of cooling cycle system of air-conditioning and refrigeration | |
| CN104999890A (en) | Motor and battery temperature integration control system of electric automobile | |
| CN102632792A (en) | Automobile double-compressor refrigeration unit | |
| CN110481269A (en) | A kind of automobile heat pump air-conditioning system can be used for engine cooling | |
| JP2004314654A (en) | Air conditioning system for aircraft | |
| CN113195984B (en) | Device for refrigerating a locomotive | |
| CN102889643A (en) | Air conditioner used for cars and ships in ultralow temperature environment and controlling method thereof | |
| CN206243008U (en) | A kind of refrigerator car air-conditioning system with backup power supply system | |
| CN202835661U (en) | Air-condition controller for mobile machinery shop | |
| CN201819465U (en) | Metro vehicle unit-type air-conditioning unit | |
| JP2008056240A (en) | Air conditioner for aircraft | |
| CN106627326A (en) | Refrigerator car air-conditioner system provided with stand-by power system | |
| CN114312206B (en) | Electric vehicle thermal management system and electric vehicle | |
| CN209852017U (en) | Air conditioning system and vehicle | |
| CN213414256U (en) | Frequency conversion aircraft ground air-conditioning vehicle |
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 |