CN106428572A - Ventilating and cooling system and cooling method for airplane air-conditioner assembly cabin - Google Patents
Ventilating and cooling system and cooling method for airplane air-conditioner assembly cabin Download PDFInfo
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- CN106428572A CN106428572A CN201610883721.0A CN201610883721A CN106428572A CN 106428572 A CN106428572 A CN 106428572A CN 201610883721 A CN201610883721 A CN 201610883721A CN 106428572 A CN106428572 A CN 106428572A
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- 238000001816 cooling Methods 0.000 title claims abstract description 65
- 238000004378 air conditioning Methods 0.000 claims description 34
- 238000009423 ventilation Methods 0.000 claims description 21
- 238000000034 method Methods 0.000 claims description 16
- 238000012544 monitoring process Methods 0.000 claims description 14
- 238000005086 pumping Methods 0.000 claims description 8
- 238000011217 control strategy Methods 0.000 claims description 2
- 238000004891 communication Methods 0.000 claims 2
- 230000007613 environmental effect Effects 0.000 claims 2
- 238000012360 testing method Methods 0.000 abstract description 2
- 238000010276 construction Methods 0.000 description 3
- 239000000295 fuel oil Substances 0.000 description 3
- 108010066057 cabin-1 Proteins 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000004907 flux Effects 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000005057 refrigeration Methods 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 210000004243 sweat Anatomy 0.000 description 1
Classifications
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- 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
- B64D13/006—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being used to cool structural parts of the aircraft
-
- 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
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- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Air Conditioning Control Device (AREA)
Abstract
The invention provides a ventilating and cooling system and a cooling method for an airplane air-conditioner assembly cabin. The ventilating and cooling system includes a cold source air-inflow pipeline, an automatic turn-off valve, an air-inflow fan, an exhaust pipeline, a temperature sensor and a three-way valve, wherein an outlet of the cold source air-inflow pipeline is connected with an air inlet of the airplane air-conditioner assembly cabin; the automatic turn-off valve is arranged on the inlet region of the cold source air-inflow pipeline; the air-inflow fan is arranged on the cold source air-inflow pipeline and is located at the lower course of the automatic turn-off valve; an inlet of the exhaust pipeline is connected with an air outlet of the airplane air-conditioner assembly cabin; the temperature sensor is arranged in the exhaust pipeline and is used for testing the exhaust temperature in the exhaust pipeline; a first port of the three-way valve is connected with the outlet of the exhaust pipeline, a second port of the three-way valve is connected with the cold source air-inflow pipeline through a second air-inflow pipeline and a third port of the three-way valve communicates with the external environment. According to the ventilating and cooling system, the ventilating and cooling requirements of the air-conditioner assembly cabin can be met under the designed work conditions, the flight envelope is covered by every working condition and the ventilating and cooling of the airplane air-conditioner assembly cabin in the whole stage can be finished.
Description
Technical field
The present invention relates to the ventilation cooling system in civil aircraft air-conditioning assembly cabin is and in particular to civil aircraft air-conditioning assembly cabin
Cooling.
Background technology
Electronic cooling is one of civil aviation key area, and security requirement is very high.Many power technologies answer purpose
Taste increasing caloric value, and the cooling of equipment also increasingly receives publicity therewith.
Typical taking air-conditioning assembly as a example air-conditioning assembly is the topmost refrigeration unit of aircraft, and caloric value itself is greatly, empty
The heat absorption problem adjusting assembly cabin is that aircraft is urgently to be resolved hurrily.
In this regard, service aircraft is mainly processed using following several ways：First, feeder liner and narrow body main-line-aircraft
How not carry out special handling；Second, part aircraft utilization ram-air, as low-temperature receiver, is aerated cooling down using bourdon's tube；The
Three, Boeing 787 to part high-power electronic device with ram-air as low-temperature receiver, by sweat cooling and liquid are cold match by way of
Cooled down；4th, part aircraft stores to low-temperature receivers such as ram-airs in flight course, is divided with unified hybrid chamber again
Join cooling.
Wide-bodied aircraft mostly is long voyage aircraft, if air-conditioning assembly ventilating and cooling can not be handled well, the performance of assembly itself
Cannot be guaranteed, safety of structure also can have very big hidden danger, or even sky also repeatedly in the such narrow body short-haul aircraft of A320
Adjusting system overtemperature fault.Ram-air must be sucked mobile system with the third processing method by above-mentioned second, and ram-air is
One of important sources of aircraft fuel oil panelty, the fall of aircraft economy is also thought in the increase of aircraft ram-air usage amount
Low.The source of the 4th kind of low-temperature receiver air is generally ram-air or electromotor low pressure bleed, equally causes aircraft entirety fuel oil
The raising of panelty.Additionally, three kinds of methods are required for additionally increasing chiller, not only increase weight, and be not easy to
The installation in air-conditioning assembly and its cabin and maintenance.
Content of the invention
It is an object of the invention to provide a kind of cost aircraft air condition assembly cabin ventilation cooling system lower, in hgher efficiency and
Cooling means.
The principle that the present invention is recycled based on reduction aircraft fuel oil panelty and return air stream, proposes a kind of civilian winged
Ventilating and cooling method for designing under ground and aerial different conditions for the air conditioner assembly cabin, ensures low-temperature receiver using precise controlling simultaneously
Air-flow is fully utilized.Specifically in the state of ground, ventilating and cooling is realized using air conditioning system or aircraft passenger compartment air, in the air
Realize ventilating and cooling using aircraft passenger compartment air or ventilating system itself air circulation.Control aspect use temperature sensor,
The mode that valve and fan match controls shutoff and the gas feed flow rate of air-flow, realizes cold energy Optimum utilization.
According to an aspect of the present invention, there is provided a kind of aircraft air condition assembly cabin ventilation cooling system, described ventilating and cooling
System includes：
Low-temperature receiver admission line, the outlet of described low-temperature receiver admission line is connected with the air inlet in aircraft air condition assembly cabin；
Automatically shut down valve, the described valve that automatically shuts down is arranged on the entrance of described low-temperature receiver admission line；
Supply fan, described supply fan is arranged on described low-temperature receiver admission line and is located at described automatically shutting down under valve
Trip；
Discharge duct, the entrance of described discharge duct is connected with the air vent in described aircraft air condition assembly cabin；
Temperature sensor, described temperature sensor is arranged in described discharge duct and for detecting in described discharge duct
Delivery temperature；And
Tee valve, the first port of described tee valve is connected with the outlet of described discharge duct, described tee valve
Second port be connected with described low-temperature receiver admission line via the second admission line, and the 3rd port of described tee valve with
External environment connects.
In one embodiment, the arrival end of described second admission line is connected with the second port of described tee valve, and institute
State the port of export of the second admission line and junction point that described low-temperature receiver admission line is connected is located at and described automatically shuts down valve and institute
State between supply fan.
In one embodiment, described supply fan is variable-frequency fan.
In one embodiment, described ventilation cooling system also includes control device, and described control device is arranged to according to described
The temperature that temperature sensor detects or the environment according to residing for aircraft are automatically shutting down valve and described threeway described in controlling
The operation of valve.
According to a further aspect in the invention, there is provided a kind of method that aircraft air condition assembly cabin is cooled down, described side
Method comprises the following steps：
There is provided a kind of ventilation cooling system, described ventilation cooling system includes：
Low-temperature receiver admission line, the outlet of described low-temperature receiver admission line is connected with the air inlet in aircraft air condition assembly cabin；
Automatically shut down valve, the described valve that automatically shuts down is arranged on the entrance of described low-temperature receiver admission line；
Supply fan, described supply fan is arranged on described low-temperature receiver admission line and is located at described automatically shutting down under valve
Trip；
Discharge duct, the entrance of described discharge duct is connected with the air vent in described aircraft air condition assembly cabin；
Temperature sensor, described temperature sensor is arranged in described discharge duct and for detecting in described discharge duct
Delivery temperature；And
Tee valve, the first port of described tee valve is connected with the outlet of described discharge duct, described tee valve
Second port be connected with described low-temperature receiver admission line via the second admission line, and the 3rd port of described tee valve with
External environment connects；
Confirm aircraft present position；And
Low-temperature receiver is selected according to aircraft present position and takes corresponding control strategy.
In one embodiment, when aircraft is in ground, if the air themperature of aircraft pressure cabin exceedes predetermined value, use
The cold air of air-conditioning assembly turbine outlet is aerated to aircraft air condition assembly cabin cooling down as low-temperature receiver.
In one embodiment, when aircraft is in ground, if the air themperature of aircraft pressure cabin exceedes predetermined value, described
Automatically shut down valve to open, low-temperature receiver is air-conditioning assembly turbine outlet cold air, described supply fan and air-conditioning assembly are run, described temperature
Spend sensor real-time monitoring temperature, and described tee valve is opened with aerofluxuss.
In one embodiment, when aircraft is in ground, if the air themperature of aircraft pressure cabin is not less than predetermined value, profit
Use described self-acting valve, the mode adopting pumping is using aircraft pressure cabin circulation air as low-temperature receiver.
In one embodiment, when aircraft is in ground, if the air themperature of aircraft pressure cabin is not less than predetermined value, institute
State and automatically shut down valve and open, the air that low-temperature receiver meets for the temperature that pressure cabin was utilized, described supply fan runs, described
Temperature sensor real-time monitoring temperature, and described tee valve opens with aerofluxuss.
In one embodiment, when aircraft is in low latitude state, then pass through described automatically shut down valve adopt air suction mode with
The circulation air of aircraft pressure cabin is aerated to air-conditioning assembly cabin cooling down for low-temperature receiver.
In one embodiment, when aircraft is in low latitude state, the described valve that automatically shuts down is opened, and low-temperature receiver is aircraft pressure cabin
The air that the temperature being utilized meets, described supply fan and air-conditioning assembly are run, described temperature sensor real-time monitoring temperature
Spend, and described tee valve is opened with aerofluxuss.
In one embodiment, when aircraft is in the contour dummy status of cruise, realized by circulation in ventilating system for the air
The automatic cooling in air-conditioning assembly cabin.
In one embodiment, when aircraft is in the contour dummy status of cruise, the described valve that automatically shuts down is closed, described air inlet wind
Fan runs to extract described tee valve circulation air out, and described air-conditioning assembly is run, and described temperature sensor is supervised in real time
Testing temperature, and described tee valve opens for use as circulation in ventilating system for the air and according to temperature monitoring situation must
Air-out when wanting.
It is cold that the aircraft air condition assembly cabin ventilation cooling system of the present invention can meet the ventilation of air-conditioning assembly cabin under design conditions
But demand, each operating mode covers flight envelope, can complete the ventilating and cooling in full stage flight air-conditioning assembly cabin.
Brief description
Fig. 1 is the system block diagram of aircraft air condition assembly cabin according to an embodiment of the invention ventilation cooling system.
Specific embodiment
Below with reference to accompanying drawing, presently preferred embodiments of the present invention is described in detail, to become apparent from understanding the present invention's
Objects, features and advantages.It should be understood that embodiment shown in the drawings does not limit the scope of the present invention, and it is simply
The connotation of explanation technical solution of the present invention.
Fig. 1 illustrates aircraft air condition assembly cabin according to an embodiment of the invention ventilation cooling system.As shown in figure 1, aircraft
Air-conditioning assembly cabin 1 is used for accommodating aircraft air condition assembly 2.Aircraft air condition assembly cabin 1 is provided with air inlet 101 and air vent 102.Enter
QI KOU 101 is connected with the outlet of low-temperature receiver admission line 3.Air vent 102 is connected with the entrance of discharge duct 4.Low-temperature receiver admission line 3
Upstream be provided with and automatically shut down valve 7.Specifically, automatically shut down valve 7 to be arranged on the entrance 301 of low-temperature receiver admission line.
Automatically shut down valve 7 and can be selected for any suitable structure in this area and model.
There is supply fan 6 in the arranged downstream automatically shutting down valve 7 on low-temperature receiver admission line 3.It is preferred that supply fan 6
For variable-frequency fan.The rotating speed of variable-frequency fan 6 under different feedback conditions, can be controlled, thus controlling entrance cabin under different operating modes
The cold air flows of room.
Discharge duct 4 is provided with temperature sensor 8.Temperature sensor 8 is used for detecting the aerofluxuss temperature in described discharge duct
Degree.Control system can take different cooling strategies according to the temperature detected by temperature sensor 8, hereafter will furtherly
Bright.
On discharge duct, the upstream in temperature sensor is provided with tee valve 9.The first port 901 of tee valve 9 and row
The outlet of feed channel connects.The second port 902 of tee valve 9 is connected with low-temperature receiver admission line 3 via the second admission line 5.
3rd port 903 of tee valve 9 is connected with external environment.Specifically, the arrival end of the second admission line 5 and tee valve 9
Second port 902 connect, and the junction point that the port of export of the second admission line 5 is connected with low-temperature receiver admission line 3 is located at automatically
Turn off between valve 7 and supply fan 6.Here tee valve 9 can be selected for known in the art or leaved for development any suitable three
Logical valve.
In above-mentioned ventilation cooling system, the controlled refrigeration of mode that temperature sensor 8, valve 7,9 and fan combine
But the shutoff of air-flow and size, realizes making full use of of cold energy.Ensure that the air-flow meeting cooling condition (controls under precise controlling
For all cooling air-flows, can be ram-air, the cold air of assembly turbine outlet offer, other such as cargo hold, main cabin, driving
The pressure cabins such as cabin meet the air of chilling temperature demand) recycled by air return method, fully realize the economic utilization of cold energy.
The heating power protection (performance of typical case such as aircraft composite machine body) to housing construction is realized in the uninterrupted circulation of air-flow.
The method by above-mentioned ventilation cooling system, aircraft air condition assembly cabin being aerated cooling down below is described.
First, low-temperature receiver selects
1. in the state of ground
A) the very hot sky in ground, if pressure cabin air themperature is higher is unsatisfactory for low-temperature receiver condition, is gone out using air-conditioning assembly turbine
Mouth cold air is aerated to cabin cooling down as low-temperature receiver；
B) ground other situation, if pressure cabin air themperature is relatively low, meets cooling condition, using valve, using pumping
Mode using pressure cabin circulation air as low-temperature receiver；
2. in state of flight
A) low latitude state, is controlled by valve and adopts air suction mode for low-temperature receiver, cabin to be led to pressure cabin circulation air
Air cooling.Here, low latitude is commonly referred to as the height that height above sea level is less than 15000 feet.
B) cruise contour dummy status, when ambient temperature is sufficiently low, does not extract ambient atmos, by air in ventilating system
Circulation realize from cabin cooling (feasibility pass through Flow and heat flux simplation verification).Here, high-altitude is commonly referred to as sea
Lift in 15000 feet of height.
2nd, control logic
Fuel penalty calculates and raises and rise depending mainly on weight, engine bleed, ram-air and four variables of power
Height, wherein engine bleed, ram-air are particularly evident.
Control the rotating speed under different feedback conditions using variable-frequency fan, thus controlling the cold sky entering cabin under different operating modes
Throughput；Feed back delivery temperature using line temperature sensor；Using automatically shutting down valve and tee valve optimal control air-flow.
When delivery temperature relatively low (threshold value determines according to actual needs), exhaust cycle supplies, and under corresponding conditionses, fan turns
Speed reduces, and air supply source stops or reduces supply.
When delivery temperature higher (threshold value determines according to actual needs), aerofluxuss are discharged by tee valve, simultaneously fan
Rotating speed improves, and air supply source supply increases.
Specifically, running situation is as follows：
1. in the state of ground
C) the very hot sky in ground, if pressure cabin air themperature is higher is unsatisfactory for low-temperature receiver condition, is gone out using air-conditioning assembly turbine
Mouth cold air is aerated to cabin cooling down as low-temperature receiver.Now, automatically shut down valve 1 to open, low-temperature receiver goes out for air-conditioning assembly turbine
Mouth cold air, variable-frequency fan 2 runs and simultaneously determines characteristic frequency pumping on demand, and air-conditioning assembly 5 is run, and line temperature sensor 4 is real-time
Monitoring temperature, tee valve 3 is opened and is mainly used as aerofluxuss.
D) ground other situation, if pressure cabin air themperature is relatively low, meets cooling condition, using valve, using pumping
Mode using pressure cabin circulation air as low-temperature receiver.Now, automatically shut down valve 1 to open, low-temperature receiver was utilized for pressure cabin
The air that temperature meets, variable-frequency fan 2 runs and determines characteristic frequency pumping on demand, and air-conditioning assembly 5 regards its system itself to be needed
Can run and can not run, line temperature sensor 4 real-time monitoring temperature, tee valve 3 is opened and is mainly used as aerofluxuss.
2. in state of flight
C) low latitude state, is controlled by valve and adopts air suction mode for low-temperature receiver, cabin to be led to pressure cabin circulation air
Air cooling.Now, automatically shut down valve 1 to open, the air that low-temperature receiver meets for the temperature that pressure cabin was utilized, variable-frequency fan 2
Run and determine characteristic frequency pumping on demand, air-conditioning assembly 5 is run and met aircraft needs, line temperature sensor 4 real-time monitoring
Temperature, tee valve 3 is opened and is mainly used as aerofluxuss.
D) cruise contour dummy status, when ambient temperature is sufficiently low, does not extract ambient atmos, by air in ventilating system
Circulation realize from cabin cooling (feasibility pass through Flow and heat flux simplation verification).Now, automatically shut down valve 1 to close
Close, low-temperature receiver that need not be special supplies, variable-frequency fan 2 runs and simultaneously determines characteristic frequency pumping main extraction tee valve on demand out
Circulation air, air-conditioning assembly 5 run meet aircraft needs, line temperature sensor 4 real-time monitoring temperature, tee valve 3 dozens
Open and be mainly used as circulation in ventilating system for the air the temperature monitoring situation air-out if necessary according to 4.
The aircraft air condition assembly cabin ventilation cooling system of the present invention is based on the reason reducing fuel penalty and precise controlling
Read, low-temperature receiver optimized choice and control logic combined closely, air-conditioning assembly cabin ventilating and cooling demand can be met under design conditions,
Each operating mode covers flight envelope, can complete the ventilating and cooling in full stage flight air-conditioning assembly cabin.In terms of low-temperature receiver selection, ground
Very hot sky is used air-conditioning assembly turbine outlet cold air or pressure cabin circulation air as cold according to the height of pressure cabin air themperature
Source is aerated to cabin cooling down；Low latitude state, is controlled by valve and adopts air suction mode with pressure cabin circulation air as low-temperature receiver
Cabin is aerated cool down；When high dummy status ambient temperature is sufficiently low, do not extract ambient atmos, by air in ventilating system
In circulation realize from cabin cooling.In terms of control logic, based on air-conditioned cabin inner boundary cold air interlayer protective measure, propose to supply
The Precise control method of temperature degree, makes full use of the cooling capacity of supply, thus reducing energy consumption improves economy.Additionally, it is cold
But the circulating current in assembly cabin takes nacelle heat out of, can be additionally used in housing construction heat supply when aircaft configuration temperature is too low, plays
The effect (composite effect is especially apparent) of protection housing construction.
Below described presently preferred embodiments of the present invention in detail, it is understood that saying having read the above-mentioned of the present invention
After awarding content, those skilled in the art can make various changes or modifications to the present invention.These equivalent form of values equally fall within this
Application appended claims limited range.
Claims (13)
1. a kind of aircraft air condition assembly cabin ventilation cooling system is it is characterised in that described ventilation cooling system includes：
Low-temperature receiver admission line, the outlet of described low-temperature receiver admission line is connected with the air inlet in aircraft air condition assembly cabin；
Automatically shut down valve, the described valve that automatically shuts down is arranged on the entrance of described low-temperature receiver admission line；
Supply fan, described supply fan is arranged on described low-temperature receiver admission line and automatically shuts down valve downstream positioned at described；
Discharge duct, the entrance of described discharge duct is connected with the air vent in described aircraft air condition assembly cabin；
Temperature sensor, described temperature sensor is arranged in described discharge duct the aerofluxuss for detecting in described discharge duct
Temperature；And
Tee valve, the first port of described tee valve is connected with the outlet of described discharge duct, and the of described tee valve
Two-port netwerk is connected with described low-temperature receiver admission line via the second admission line, and the 3rd port of described tee valve and the external world
Environmental communication.
2. aircraft air condition assembly cabin ventilation cooling system according to claim 1 is it is characterised in that described second air inlet pipe
The arrival end in road is connected with the second port of described tee valve, and the port of export of described second admission line and described low-temperature receiver enter
The junction point that feed channel connects is located at described automatically shutting down between valve and described supply fan.
3. aircraft air condition assembly cabin ventilation cooling system according to claim 1 is it is characterised in that described supply fan is
Variable-frequency fan.
4. aircraft air condition assembly cabin ventilation cooling system according to claim 1 is it is characterised in that described ventilating and cooling system
System also includes control device, and described control device is arranged to the temperature detecting according to described temperature sensor or according to aircraft
Residing environment is automatically shutting down valve and the operation of described tee valve described in controlling.
5. a kind of method that aircraft air condition assembly cabin is cooled down is it is characterised in that the method comprising the steps of：
There is provided a kind of ventilation cooling system, described ventilation cooling system includes：
Low-temperature receiver admission line, the outlet of described low-temperature receiver admission line is connected with the air inlet in aircraft air condition assembly cabin；
Automatically shut down valve, the described valve that automatically shuts down is arranged on the entrance of described low-temperature receiver admission line；
Supply fan, described supply fan is arranged on described low-temperature receiver admission line and automatically shuts down valve downstream positioned at described；
Discharge duct, the entrance of described discharge duct is connected with the air vent in described aircraft air condition assembly cabin；
Temperature sensor, described temperature sensor is arranged in described discharge duct the aerofluxuss for detecting in described discharge duct
Temperature；And
Tee valve, the first port of described tee valve is connected with the outlet of described discharge duct, and the of described tee valve
Two-port netwerk is connected with described low-temperature receiver admission line via the second admission line, and the 3rd port of described tee valve and the external world
Environmental communication；
Confirm aircraft present position；And
Low-temperature receiver is selected according to aircraft present position and takes corresponding control strategy.
6. method according to claim 5 is it is characterised in that when aircraft is in ground, if the sky of aircraft pressure cabin
Temperature degree exceedes predetermined value, then be used the cold air of air-conditioning assembly turbine outlet as low-temperature receiver, aircraft air condition assembly cabin to be aerated
Cooling.
7. method according to claim 5 is it is characterised in that when aircraft is in ground, if the sky of aircraft pressure cabin
Temperature degree exceedes predetermined value, then the described valve that automatically shuts down is opened, and low-temperature receiver is air-conditioning assembly turbine outlet cold air, described air inlet wind
Fan and air-conditioning assembly are run, described temperature sensor real-time monitoring temperature, and described tee valve is opened with aerofluxuss.
8. method according to claim 5 is it is characterised in that when aircraft is in ground, if the sky of aircraft pressure cabin
Temperature degree not less than predetermined value, then utilizes described self-acting valve, adopt the mode of pumping using aircraft pressure cabin circulation air as
Low-temperature receiver.
9. method according to claim 5 is it is characterised in that when aircraft is in ground, if the sky of aircraft pressure cabin
Temperature degree is opened not less than predetermined value, the then described valve that automatically shuts down, the sky that low-temperature receiver meets for the temperature that pressure cabin was utilized
Gas, described supply fan runs, described temperature sensor real-time monitoring temperature, and described tee valve is opened with aerofluxuss.
10. method according to claim 5 is it is characterised in that when aircraft is in low latitude state, then pass through described automatic
Turning off valve adopts air suction mode air-conditioning assembly cabin to be aerated cool down with the circulation air of aircraft pressure cabin for low-temperature receiver.
11. methods according to claim 5 it is characterised in that when aircraft is in low latitude state, described automatically shut down work
Door is opened, the air that low-temperature receiver meets for the temperature that aircraft pressure cabin was utilized, and described supply fan and air-conditioning assembly are run, institute
State temperature sensor real-time monitoring temperature, and described tee valve is opened with aerofluxuss.
12. methods according to claim 5 it is characterised in that when aircraft be in cruise contour dummy status when, by air
The automatic cooling in air-conditioning assembly cabin is realized in circulation in ventilating system.
13. methods according to claim 5 it is characterised in that when aircraft is in the contour dummy status of cruise, described automatically
Turn off valve to close, described supply fan runs to extract described tee valve circulation air out, described air-conditioning assembly fortune
OK, described temperature sensor real-time monitoring temperature, and described tee valve opens the following in ventilating system for use as air
Ring according to temperature monitoring situation air-out when necessary.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610883721.0A CN106428572A (en) | 2016-10-10 | 2016-10-10 | Ventilating and cooling system and cooling method for airplane air-conditioner assembly cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610883721.0A CN106428572A (en) | 2016-10-10 | 2016-10-10 | Ventilating and cooling system and cooling method for airplane air-conditioner assembly cabin |
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| CN106428572A true CN106428572A (en) | 2017-02-22 |
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| CN201610883721.0A Pending CN106428572A (en) | 2016-10-10 | 2016-10-10 | Ventilating and cooling system and cooling method for airplane air-conditioner assembly cabin |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107357181A (en) * | 2017-07-31 | 2017-11-17 | 中国航空工业集团公司西安飞机设计研究所 | Electronic equipment air vent mode control system and method on a kind of machine |
| CN109292097A (en) * | 2018-09-21 | 2019-02-01 | 中国商用飞机有限责任公司 | Aircraft air condition flow control system |
| CN109334995A (en) * | 2018-11-15 | 2019-02-15 | 中国直升机设计研究所 | A kind of helicopter frequency conversion electric drive vapor cycle refrigeration 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 |
| CN112429244A (en) * | 2020-11-03 | 2021-03-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Heat comprehensive utilization system |
| CN112492846A (en) * | 2020-11-27 | 2021-03-12 | 中国商用飞机有限责任公司 | Aircraft electronic equipment cabin ventilation system |
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| CN107357181A (en) * | 2017-07-31 | 2017-11-17 | 中国航空工业集团公司西安飞机设计研究所 | Electronic equipment air vent mode control system and method on a kind of machine |
| CN109292097A (en) * | 2018-09-21 | 2019-02-01 | 中国商用飞机有限责任公司 | Aircraft air condition flow control system |
| CN109292097B (en) * | 2018-09-21 | 2021-09-07 | 中国商用飞机有限责任公司 | Flow control system of airplane air conditioner |
| CN109334995A (en) * | 2018-11-15 | 2019-02-15 | 中国直升机设计研究所 | A kind of helicopter frequency conversion electric drive vapor cycle refrigeration system |
| CN109334995B (en) * | 2018-11-15 | 2020-05-12 | 中国直升机设计研究所 | Helicopter frequency conversion electric drive evaporation circulation refrigerating 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 |
| CN112429244A (en) * | 2020-11-03 | 2021-03-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Heat comprehensive utilization system |
| CN112429244B (en) * | 2020-11-03 | 2023-08-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Heat comprehensive utilization system |
| CN112492846A (en) * | 2020-11-27 | 2021-03-12 | 中国商用飞机有限责任公司 | Aircraft electronic equipment cabin ventilation system |
| CN112492846B (en) * | 2020-11-27 | 2021-12-10 | 中国商用飞机有限责任公司 | Aircraft electronic equipment cabin ventilation system |
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