CN103723276A - Electronic equipment ventilation cooling system based on Y7 aircraft environment control system - Google Patents
Electronic equipment ventilation cooling system based on Y7 aircraft environment control system Download PDFInfo
- Publication number
- CN103723276A CN103723276A CN201310648508.8A CN201310648508A CN103723276A CN 103723276 A CN103723276 A CN 103723276A CN 201310648508 A CN201310648508 A CN 201310648508A CN 103723276 A CN103723276 A CN 103723276A
- Authority
- CN
- China
- Prior art keywords
- air
- ventilation cooling
- aircraft
- cooling system
- electronic equipment
- 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.)
- Pending
Links
Images
Abstract
The invention belongs to the cooling technology of airborne electronic equipment and particularly relates to an electronic equipment ventilation cooling system based on an Y7 aircraft environment control system. The electronic equipment ventilation cooling system based on the Y7 aircraft environment control system comprises an original aircraft air conditioning system and an air introduction pipeline. The original air conditioning system comprises a left air conditioning system and a right air conditioning system, the air introduction pipeline replaces an upper air duct of the original aircraft air conditioning system, one end of the air introduction pipeline is communicated with the upper air duct on the left side through a transfer valve, and the other end of the air introduction pipeline is connected with electronic equipment to be cooled. The ventilation cooling system does not affect air safety and can meet the requirements of the GJB2882<general specification for ventilation cooling system of airborne electronic equipment>. The change of the carrier aircraft aerodynamic shape is not involved, loads of an engine and a power system are not increased, the gained weight of refitted items can be almost ignored, and platform performance compensation losses caused by ram air introduction refitting or additional fitting of a large-scale centrifugal ventilator are avoided. The noise level of a passenger cabin is not increased, which helps to improve the working environment for people taking part in a test.
Description
Technical field
The invention belongs to air environment cooling technology, be specifically related to a kind of electronic machine ventilation cooling system based on Y7 aircraft environmental control system.
Background technology
Domestic Y7(fortune seven) aircraft is with its safety, and economic feature is widely used as the flight test platform of various task systems.The air environment of task system often needs forced ventilation cooling, general employing drawn the technical implementation way of getting extraneous ram air or installing ventilating set additional, but for the electronic machine being arranged in aircraft supercharging sealed module, cannot adopt ram air to carry out cooling, can only carry out forced ventilation with ventilating set cooling, in use there are problems in this method: the pressure head that small-sized ventilating set can provide is less, is difficult to meet vent flow requirement, and cooling performance is poor; Large centrifugal ventilating set volume and weight is large, power consumption is large, and the compensatory loss of carrier aircraft performance is large; To test personnel's working environment, there is serious noise pollution in ventilating set.
Summary of the invention
The object of the invention is: a kind of electronic machine ventilation cooling system based on Y7 aircraft environmental control system is provided, and this system ventilation flow is large, good cooling results, can carry out effective cooling to the electronic machine in aircraft supercharging sealed module.
Technical solution of the present invention is:
A kind of electronic machine ventilation cooling system based on Y7 aircraft environmental control system, it comprises former air conditioner system, bleed air line, wherein, former a/c system comprises left and right a/c system, bleed air line is replaced the left a/c system upper air duct of former machine, and one end is communicated with left side upper air duct through changeover valve, and the other end connects electronic machine to be cooled.
Described bleed breather pipe adopts thin-walled rustproof aluminum alloy pipe manufacturer, and catheter end head adopts HB4-110 roll wave version.
One end of bleed air line connecting electronic equipment is provided with tap hole.
Left and right is provided with on a/c system supercharged air communicating pipe for blocking the isolation baffle plate of left and right a/c system supercharged air.
On the test cell of main cabin, install temperature gage and the coolant-temperature switch identical with former machine additional, form electronic machine bleed temperature control circuitry.
Advantage of the present invention: the electronic machine ventilation cooling system that the present invention is based on Y7 aircraft environmental control system provides supercharged air by the system parallel connection of two of left and right for main cabin, and its temperature can regulate in a big way.When Y7 aircraft is used as flight test platform, less demanding to cabin temperature amenity, but repacking can not affect the pressure adjusting function in main cabin, to guarantee flight safety.This programme is by the isolation of former machine left and right a/c system and carry out respectively temperature control, has taken into account high-altitude, main cabin demand for heat and electronic machine cooling requirement, and repacking does not relate to former passenger cabin pressure regulating system, does not affect flight safety;
In addition, the present invention is based on supercharged air that the electronic machine ventilation cooling system of Y7 aircraft environmental control system quotes from engine bleed, flow is large, pressure head is higher, can meet the requirement of GJB2882 < < air environment ventilation ventilation cooling system general specification > > completely.And do not relate to carrier aircraft aerodynamic configuration and change, do not increase driving engine and power-supply system load, the weightening finish of repacking project almost can be ignored, avoided ram air bleed repacking or installed the compensatory loss of platform property that large centrifugal ventilating set brings additional, can not increase main cabin noise level simultaneously yet, be conducive to improve test personnel's working environment, therefore there is larger actual application value.
Accompanying drawing explanation
Fig. 1 is Y7 aircraft environmental control system bleed repacking schematic diagram;
Fig. 2 is that bleed temperature is controlled repacking schematic diagram,
Wherein: the coolant-temperature switch that the feed air temperature table 17-former machine driving compartment coolant-temperature switch 18-main cabin that on the left a/c system of the right a/c system 3-of the left a/c system 2-of 1-, the former machine driving compartment of the temperature control valve 15-feed air temperature table 16-main cabin of the right a/c system of the left a/c system feed air temperature of temperature control valve 12-sensor 13-right a/c system feed air temperature sensor 14-of the left a/c system of the left a/c system lower air duct of lower air duct changeover valve 4-left a/c system upper air duct 5-6-electronic machine bleed breather pipe 7-isolation baffle plate 8-left and right a/c system supercharged air communicating pipe 9-task system electronic machine 10-air entraining pipe tube wall tap hole 11-installs additional installs additional.
The specific embodiment
Below in conjunction with the drawings and specific embodiments, the present invention will be further described:
Two from left and right of Y7 aircraft environmental control systems of the present invention start power traction to get supercharged air, carry out temperature regulate backward main cabin air feed by the identical a/c system in two of left and right 1/2.When aircraft is during in high-altitude flight, the a/c system of aircraft is generally in heated condition, if therefore by left and right two cover system "off", make right system in heated condition, to meet the needs of heating of aircraft itself, and make left system in refrigerating state, just can be used for the cooling of electronic machine.After supercharged air is introduced to electronic machine, be discharged into again in main cabin, do not affect CAB PRFS function.
The present invention comprises that to the repacking of former machine environmental control system bleed air line is reequiped and bleed temperature control circuitry is reequiped two aspects.
As shown in Figure 1, repacking needs to remove the left a/c system upper air duct 4 of former machine in bleed air line repacking, installs bleed breather pipe 6 and isolation baffle plate 7 additional.Wherein, bleed breather pipe adopts thin-walled rustproof aluminum alloy pipe manufacturer, catheter end head adopts HB4-110 roll wave version, conduit connects employing gum sleeve and flexibly connects form, its one end is communicated with left side upper air duct through changeover valve 3, to replace former left side upper air duct 4, the other end connects electronic machine 9 to be cooled.In addition, one end that bleed breather pipe closes on electronic machine is provided with some tap holes 10.Isolation baffle plate 7 was arranged on left and right a/c system supercharged air communicating pipe 8, to block left and right a/c system supercharged air, realized the object that left and right system feed air temperature is controlled respectively.
As shown in Figure 2, because former machine driving compartment feed air temperature table 15 and former machine driving compartment coolant-temperature switch 17 are, left and right a/c system is in parallel to be shown and controls for bleed temperature control circuitry repacking, need be from former electric cable conducting detach relevant signal conductor.On the test cell of main cabin, install the coolant-temperature switch 18 identical with former air conditioner system additional, and be connected with left a/c system temperature control valve 11, to control bleed temperature by left a/c system temperature control valve.On the test cell of main cabin, install the temperature gage 16 identical with former air conditioner system additional, and be connected with left a/c system feed air temperature sensor 12, for showing bleed temperature.And from aircraft bus-bar, draw direct current 28V, the indicating & controlling device part that power supply is installed additional to main cabin.After repacking, former machine driving compartment feed air temperature table 15 can only show the temperature information of right a/c system feed air temperature sensor 13, and the feed air temperature table 16 that main cabin installs additional shows the temperature information of left a/c system feed air temperature sensor 12; Former machine driving compartment coolant-temperature switch 17 can only be controlled the temperature control valve 14 of right a/c system, and the temperature control valve 11 of the left a/c system of 18 control is opened in the temperature control that main cabin installs additional.
During electronic machine ventilation cooling system real work of the present invention, by test system, powered on, driving engine is driven and is opened bleed switch, handle the coolant-temperature switch 18 on the test cell of main cabin, by left a/c system temperature control valve 11, change the air-flow ratio on He Leng road, former left a/c system Ci Re road, thereby control the gas flow temperature in bleed breather pipe 6, to realize, to electronic machine, ventilate cooling.Wherein, because former passenger cabin supercharge amount is larger, and the required cooling air delivery of electronic machine is less, after avoiding accessing electronic machine, because increasing, flow resistance changes the left a/c system mode of operation of former machine, and unnecessary flow can tap hole shunting on air entraining pipe tube wall.
The electronic machine ventilation cooling system that the present invention is based on Y7 aircraft environmental control system provides supercharged air by the system parallel connection of two of left and right for main cabin, and its temperature can regulate in a big way.When Y7 aircraft is used as flight test platform, less demanding to cabin temperature amenity, but repacking can not affect the pressure adjusting function in main cabin, to guarantee flight safety.This programme is by the isolation of former machine left and right a/c system and carry out respectively temperature control, has taken into account high-altitude, main cabin demand for heat and electronic machine cooling requirement, and repacking does not relate to former passenger cabin pressure regulating system, does not affect flight safety.The supercharged air of quoting is from engine bleed, flow is large, pressure head is higher, can meet the requirement of GJB2882 < < air environment ventilation ventilation cooling system general specification > > completely.And do not relate to carrier aircraft aerodynamic configuration and change, do not increase driving engine and power-supply system load, the weightening finish of repacking project almost can be ignored, avoided ram air bleed repacking or installed the compensatory loss of platform property that large centrifugal ventilating set brings additional, can not increase main cabin noise level simultaneously yet, be conducive to improve test personnel's working environment, therefore there is larger actual application value.
Claims (5)
1. the electronic machine ventilation cooling system based on Y7 aircraft environmental control system, it is characterized in that, comprise former air conditioner system, bleed air line, wherein, former a/c system comprises left and right a/c system, bleed air line is replaced first left a/c system upper air duct, and one end is communicated with left side upper air duct through changeover valve, and the other end connects electronic machine to be cooled.
2. the electronic machine ventilation cooling system based on Y7 aircraft environmental control system according to claim 1, is characterized in that, described bleed breather pipe adopts thin-walled rustproof aluminum alloy pipe manufacturer, and catheter end head adopts HB4-110 roll wave version.
3. the electronic machine ventilation cooling system based on Y7 aircraft environmental control system according to claim 1, is characterized in that, one end of bleed air line connecting electronic equipment is provided with tap hole.
4. the electronic machine ventilation cooling system based on Y7 aircraft environmental control system according to claim 1, is characterized in that, left and right is provided with on a/c system supercharged air communicating pipe for blocking the isolation baffle plate of left and right a/c system supercharged air.
5. the electronic machine ventilation cooling system based on Y7 aircraft environmental control system according to claim 1, is characterized in that, installs temperature gage and the coolant-temperature switch identical with former machine on the test cell of main cabin additional, forms electronic machine bleed temperature control circuitry.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310648508.8A CN103723276A (en) | 2013-12-04 | 2013-12-04 | Electronic equipment ventilation cooling system based on Y7 aircraft environment control system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310648508.8A CN103723276A (en) | 2013-12-04 | 2013-12-04 | Electronic equipment ventilation cooling system based on Y7 aircraft environment control system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103723276A true CN103723276A (en) | 2014-04-16 |
Family
ID=50447638
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310648508.8A Pending CN103723276A (en) | 2013-12-04 | 2013-12-04 | Electronic equipment ventilation cooling system based on Y7 aircraft environment control system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103723276A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108216643A (en) * | 2018-01-11 | 2018-06-29 | 北京航空航天大学 | Civil aircraft main cabin based on radiation temperature or so cabin independence temperature-controlling system and method |
| CN110053778A (en) * | 2019-03-26 | 2019-07-26 | 南京航空航天大学 | The supply of cooling medium and thermoregulating system on a kind of centrifugation turntable |
| CN110510124A (en) * | 2019-08-09 | 2019-11-29 | 中国商用飞机有限责任公司 | A kind of airplane air entraining system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB844863A (en) * | 1955-11-30 | 1960-08-17 | United Aircraft Corp | Air conditioning system for aircraft |
| CN1138685A (en) * | 1995-12-28 | 1996-12-25 | 南京航空航天大学 | Air circulating plane environmental control system able to fully utilizing energy |
| CN101973402A (en) * | 2010-09-26 | 2011-02-16 | 北京航空航天大学 | Novel variable air supply system for large conveyer |
| CN102159459A (en) * | 2009-02-25 | 2011-08-17 | 空中客车作业有限公司 | System and method for cooling aircraft zone by utilizing aircraft-external air unit |
| US20130082138A1 (en) * | 2011-09-30 | 2013-04-04 | Airbus Operations Sas | Ventilation system, air blowing and extraction circuits of such a system, as well as an aircraft avionics bay |
-
2013
- 2013-12-04 CN CN201310648508.8A patent/CN103723276A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB844863A (en) * | 1955-11-30 | 1960-08-17 | United Aircraft Corp | Air conditioning system for aircraft |
| CN1138685A (en) * | 1995-12-28 | 1996-12-25 | 南京航空航天大学 | Air circulating plane environmental control system able to fully utilizing energy |
| CN102159459A (en) * | 2009-02-25 | 2011-08-17 | 空中客车作业有限公司 | System and method for cooling aircraft zone by utilizing aircraft-external air unit |
| CN101973402A (en) * | 2010-09-26 | 2011-02-16 | 北京航空航天大学 | Novel variable air supply system for large conveyer |
| US20130082138A1 (en) * | 2011-09-30 | 2013-04-04 | Airbus Operations Sas | Ventilation system, air blowing and extraction circuits of such a system, as well as an aircraft avionics bay |
Non-Patent Citations (1)
| Title |
|---|
| 何君等: "综合数字控制技术在飞机环境控制系统的应用", 《系统仿真学报》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108216643A (en) * | 2018-01-11 | 2018-06-29 | 北京航空航天大学 | Civil aircraft main cabin based on radiation temperature or so cabin independence temperature-controlling system and method |
| CN110053778A (en) * | 2019-03-26 | 2019-07-26 | 南京航空航天大学 | The supply of cooling medium and thermoregulating system on a kind of centrifugation turntable |
| CN110053778B (en) * | 2019-03-26 | 2022-04-08 | 南京航空航天大学 | Cooling medium supply and temperature regulation system on centrifugal turntable |
| CN110510124A (en) * | 2019-08-09 | 2019-11-29 | 中国商用飞机有限责任公司 | A kind of airplane air entraining system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105270134B (en) | System and method for controlling the air-flow in vehicle | |
| DE602007009722D1 (en) | COOLING AND VENTILATION SYSTEM AND METHOD FOR A VENTILATION BASED ON A VEHICLE | |
| WO2011147977A9 (en) | Air conditioning system with hybrid operation for an aircraft | |
| CN102381479B (en) | Comprehensive environmental control/liquid cold and heat energy management system for non-stamping air inlet duct | |
| CN202231122U (en) | Intelligent heat management system for power battery box of hybrid power electric vehicle | |
| CN102390538A (en) | Comprehensive environmental control/liquid cooling heat energy management system without ramjet inlet | |
| CN106697297A (en) | Environmental control system capable of simultaneously providing liquid cooling and air cooling | |
| CN103723276A (en) | Electronic equipment ventilation cooling system based on Y7 aircraft environment control system | |
| CN206278283U (en) | A kind of large transport airplane multifunctional ground service truck | |
| CN104309442A (en) | Air conditioner device adopting storage battery power supply mode during running and stopping of double-compressor automobile | |
| CN102975733A (en) | Air conditioner for high-speed magnetic levitation train | |
| CN101817296A (en) | Airplane ground air-conditioning vehicle utilizing exhaust waste heat of diesel engine | |
| CN204956140U (en) | Electrombile thermal management system | |
| CN104260618B (en) | There is the new-energy automobile of Dual-energy source air-conditioning | |
| CN203637508U (en) | Novel vehicle-mounted heating and cooling air conditioning system | |
| CN203005440U (en) | Air-conditioning device for high-speed magnetic levitation trains | |
| CN103182978B (en) | A kind of Novel ice-storage airplane air conditioner vehicle | |
| CN202770042U (en) | Whole sealing air circulation refrigerating system driven by power turbine | |
| CN203978576U (en) | A kind of tail gas heat energy recovering device of hybrid vehicle | |
| CN207374680U (en) | A kind of cold and hot air interchanger of ground cockpit | |
| CN201619693U (en) | Ground air-conditioning vehicle for airplane | |
| CN104505556B (en) | Power battery natural air cooling system of blade electric vehicles and control method thereof | |
| CN201530284U (en) | Multi-borne multiplex bus air conditioner | |
| CN104534757B (en) | A kind of control method of universal liquid cool equipment | |
| CN103287585A (en) | Natural cooling energy-efficient aircraft ground air-conditioned vehicle and control method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140416 |