WO2010057548A1 - Procédé et système de ventilation d'urgence dans une cabine d'avion en cas de fuite dans la région d'un mélangeur d'air - Google Patents

Procédé et système de ventilation d'urgence dans une cabine d'avion en cas de fuite dans la région d'un mélangeur d'air Download PDF

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Publication number
WO2010057548A1
WO2010057548A1 PCT/EP2009/006510 EP2009006510W WO2010057548A1 WO 2010057548 A1 WO2010057548 A1 WO 2010057548A1 EP 2009006510 W EP2009006510 W EP 2009006510W WO 2010057548 A1 WO2010057548 A1 WO 2010057548A1
Authority
WO
WIPO (PCT)
Prior art keywords
air
aircraft
mixer
emergency
cabin
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.)
Ceased
Application number
PCT/EP2009/006510
Other languages
German (de)
English (en)
Other versions
WO2010057548A8 (fr
Inventor
Frank Klimpel
Rüdiger Schmidt
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations GmbH
Original Assignee
Airbus Operations GmbH
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Airbus Operations GmbH filed Critical Airbus Operations GmbH
Priority to CN200980144654.9A priority Critical patent/CN102209665B/zh
Priority to JP2011536748A priority patent/JP5559806B2/ja
Priority to US13/126,544 priority patent/US9266601B2/en
Priority to RU2011122564/11A priority patent/RU2515025C2/ru
Priority to BRPI0922188A priority patent/BRPI0922188A2/pt
Priority to EP09778399.7A priority patent/EP2349838B1/fr
Priority to CA2740516A priority patent/CA2740516C/fr
Publication of WO2010057548A1 publication Critical patent/WO2010057548A1/fr
Publication of WO2010057548A8 publication Critical patent/WO2010057548A8/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/18—Floors
    • 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
    • B64D13/02—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being pressurised
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/009—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like comprising decompression panels or valves for pressure equalisation in fuselages or floors
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Definitions

  • the invention relates to a method and a system for emergency ventilation of an aircraft cabin in the event of a leak in the region of an air mixer of the aircraft air conditioning system.
  • airliners are currently used for air conditioning of the aircraft cabin usually called air-based air conditioning.
  • the aircraft air conditioning system is used to cool the aircraft cabin, which would otherwise be subject to heat loads, such as heat. Solar radiation, body heat of passengers and waste heat from existing on board the aircraft devices would be too hot.
  • the aircraft air conditioning system supplies sufficient fresh air to the aircraft cabin to ensure that a prescribed minimum level of oxygen is present in the aircraft cabin.
  • the aircraft air conditioning system is used to maintain the pressure in the aircraft cabin during flight operation of the aircraft above a certain altitude at a level higher than the ambient pressure.
  • hot process air which is tapped off from the aircraft engines during flight operation of the aircraft, is supplied to two independently operable air conditioning units.
  • the process air which is supplied with a high temperature and high pressure, is treated in such a way that it leaves the air conditioning units as a relaxed and cooled process air.
  • the relaxed and cooled process air is supplied as fresh air to a mixer in which it is mixed with recirculated air discharged from the aircraft cabin.
  • the recirculation air is usually conveyed by recirculation fans from the aircraft cabin into the mixer.
  • the air mixture of fresh air and recirculation air generated in the mixer is finally directed into the aircraft cabin for aeration of the aircraft cabin.
  • the aircraft If a defect in the aircraft air conditioning system occurs during the flight, which causes the aircraft cabin can no longer be supplied with sufficient fresh air, so the aircraft drops to a safe altitude, in which it is no longer necessary, the pressure in the aircraft cabin to maintain a level higher than the ambient pressure, and flies unprinted to the destination airport or to a nearby airfield. To provide the necessary breathing air for this period, it is known to provide aircraft with one or more emergency breathing air inlets.
  • the emergency ram air inlet flaps can be arranged to supply ram air from the aircraft environment via the emergency ram air inlets and to feed it as fresh air into the mixer of the aircraft air conditioning system.
  • the pressure drop in the mixer causes the recirculation fans to suck air from the mixer rather than from the aircraft cabin. Consequently, there is a short circuit in the recirculation air system, which causes the recirculation air flow to collapse. In case of failure of a leak in the area of the mixer, neither sufficient fresh air from the air conditioning units nor sufficient recirculation air is conducted into the aircraft cabin.
  • the fresh air supply via the emergency ram air inlets can also ensure a sufficient supply of fresh air to the aircraft cabin in the event of a leak in the area of the mixer, since the fresh air supplied via the emergency ram air inlets is distributed via the mixer in the cabin. As a result, the fresh air supplied via the emergency ram air inlets escapes unused into the environment of the mixer in the underfloor area of the aircraft. A leak in the area of the mixer of the aircraft air conditioning system can thus lead, in particular in aircraft in which no cockpit or cabin window can be opened, the CO 2 content in the cabin air to a health-damaging level.
  • the invention has for its object to provide a method and a system for emergency ventilation of an aircraft cabin, which also in the case of a leak in the area an air mixer of the aircraft air conditioning system to ensure adequate supply of the aircraft cabin with fresh air.
  • the presence of a leak in the region of an air mixer of an aircraft air conditioning system is detected in a first step.
  • the leak present in the region of the air mixer of the aircraft air conditioning system can be, for example, a leak caused by a disconnected rotor part or the like.
  • the leak detection or leak detection can be carried out, for example, by an electronic control unit based on signals that are transmitted to the electronic control unit of sensors already provided in the aircraft air conditioning system.
  • the sensors may, for example, be pressure sensors arranged in different areas of the aircraft air conditioning system, so that the electronic control unit can detect a leak present in the area of the air mixer of the aircraft air conditioning system based on the pressure developments in the various areas of the aircraft air conditioning system which are characteristic of such an error situation.
  • the sensors whose signals may be used to detect a leak in the area of the air mixer of the aircraft air conditioning system may be sensors that supply a fresh air mass flow from an air conditioning unit of the aircraft air conditioning system to the air mixer, a recirculation air mass flow and / or one from the air mixer into the air conditioning system Aircraft cabin directed to measure mixed air flow.
  • an emergency air flap which prevents air exchange between the aircraft area adjacent to the air mixer and the aircraft cabin in a closed position is controlled into an open position.
  • the emergency air damper can be controlled by means of the electronic control unit, which also detects the leakage in the area of the air mixer. This may be, for example, the central control unit of the aircraft air conditioning system. Alternatively, for the Leak detection and the control of the emergency air damper but also be provided separate electronic control units.
  • the desired delivery of air from the aircraft area adjacent to the air mixer into the aircraft cabin itself is not impaired by damage to the aircraft outer skin in the surroundings of the air mixer, since the external pressure on the damaged aircraft outer skin during flight operation of the aircraft is so high that no air exits the area adjacent to the air mixer aircraft area in the aircraft environment.
  • the air which escapes from the air mixer into the aircraft region adjacent to the air mixer due to a leak in the region of the air mixer can be conveyed from the aircraft region adjacent to the air mixer into the aircraft cabin by any suitable conveying device.
  • a fan or a blower can be provided in the aircraft area adjacent to the air mixer, which if necessary can serve to convey air from the aircraft area adjacent to the air mixer through the opened emergency air flap into the aircraft cabin.
  • the conveyor can be controlled by means of the control device, which also assumes the leak detection in the area of the air mixer and / or the control of the emergency air damper.
  • a separate control device for controlling the conveyor may also be provided.
  • an air outlet valve of an aircraft cabin pressure control system is controlled to an open position such that a pressure which is less than that is generated in an area of the aircraft adjacent to the air outlet valve Pressure in the aircraft area adjacent to the air mixer.
  • This is possible, for example, in an operating state of the air outlet valve, in which the air outlet valve designed in the form of a flap is opened 50%.
  • a negative pressure of -0.1 cp relative to the aircraft ambient pressure may be generated.
  • the emergency ventilation method according to the invention preferably opens an air outlet valve which is arranged in a rear fuselage area of the aircraft.
  • the selective adjustment of a negative pressure in the aircraft region adjacent to the air outlet valve by corresponding control of the opening state of the air outlet valve allows the generation of a vacuum-driven air flow from the aircraft mixer adjacent aircraft area in the aircraft cabin.
  • the air is finally sucked out of the aircraft cabin into the aircraft region adjacent to the air outlet valve and discharged through the opened air outlet valve into the aircraft environment.
  • the air flow from the aircraft cabin into the aircraft region adjacent to the air outlet valve can take place, for example, through air outlet openings which are formed in a floor and / or side walls of the aircraft cabin which separate the aircraft cabin from the underfloor area of the aircraft.
  • the air outlet valve of the aircraft cabin pressure control system can be controlled by means of the control unit, which is also used to detect the leak in the air mixer of the aircraft air conditioning system and / or to control the emergency air damper.
  • a separate electronic control unit or an electronic control unit of the aircraft cabin pressure control system can be included in the method according to the invention for the emergency ventilation of an aircraft cabin and used to control the air outlet valve.
  • the vacuum-driven delivery of air from the aircraft area surrounding the air mixer into the aircraft cabin by a corresponding control of the air outlet valve of the aircraft cabin pressure control system makes it possible to dispense with a separate conveyor. As a result, weight and installation space savings can be realized. Furthermore, the reliability of the emergency ventilation system increases, since it can be ruled out that in a fault, the separate conveyor is damaged and therefore is no longer operational.
  • the air conditioning unit is preferably controlled so that generated by the air conditioning unit, a maximum air mass flow and the air mixer is supplied. If both air conditioning units of the aircraft air conditioning system are still operational, preferably both air conditioning units are controlled so that they generate a maximum air mass flow and feed the air mixer. This ensures that there is sufficient air for supply to the aircraft cabin in the air mixer and in particular in the aircraft area adjacent to the air mixer.
  • an emergency ram air inlet door may be controlled to an open position such that aircraft ambient air may be supplied to the air mixer through an emergency ram air inlet. If there are several emergency ram air inlets, preferably all the ram air inlet lids are controlled to their open position.
  • the supply of aircraft ambient air into the air mixer via an emergency air intake is particularly important if both air conditioning units of the aircraft air conditioning system have failed.
  • An ambient air supply via an emergency air intake is also conceivable in the operational state of the air conditioning units of the aircraft air conditioning system, for example to provide for an additional air supply into the air mixer and in particular in the aircraft area adjacent to the air mixer.
  • control of the air conditioning units of the aircraft air conditioning system and the emergency air intake damper of the emergency air intake can be done with the aid of the control unit, which is also used to detect the leak in the area of the air mixer and / or to control the emergency air damper.
  • control unit which is also used to detect the leak in the area of the air mixer and / or to control the emergency air damper.
  • the operation of the air conditioning units and the emergency air intake door may also be controlled by separate control unit (s).
  • the recirculation fans of the aircraft air conditioning system are furthermore controlled such that their operation is interrupted.
  • the pressure in the region of the air mixer which counteracts the supply of air from the air conditioning units and the emergency air intake into the air mixer, can be reduced.
  • the recirculation fans suck in the presence of appropriate pressure conditions air from the air mixer.
  • the recirculation ons fans can be controlled with the help of the electronic control unit, which also handles the leak detection in the area of the air mixer and / or the control of the emergency air damper.
  • the operation of the recirculation ventilators can also be controlled by a separate control unit.
  • the emergency air damper is disposed in a cabin lining panel or formed by a cabin lining panel.
  • the cabin trim panel may be, for example, a dado panel of the aircraft cabin paneling.
  • a plurality of emergency air dampers may be provided.
  • part or all of the dado panels of the aircraft cabin lining may be designed as emergency air flaps.
  • the dado panels may be movably disposed so as to prevent air exchange between the aircraft area adjacent to the air mixer and the aircraft cabin in a closed position and to allow air to be delivered from the aircraft area adjacent the air mixer to the aircraft cabin in an open position ,
  • a system according to the invention for emergency ventilation of an aircraft cabin comprises an electronic control unit which is adapted to detect a leak in the area of an air mixer of an aircraft air conditioning system and an emergency air flap which, in a closed position, exchanges air between an aircraft area adjacent to the air mixer and the aircraft cabin prevents controlling in an open position.
  • the emergency ventilation system according to the invention comprises a device for conveying air from the aircraft area adjacent to the air mixer through the opened emergency air flap into the aircraft cabin. Due to the emergency ventilation system according to the invention, proper ventilation of the aircraft cabin can be ensured even in the event of a fault in which the air mixer of the aircraft air conditioning system is damaged so that air exits the air mixer into the aircraft area adjacent to the air mixer.
  • the means for conveying air from the aircraft area adjacent the air mixer to the aircraft cabin comprises an air outlet valve of an aircraft cabin pressure control system adapted to be controlled to an open position to create a pressure in an area of the aircraft adjacent to the air outlet valve which is less than the pressure in the aircraft area adjacent to the air mixer. Since the area adjacent to the air outlet valve portion of the aircraft from which to the air mixer A negative pressure-driven air flow from the aircraft area adjacent to the air mixer can be generated via the aircraft cabin into the aircraft area adjacent to the air outlet valve through a corresponding opening of the air outlet valve. On the provision of a separate conveyor for conveying air from the to the to the
  • Air mixer adjacent aircraft area in the aircraft cabin can thus be dispensed with.
  • the emergency ventilation system may further comprise an electronic control unit, which is set up to control an air conditioning unit of the aircraft cabin in such a way that a maximum air mass flow is generated by the air conditioning unit and supplied to the air mixer. If both air conditioning units of the aircraft air conditioning system are still operational, the electronic control unit is preferably configured to control both air conditioning units such that a maximum air mass flow is generated by the air conditioning units and supplied to the air mixer.
  • the emergency ventilation system may comprise an electronic control unit which is set up to control an emergency air intake flap to an open position, so that aircraft ambient air can be supplied to the air mixer through an emergency air intake.
  • an electronic control unit may be provided, which is set up to control recirculation fans of the aircraft air conditioning system in such a way that their operation is interrupted.
  • the electronic control unit of the emergency ventilation system which serves to detect a leak present in the area of the air mixer and / or to control the emergency air flap, can also be used to control the air conditioning unit / engine units of the aircraft air conditioning system, the emergency air intake flap and / or the recirculation fans become.
  • this electronic control unit may be the central control unit of the aircraft air conditioning system.
  • separate electronic control units may also be used to detect leaks, control the emergency air damper, control the engine unit (s), control the emergency ram air inlet door and / or control the recirculation fans.
  • control of the air outlet valve of the aircraft cabin pressure control system be adopted by the electronic control unit, which also serves to detect a present in the air mixer leak and / or to control the emergency air damper.
  • the electronic control unit which also serves to detect a present in the air mixer leak and / or to control the emergency air damper.
  • a separate electronic control unit or an electronic control unit of the aircraft cabin pressure control system may be part of the emergency ventilation system according to the invention.
  • the emergency air flap is arranged in a cabin lining panel or formed by a cabin lining panel.
  • the cabin trim panel may be, for example, a dado panel of the aircraft cabin paneling.
  • Figure 1 is an overview of a system for emergency ventilation of a
  • Figures 2a and 2b show in an emergency ventilation system according to Figure 1 used as emergency air flaps dado panels of an aircraft cabin paneling.
  • FIG. 1 shows a system 10 for emergency ventilation of an aircraft cabin 12.
  • aircraft cabin 12 is to be understood here as meaning all areas of the aircraft to be ventilated during normal operation of an aircraft, such as a cockpit, a passenger cabin, crew areas and cargo spaces to be ventilated.
  • the emergency ventilation system 10 comprises an electronic control unit 14 which receives signals from a plurality of sensors 18 arranged in the region of an aircraft air conditioning system 16. The sensors 18 serve to measure the pressure and air mass flows in various areas of the aircraft air conditioning system 16.
  • the aircraft air conditioning system 16 comprises two independently operable air conditioning units 20, 22.
  • the air conditioning units 20, 22 supplied by the engines of the aircraft hot bleed air is treated such that it leaves the air conditioning units 20, 22 as a relaxed and cooled process air.
  • the relaxed and cooled process air is supplied as fresh air to a central mixer 24.
  • the mixer 24 the fresh air from the air conditioning units 20, 22nd mixed with recirculation air, the recirculation fans 26, 28 from the aircraft cabin 12 in the mixer 24 promote.
  • the air mixture of fresh air and recirculation air generated in the mixer 24 is finally conducted into the aircraft cabin 12 via an air distribution system (not illustrated in FIG. 1).
  • the mixer 24 of the aircraft air conditioning system 16 is also in communication with an emergency air intake 30.
  • the emergency air intake 30 is closed by an emergency air intake flap 32 arranged in the region of the aircraft outer skin. With the emergency ram air inlet flap 32 open, ram air from the aircraft environment may be directed through the emergency ram air inlet 30 into the mixer 24 of the aircraft air conditioning system 16.
  • the operation of the emergency ram air inlet door 32 is controlled by the electronic control unit 14.
  • FIG. 1 illustrates a first and a second air outlet valve 34, 36 of an aircraft cabin pressure control system.
  • the air outlet valves 34, 36 serve to provide pressure equalization between the aircraft environment and an aircraft area at a decreasing altitude of the aircraft, which is maintained above a certain altitude of the aircraft under a pressure increased from the ambient pressure.
  • the air flow from the aircraft cabin 12 in the direction of the second air outlet valve 36 takes place through air outlet openings 44, which are formed in a floor 46 separating the aircraft cabin 12 from the underfloor area of the aircraft.
  • the first air outlet valve 34 is disposed in a front region of the aircraft, while the second air outlet valve 36 is located in a rear body region of the aircraft. In other words, the second air outlet valve 36 is along a longitudinal axis of
  • the emergency ventilation system 10 comprises a plurality of emergency air flaps 38 which are only schematically indicated in FIG. 1 and which, in a closed position, prevent an air exchange between an aircraft region 40 adjacent to the air mixer 24 and the aircraft cabin 12.
  • the emergency air flaps 38 are formed by dado panels of the aircraft cabin paneling.
  • the dado panels are movable between their closed position in which they prevent air exchange between the aircraft region 40 adjacent the mixer 24 in the underfloor area of the aircraft and the aircraft cabin 12, and an open position. In her open position The dado panels allow the supply of air from the aircraft area 40 adjacent to the mixer 24 into the aircraft cabin 12.
  • the operation of the emergency air damper 38, as well as the operation of the emergency ram air inlet door 32, are controlled by the electronic control unit 14. Furthermore, the electronic control unit 14 is used to control the operation of the air conditioning units 20, 22, the recirculation ventilators 26, 28 and the air outlet valves 34, 36.
  • the pressure drop in the mixer 24 causes the recirculation fans 26, 28 to draw air from the mixer 24 rather than from the aircraft cabin 12. Consequently, a short circuit in the recirculation air system of the aircraft air conditioning system 16, which causes the recirculation air flow into the mixer 24 breaks down.
  • This development of the pressure conditions and the air mass flows in the various areas of the air conditioning units 16 is detected by the sensors 18. Consequently, the electronic control unit 14 can detect the presence of a leak in the region of the air mixer 24 of the aircraft air conditioning system 16 on the basis of the signals transmitted by the sensors 18.
  • the electronic control unit 14 controls the emergency air flaps 38 in their open state. This makes it possible for air escaping from the mixer 24 to flow from the aircraft region 40 adjacent to the mixer 24 into the aircraft cabin 12.
  • the electronic control unit 14 controls the second air outlet valve 36 in an open state in which the second air outlet valve 36, which is in the form of a flap, is opened 50%.
  • a pressure which is less than the pressure in the aircraft area 40 adjacent to the air mixer 24.
  • the pressure control described above allows the aircraft region 42 adjacent to the second air outlet valve 36 a low-pressure-driven air flow from the aircraft area 40 adjacent to the mixer 24 into the aircraft cabin 12 and from the aircraft cabin 12 into the aircraft area 42 adjacent to the second air outlet valve 36.
  • the air flow from the aircraft cabin 12 into the aircraft area adjacent to the second air outlet valve 36 42 takes place through the air outlet openings 44 formed in the bottom 46.
  • a separate device for conveying air out of the aircraft area 40 adjacent to the mixer 24 into the aircraft cabin 12 can therefore be dispensed with.
  • the electronic control unit 14 controls this air conditioning unit 20, 22 such that a maximum air flow is generated by the air conditioning unit 20, 22 and the air
  • both air conditioning units 20, 22 are controlled by the electronic control unit 14 such that a maximum air mass flow is generated by the air conditioning units 20, 22 and supplied to the air mixer 24. This ensures that in the mixer 24 and in particular in the aircraft adjacent to the mixer 24
  • the electronic control unit 14 controls the emergency ram air inlet flap 32 to an open position. As a result, air can be conducted from the aircraft environment into the air mixer 24 through the emergency air intake 30.
  • the electronic control unit 14 controls the recirculation fans 26, 28 such that their operation is interrupted.
  • the supply of fresh air from the air conditioning units 20, 22 or via the emergency air intake 30 in the mixer 24 is counteracted by reducing the pressure.
  • the recirculation fans 26, 28 are prevented from sucking air from the mixer 24.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Health & Medical Sciences (AREA)
  • General Health & Medical Sciences (AREA)
  • Pulmonology (AREA)
  • Mechanical Engineering (AREA)
  • Ventilation (AREA)
  • Air Conditioning Control Device (AREA)
  • Air-Conditioning For Vehicles (AREA)

Abstract

L'invention concerne un procédé de ventilation d'urgence d'une cabine d'avion (12) selon lequel une fuite est détectée dans la région d'un mélangeur d'air (24) d'un système de conditionnement d'air (16) d'avion. Un clapet de ventilation d'urgence (38) qui empêche, dans une position fermée, un échange d'air entre une zone d'avion (40) voisine du mélangeur d'air (24) et la cabine d'avion (12) est manoeuvré dans une position ouverte. Enfin, l'air provenant de la zone d'avion (40) voisine du mélangeur d'air (24) est transporté via le clapet de ventilation d'urgence (38) ouvert dans la cabine d'avion (12).
PCT/EP2009/006510 2008-11-21 2009-09-08 Procédé et système de ventilation d'urgence dans une cabine d'avion en cas de fuite dans la région d'un mélangeur d'air Ceased WO2010057548A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
CN200980144654.9A CN102209665B (zh) 2008-11-21 2009-09-08 用于在空气混合器的区域中发生泄漏的情况下对飞机机舱紧急通风的方法和系统
JP2011536748A JP5559806B2 (ja) 2008-11-21 2009-09-08 空気混合機周辺のリークの場合の航空機キャビンの緊急換気方法及びそのシステム
US13/126,544 US9266601B2 (en) 2008-11-21 2009-09-08 Method and system for emergency ventilation of an aircraft cabin in the case of a leak in the area of an air mixer
RU2011122564/11A RU2515025C2 (ru) 2008-11-21 2009-09-08 Способ и система аварийной вентиляции кабины воздушного судна в случае утечки в зоне смесителя воздуха
BRPI0922188A BRPI0922188A2 (pt) 2008-11-21 2009-09-08 método e sistema para a ventilação de emergência de uma cabina de aeronave
EP09778399.7A EP2349838B1 (fr) 2008-11-21 2009-09-08 Procede et systeme de ventilation d'urgence dans une cabine d'avion en cas de fuite dans la region d'un melangeur d'air
CA2740516A CA2740516C (fr) 2008-11-21 2009-09-08 Methode et systeme de ventilation d'urgence d'une cabine d'aeronef en cas de fuite dans la zone d'un melangeur d'air

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US11667608P 2008-11-21 2008-11-21
US61/116,676 2008-11-21
DE102008058451.7 2008-11-21
DE102008058451A DE102008058451B4 (de) 2008-11-21 2008-11-21 Verfahren und System zur Notbelüftung einer Flugzeugkabine im Fall eines Lecks im Bereich eines Luftmischers

Publications (2)

Publication Number Publication Date
WO2010057548A1 true WO2010057548A1 (fr) 2010-05-27
WO2010057548A8 WO2010057548A8 (fr) 2010-08-26

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2009/006510 Ceased WO2010057548A1 (fr) 2008-11-21 2009-09-08 Procédé et système de ventilation d'urgence dans une cabine d'avion en cas de fuite dans la région d'un mélangeur d'air

Country Status (9)

Country Link
US (1) US9266601B2 (fr)
EP (1) EP2349838B1 (fr)
JP (1) JP5559806B2 (fr)
CN (1) CN102209665B (fr)
BR (1) BRPI0922188A2 (fr)
CA (1) CA2740516C (fr)
DE (1) DE102008058451B4 (fr)
RU (1) RU2515025C2 (fr)
WO (1) WO2010057548A1 (fr)

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EP2740665A1 (fr) 2012-12-10 2014-06-11 Airbus Operations GmbH Procédé et système de secours pour pressuriser et ventiler une cabine d'aéronef

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US8701718B1 (en) 2006-08-16 2014-04-22 Rescue Air Systems, Inc. Emergency air system and method of a marine vessel
DE102009010150B4 (de) 2009-02-23 2013-09-19 Airbus Operations Gmbh System und Verfahren zur Notbelüftung einer Flugzeugkabine
DE102009012015A1 (de) * 2009-03-06 2010-09-09 Airbus Deutschland Gmbh Dekompressionsanordnung für ein Luftfahrzeug
CN102545546B (zh) * 2011-12-01 2014-05-14 国家电网公司 循环冷却系统及控制循环冷却系统的方法
CN105051453A (zh) * 2013-04-10 2015-11-11 3M创新有限公司 远程照明光导管
US9862494B2 (en) * 2014-09-25 2018-01-09 Hamilton Sundstrand Corporation Flight deck tap off for mixer
DE102015216247A1 (de) * 2015-08-26 2017-03-02 Airbus Operations Gmbh Flugzeugklimaanlage zur Verbindung mit einem flugzeugexternen Lufterzeugungsaggregat
DE102016207149A1 (de) * 2016-04-27 2017-11-02 Airbus Operations Gmbh System und Verfahren zur Notbelüftung eines Flugzeugs
GB2634112A (en) * 2023-09-21 2025-04-02 Airbus Sas Aircraft cabin air distribution system

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CA2740516A1 (fr) 2010-05-27
DE102008058451B4 (de) 2010-11-18
CN102209665B (zh) 2014-11-26
US20120003908A1 (en) 2012-01-05
JP2012509216A (ja) 2012-04-19
EP2349838A1 (fr) 2011-08-03
WO2010057548A8 (fr) 2010-08-26
CA2740516C (fr) 2016-07-12
US9266601B2 (en) 2016-02-23
RU2011122564A (ru) 2012-12-27
EP2349838B1 (fr) 2013-11-06
RU2515025C2 (ru) 2014-05-10
DE102008058451A1 (de) 2010-05-27
BRPI0922188A2 (pt) 2015-12-29
CN102209665A (zh) 2011-10-05

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