CN104260891B - A kind of method and system for air heat aircraft hold - Google Patents
A kind of method and system for air heat aircraft hold Download PDFInfo
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- CN104260891B CN104260891B CN201410489696.9A CN201410489696A CN104260891B CN 104260891 B CN104260891 B CN 104260891B CN 201410489696 A CN201410489696 A CN 201410489696A CN 104260891 B CN104260891 B CN 104260891B
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- 238000000034 method Methods 0.000 title description 9
- 238000010438 heat treatment Methods 0.000 claims abstract description 48
- 230000002093 peripheral effect Effects 0.000 claims abstract description 7
- 238000009423 ventilation Methods 0.000 claims description 27
- 238000004378 air conditioning Methods 0.000 claims description 6
- 230000005855 radiation Effects 0.000 claims description 6
- 238000011144 upstream manufacturing Methods 0.000 claims description 3
- 230000017525 heat dissipation Effects 0.000 description 5
- 239000000446 fuel Substances 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 239000010410 layer Substances 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 238000010304 firing Methods 0.000 description 2
- 239000000295 fuel oil Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000009413 insulation Methods 0.000 description 2
- 241000521257 Hydrops Species 0.000 description 1
- 206010030113 Oedema Diseases 0.000 description 1
- 230000003187 abdominal effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 210000000744 eyelid Anatomy 0.000 description 1
- 239000011229 interlayer Substances 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 239000003921 oil Substances 0.000 description 1
- 238000013517 stratification Methods 0.000 description 1
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- Air-Conditioning For Vehicles (AREA)
Abstract
The invention provides a kind of system for air heat aircraft hold, described system includes: the first temperature sensor, and it is for detecting the temperature in cargo hold；Heated fan；Heat exchanger；Draught fan；Heating element heater, it is arranged on cargo deck bottom；And controller, it is for determining the rotating speed of described heated fan when the temperature in described cargo hold is less than desired temperature and starts described heated fan；Wherein, hot-air is passed through the hot limit of described heat exchanger by described heated fan, with the heating air from cargo hold and cargo hold peripheral region through the cold limit of described heat exchanger, to produce the vent air of warm cargo；And wherein, hot-air through the hot limit of described heat exchanger is assigned to described tank top via described heating element heater, so that described tank top is heated, and the vent air of described warm cargo is assigned in described cargo hold via described draught fan, so that described cargo hold is heated.
Description
Technical field
The present invention relates to a kind of method and device for air heat aircraft hold.
Background technology
Owing to commercial aircraft operation scope is wide, using environment special, external environment condition changes greatly,
Aircraft is under cruising condition, under the temperature in cargo hold can be along with drastically reducing of ambient temperature
Fall.Normal cruise under state, the atmospheric temperature of aircraft exterior between-30 DEG C to-70 DEG C, by
In cargo compartment without heat-producing device and biology, if cargo hold not being aerated and heating, aircraft
The temperature of goods can be reduced to less than 0 DEG C, and to transport being in aircraft hold, being is by nothing
Method tolerates such low temperature for a long time.Therefore, when aircraft has the requirement transporting being, all
Aircraft hold can be aerated heating.
At present, the cargo space ventilation heating of most of aircrafts uses electric heater to enter vent air
Row heating, or with the high-temperature hot air from APU, electromotor, vent air is joined
Flat heating.But either electric heater, or high-temperature hot trim air, the most all by conversion
For the fuel oil consumption of aircraft, increase the Financial cost of aircraft hold heating.
Additionally, substantial amounts of luggage or goods, these luggage and goods would generally be filled in aircraft hold
Thing occupies the most of spaces in cargo hold.When therefore cargo space ventilation air being heated, due to
Vent air can be stopped by goods, cut off, and is difficult in cargo hold circulation.Further, by
In tank top stack goods, tank top cannot be heated.Therefore, current aircraft goods
The mode of cabin air heat, it is impossible to heating tank top, cargo space ventilation heats is easy
Being affected by cargo hold built-in loading thing, cargo compartment temperature is difficult to control to, and the temperature in cargo hold is equal
Even property is the most excessively poor.
Fig. 1 shows the cross-sectional view of aircraft hold.As it is shown in figure 1, cargo hold top is visitor
Bottom, floor, cabin interlayer, cargo hold both sides are cargo hold trigonums, and cargo hold trigonum communicates with main cabin,
Outside air in main cabin is via discharge cabin, cargo hold trigonum.Cargo hold trigonum is near eyelid covering
Side is equipped with adiabatic sound insulating layer.Therefore, in the air themperature of cargo hold trigonum and main cabin
Air themperature is closely.
Additionally, tank top is near the abdominal part of aircraft as shown in Figure 1, owing to spreading bottom aircraft
If during heat insulation layer, owing to easy hydrops makes moist, corroded, bottom aircraft hold the most not
Lay adiabatic sound insulating layer.On the other hand, non-due to the hardware heat conductivity of tank top
Chang Hao, therefore, the temperature bottom aircraft hold is the lowest under cruising condition, aircraft hold
Bottom is the region that cargo hold UA value (being used for calculating heat dissipation capacity and thermal force) is maximum.Therefore,
Tank top account for the overwhelming majority of aircraft hold heat dissipation capacity, and tank top is also aircraft cruise
The region that under state, temperature is minimum.
So, when cargo hold is heated, if tank top heat dissipation capacity can be reduced, so that it may significantly carry
The air heat efficiency of high cargo hold, improves the thermal stratification that cargo hold inner top is warm, bottom is cold existing
As, it is also possible to overcome directly to the inefficient shortcoming of cargo hold blowing air.
At present, what the heating of aircarrier aircraft cargo hold used is all the side to the heating of cargo space ventilation air
Formula.Some aircrafts are to install heater additional, to cargo space ventilation at the arrival end of cargo space ventilation pipeline
Air heats；Some aircrafts are that the vent air to cargo hold carries out hot trim.Both
Mode needs to consume the electric energy of aircraft or the hot trim air from electromotor, between the most all
Ground connection increases the fuel consumption of aircraft.It addition, both cargo hold mode of heatings are all by cargo hold
The internal impact loading goods, vent air circulation is not smooth, and the efficiency of heating surface of cargo hold is low, goods
Bilge portion heat dissipation capacity is big, poor temperature uniformity in cargo hold.
Summary of the invention
Consider based on above-mentioned, present invention aim at providing a kind of and use on commercial aircraft,
Improve the draft type of the cargo hold efficiency of heating surface.Meanwhile, also need to reduce cargo space ventilation heating process
Using and the use of hot trim air of middle heater, reduces the fuel consumption of aircraft, rises
To improving cargo hold heats and reducing the double effects that aircraft fuel oil consumes.
It is proposed to this end that a kind of system for air heat aircraft hold, described system includes:
First temperature sensor, it is for detecting the temperature in cargo hold；Heated fan；Heat exchanger；Logical
Wind fan；Heating element heater, it is arranged on cargo deck bottom；And controller, it is for working as
Determine the rotating speed of described heated fan and open when temperature in described cargo hold is less than desired temperature
Dynamic described heated fan；Wherein, hot-air is passed through the heat of described heat exchanger by described heated fan
Limit, with the heating sky from cargo hold and cargo hold peripheral region through the cold limit of described heat exchanger
Gas, to produce cargo space ventilation air；And wherein, the heat through the hot limit of described heat exchanger is empty
Gas is assigned to described tank top via described heating element heater, to carry out described tank top
Heat, and the vent air of the described cargo hold of described heating is assigned to via described draught fan
In described cargo hold, so that described cargo hold is heated.
Preferably, described system also includes the second temperature sensor, and it is used for detecting described heat exchange
The temperature of the hot-air on the hot limit of device, and described controller is additionally operable to according to described heat exchanger
Temperature in the temperature of the hot-air on hot limit and described cargo hold determines the rotating speed of described heated fan.
Preferably, described first temperature sensor and/or described second temperature sensor are air-conditioning systems
System parts.
Preferably, described system also includes valve, and it is positioned at the upstream of described heated fan, and
And described controller is additionally operable to when the temperature in described cargo hold is less than desired temperature to open described
Valve, to allow the hot-air on the hot limit of described heat exchanger to be passed through described heated fan.
Preferably, described controller is additionally operable to when the temperature in described cargo hold sets higher than described temperature
Close described valve and described heated fan during definite value, and the heat on the hot limit of described heat exchanger is empty
Gas is immediately discharged exhaust valve via discharge duct, or stops providing described hot-air.Such as
Close firing equipment.
Preferably, the hot-air on the described exchanger heat limit after described tank top being heated
It is discharged to described exhaust valve.
Preferably, described draught fan, described heating element heater and described discharge duct are that aircraft is empty
Adjusting system parts.
Preferably, described heating element heater include following at least one: flute type pipe, ventilation slot,
And possess the cargo deck of air heat function.
Preferably, the hot-air entering exchanger heat limit after heated fan can be from electricity
The heat radiation air in subset cabin, or via the hot-air obtained after the heating of other firing equipments, or
Hot-air from other high temperature heat sources of gas such as APU, electromotor.
Cargo hold can be improved by the present invention and add the gentle air heat mode transporting being, effectively
Improve the draft type that cruising phase temperature in cargo hold is on the low side, solve that cargo hold heats is poor, fire
The shortcoming that oil consumption is big.
Specifically, by the cargo space ventilation heating system of the method design according to the present invention, permissible
Reduce heater or the use of trim hot-air, make full use of the heat radiation air of electronic equipment or logical
Cross the hot-air that other thermals source obtain, increase the fuel economy of aircraft.Meanwhile, the present invention can
(the most logical to make up the deficiency separately through the air heating systems to cargo compartment conveying hot-air
Wind air is easily affected by the internal goods that loads, and ventilates the most smooth, it is impossible to carry out tank top
Heating, the efficiency of heating surface is low), improve the heating drafting efficiency of cargo hold.
Further, the hot-air in the present invention can come from the electronic equipment dissipating heat of interior of aircraft
Air.Under normal circumstances, the ventilation and heat air of electronics bay completes electronic equipment
After cooling channel, aircraft exterior will be discharged to by discharge duct and valve, this of electronic equipment
Partial heat energy will be wasted, and the cargo space ventilation heating system in the present invention can effective land productivity
The heat energy discharged with electronic equipment dissipating heat, improves the energy utilization rate of aircraft, indirectly drops
The fuel consumption of low aircraft.
Various aspects of the invention are more clear by the explanation by embodiment in detail below
Clear.
Accompanying drawing explanation
By reading retouching in detail with reference to made non-limiting example is made of the following drawings
Stating, the other features, objects and advantages of the present invention will become more apparent:
Fig. 1 shows the cross-sectional view of aircraft hold；
Fig. 2 shows according to an embodiment of the invention for air heat aircraft hold
The schematic diagram of system；
Fig. 3 shows heating element heater according to an embodiment of the invention；And
Fig. 4 shows heating element heater according to another embodiment of the invention.
In the drawings, running through different diagrams, same or similar reference represents identical or phase
Corresponding parts or feature.
Detailed description of the invention
Fig. 2 shows according to an embodiment of the invention for air heat aircraft hold
The schematic diagram of system.
As in figure 2 it is shown, the temperature sensor 2 being arranged in cargo hold detects the temperature in cargo hold
When degree is less than desired temperature, control unit 3 is according to the temperature in this cargo hold and temperature sensing
The temperature of the hot-air 15 that device 4 records, opens valve 17, and determines heated fan 5
Rotating speed, and start heated fan 5, by hot-air 15 input heat exchanger 6.
Preferably, hot-air 15 is the heat radiation air from electronics bay.Can certainly
It is the hot-air through heater heating, or from APU, the hot-air of electromotor.
Preferably, for detecting the temperature sensor 2 of cargo compartment temperature and setting for detecting electronics
The temperature sensor 4 of the hot air temperature in standby cabin is air conditioning system components.
Referring now still to Fig. 2, hot-air 15 enters the hot limit (in the horizontal direction) of heat exchanger 6,
And from cargo hold peripheral region 11 and the inside of cargo hold 16 air enter heat exchanger 6 cold
Limit (vertically).Here, use the hot-air 15 on hot limit right by heat exchanger 6
The above-mentioned air from cargo hold peripheral region 11 and the inside of cargo hold 16 on cold limit adds
Heat, to produce cargo space ventilation air 18.
Subsequently, the cargo space ventilation air 18 after heat exchanger 6 heats is vented 1 point of fan
It is assigned to cargo hold 16 internal.And the hot-air 15 after heat exchanger 6 is via being arranged on cargo hold
The heating element heater 7 of bottom, floor 13 is assigned to tank top, to poor thermal insulation property, heat radiation
Measure high cargo deck 13 to heat.Preferably, this heating element heater 7 can be flute type pipe,
Ventilation slot and possess the cargo deck of air heat function.
Then, this part hot-air 15 via discharge duct 8 and is arranged on aircraft skin 12
On exhaust valve 10 be discharged to aircraft exterior.
Preferably, said fans, discharge duct are aircraft air-conditioning system parts.
And when said system is closed, such as, detect that cargo hold 16 is internal when temperature sensor 2
When air themperature is higher than setting value, control unit 3 will send signal, close fan 5 and live
Door 17, stops heating cargo space ventilation air 18 and cargo deck 13, only by
Cargo hold is aerated by draught fan 1.Here, cargo space ventilation fan 1 will be from cargo hold 16
Cargo hold is led to by internal and cargo hold peripheral region 11 air again by air distribution duct 14
It is internal that wind air is delivered to cargo hold 16.
Fig. 3 shows heating element heater according to an embodiment of the invention.Fig. 4 shows
Heating element heater according to another embodiment of the invention.Fig. 3 shows flute type pipe.Fig. 4
Show ventilation slot.Here, flute type pipe may be mounted at tank top, with warm cargo ground
Plate.Alternatively, it is also possible to integrated installation ventilation slot in cargo deck.Preferably, above-mentioned
Flute type pipe, ventilation slot are aircraft air-conditioning system parts.
Therefore, the air distribution system according to the present invention can also be empty for tank top conveying heat
Gas.The cargo compartment temperature that this system can detect according to cargo compartment temperature sensor,
And the temperature in cargo hold and the difference of design temperature, start cargo space ventilation heating system in real time,
More efficiently cargo hold is heated.
Hereafter will be described the method for cargo space ventilation mode of heating, the method includes as follows
Step (skilled artisan would appreciate that some step of following method there is no priority
Point):
1) mounting temperature sensor in cargo hold, for detecting the temperature in cargo hold for controlling
Unit provides the real-time monitoring of cargo compartment temperature.When cargo compartment temperature is less than desired temperature, control
The temperature of the hot-air (aerofluxus) that unit processed records according to another temperature sensor, determines and adds
The rotating speed of Hot-air fan, and start heated fan, thus by the hot limit of hot-air input heat exchanger.
By in the cold limit of the hot-air heat exchanger in the hot limit of heat exchanger from cargo hold peripheral region
The cargo space ventilation air of the inside of territory and cargo hold heats.Goods after heat exchanger heats
Cabin vent air is vented fan and distributes to cargo hold.
2) installing heat exchanger on cargo space ventilation pipeline, this heat exchanger is for from cargo hold week
The air of the inside enclosing region and cargo hold heats, when the temperature sensor in cargo hold detects
When the temperature arrived is less than setting value, control unit starts heated fan, is passed through by hot-air and changes
The hot limit of hot device.
3) rotating speed of heated fan is recorded by the temperature sensor being arranged on heated fan upstream
Temperature and the cargo hold thermal force determined in cargo compartment temperature of hot-air determine.
4) the flute type pipe on warm cargo floor is installed at tank top, or in cargo deck
Integrated installation ventilation slot, the hot-air through exchanger heat limit via these flute type pipes, ventilation slot,
Or other possesses the cargo deck of air heat function, warm cargo floor, indirectly reduce goods
The heat dissipation capacity in bilge portion.
5) air after heating tank top is via tank top and the row at cargo hold rear portion
Gas valve is discharged to aircraft exterior.
6) when cargo hold heating function is closed, the heat radiation air of electronics bay leads to
Cross special discharge duct to drain near aircrafts exhaust valve, be then discharged to aircraft exterior.Replace
Dai Di, can close hot-air thermal source, stops providing hot-air.
It should be noted that above-described embodiment is only exemplary, rather than the limit to the present invention
System.Any technical scheme without departing substantially from spirit of the present invention all should fall into protection scope of the present invention
Within, this includes using the different technologies feature occurred in different embodiments, and method is permissible
It is combined, to obtain beneficial effect.
Claims (9)
1., for a system for air heat aircraft hold, described system includes:
First temperature sensor, it is for detecting the temperature in cargo hold；
Heated fan；
Heat exchanger；
Draught fan；
Heating element heater, it is arranged on cargo deck bottom；And
Controller, it is described for determining when the temperature in described cargo hold is less than desired temperature
The rotating speed of heated fan and start described heated fan；
Wherein, hot-air is passed through the hot limit of described heat exchanger by described heated fan, to heat warp
Cross the air from cargo hold and cargo hold peripheral region on the cold limit of described heat exchanger, add to produce
The vent air of the described cargo hold of heat；
And wherein, the hot-air through the hot limit of described heat exchanger is via described heating element heater quilt
Distribution is to described tank top, so that described tank top is heated, and described heating institute
The vent air stating cargo hold is assigned in described cargo hold via described draught fan, with to described
Cargo hold heats.
System the most according to claim 1, it is characterised in that described system also includes
Two temperature sensors, it is for detecting the temperature of the hot-air on the hot limit of described heat exchanger, and
Described controller is additionally operable to the temperature of the hot-air on the hot limit according to described heat exchanger and described cargo hold
Interior temperature determines the rotating speed of described heated fan.
System the most according to claim 2, it is characterised in that described first temperature sensing
Device and/or described second temperature sensor are air conditioning system components.
System the most according to claim 1, it is characterised in that described system also includes living
Door, it is positioned at the upstream of described heated fan, and described controller is additionally operable to when described cargo hold
Described valve is opened, to allow the hot limit of described heat exchanger when interior temperature is less than desired temperature
Hot-air be passed through described heated fan.
System the most according to claim 4, it is characterised in that described controller is additionally operable to
Described valve and described heating is closed when the temperature in described cargo hold is higher than described desired temperature
Fan, and the hot-air on the hot limit of described heat exchanger is immediately discharged aerofluxus via discharge duct
Valve, or stop providing described hot-air.
System the most according to claim 5, it is characterised in that described tank top is entered
The hot-air on the hot limit of the heat exchanger after row heating is discharged to described exhaust valve.
System the most according to claim 6, it is characterised in that described draught fan, institute
State heating element heater and described discharge duct is aircraft air-conditioning system parts.
System the most according to claim 1, it is characterised in that described heating element heater includes
At least one in below: flute type pipe, ventilation slot and possess the cargo hold of air heat function
Floor.
System the most according to claim 1, it is characterised in that described hot-air be from
The heat radiation air of electronics bay.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410489696.9A CN104260891B (en) | 2014-09-23 | 2014-09-23 | A kind of method and system for air heat aircraft hold |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410489696.9A CN104260891B (en) | 2014-09-23 | 2014-09-23 | A kind of method and system for air heat aircraft hold |
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| Publication Number | Publication Date |
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| CN104260891A CN104260891A (en) | 2015-01-07 |
| CN104260891B true CN104260891B (en) | 2016-08-24 |
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| CN201410489696.9A Active CN104260891B (en) | 2014-09-23 | 2014-09-23 | A kind of method and system for air heat aircraft hold |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| DE102015203170B4 (en) * | 2015-02-23 | 2021-09-09 | Airbus Operations Gmbh | Method and system for controlling an air conditioning system for air conditioning an aircraft hold |
| JP6516547B2 (en) * | 2015-04-27 | 2019-05-22 | 三菱航空機株式会社 | Duct structure and aircraft exhausted through a pressure control valve |
| CN105181359B (en) * | 2015-07-17 | 2018-03-20 | 中车青岛四方机车车辆股份有限公司 | Equipment compartment high-temperature test device and test method under a kind of EMUs car |
| CN106005429A (en) * | 2016-06-01 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Centralized type cabin temperature regulating system |
| CN107505123A (en) * | 2016-06-14 | 2017-12-22 | 武汉铁盾民防工程有限公司 | A kind of overpressure exhaust valve detection device |
| CN106428572A (en) * | 2016-10-10 | 2017-02-22 | 中国商用飞机有限责任公司 | Ventilating and cooling system and cooling method for airplane air-conditioner assembly cabin |
| CN106364663B (en) * | 2016-10-18 | 2018-08-24 | 中国商用飞机有限责任公司 | Aircraft air condition component cabin |
| DE102017105871A1 (en) * | 2017-03-20 | 2018-09-20 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Cabin air inlet module and cabin air system |
| CN107813940B (en) * | 2017-10-31 | 2020-11-24 | 中国商用飞机有限责任公司 | Aircraft electronic equipment cabin exhaust apparatus |
| CN107963198A (en) * | 2017-12-26 | 2018-04-27 | 陶文英 | Shipping unmanned aerial vehicle body construction design method and its structure |
| 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 |
| CN111244576A (en) * | 2018-11-29 | 2020-06-05 | 华为终端有限公司 | Electronic equipment and battery heating control method thereof |
| CN111516882B (en) * | 2020-05-14 | 2022-03-22 | 中国商用飞机有限责任公司 | Heating and ventilating system of aircraft cabin |
| CN113879543B (en) * | 2021-11-23 | 2024-05-14 | 中国商用飞机有限责任公司 | Aircraft ventilation system and aircraft comprising same |
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| CN104260891A (en) | 2015-01-07 |
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Address after: 1919 Expo Avenue, Pudong New Area, Shanghai, 200126 Patentee after: COMMERCIAL AIRCRAFT CORPORATION OF CHINA, Ltd. Patentee after: COMAC SHANGHAI AIRCRAFT DESIGN & Research Institute Address before: No.25, Zhangyang Road, Pudong New Area, Shanghai, 200120 Patentee before: COMMERCIAL AIRCRAFT CORPORATION OF CHINA, Ltd. Patentee before: COMAC SHANGHAI AIRCRAFT DESIGN & Research Institute |
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Effective date of registration: 20220927 Address after: 1919 Expo Avenue, Pudong New Area, Shanghai, 200126 Patentee after: COMMERCIAL AIRCRAFT CORPORATION OF CHINA, Ltd. Patentee after: Shanghai Aircraft Design Research Institute Co.,Ltd. Address before: 1919 Expo Avenue, Pudong New Area, Shanghai, 200126 Patentee before: COMMERCIAL AIRCRAFT CORPORATION OF CHINA, Ltd. Patentee before: COMAC SHANGHAI AIRCRAFT DESIGN & Research Institute |
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