EP0000312A1 - Einrichtung für Atmungsunterstützung und für Beschirmung gegen Beschleunigungseffekte in Kriegsflugzeugen - Google Patents

Einrichtung für Atmungsunterstützung und für Beschirmung gegen Beschleunigungseffekte in Kriegsflugzeugen Download PDF

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Publication number
EP0000312A1
EP0000312A1 EP19780400042 EP78400042A EP0000312A1 EP 0000312 A1 EP0000312 A1 EP 0000312A1 EP 19780400042 EP19780400042 EP 19780400042 EP 78400042 A EP78400042 A EP 78400042A EP 0000312 A1 EP0000312 A1 EP 0000312A1
Authority
EP
European Patent Office
Prior art keywords
pressure
pockets
regulator
acceleration
installation according
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.)
Granted
Application number
EP19780400042
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English (en)
French (fr)
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EP0000312B1 (de
Inventor
Raymond Beaussant
Jacques Claude
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.)
Safran Aerosystems SAS
Original Assignee
Intertechnique SA
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Filing date
Publication date
Application filed by Intertechnique SA filed Critical Intertechnique SA
Publication of EP0000312A1 publication Critical patent/EP0000312A1/de
Application granted granted Critical
Publication of EP0000312B1 publication Critical patent/EP0000312B1/de
Expired legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D10/00—Flight suits
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D16/00—Control of fluid pressure
    • G05D16/04—Control of fluid pressure without auxiliary power
    • G05D16/06—Control of fluid pressure without auxiliary power the sensing element being a flexible membrane, yielding to pressure, e.g. diaphragm, bellows, capsule
    • G05D16/063—Control of fluid pressure without auxiliary power the sensing element being a flexible membrane, yielding to pressure, e.g. diaphragm, bellows, capsule the sensing element being a membrane
    • G05D16/0644—Control of fluid pressure without auxiliary power the sensing element being a flexible membrane, yielding to pressure, e.g. diaphragm, bellows, capsule the sensing element being a membrane the membrane acting directly on the obturator
    • G05D16/0655—Control of fluid pressure without auxiliary power the sensing element being a flexible membrane, yielding to pressure, e.g. diaphragm, bellows, capsule the sensing element being a membrane the membrane acting directly on the obturator using one spring-loaded membrane
    • G05D16/0658—Control of fluid pressure without auxiliary power the sensing element being a flexible membrane, yielding to pressure, e.g. diaphragm, bellows, capsule the sensing element being a membrane the membrane acting directly on the obturator using one spring-loaded membrane characterised by the form of the obturator
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/0753—Control by change of position or inertia of system

Definitions

  • the pants pockets intended for protection against accelerations are distinct from those intended to ensure pressurization at altitude.
  • the pockets intended to protect against accelerations remain empty during normal flight, which lengthens the response buffers, i.e. the time which elapses between the reception of the inflation order of the pockets and the moment when the pressure in the pockets is sufficient for the protection to be real.
  • the present invention aims to provide an installation in which the drawbacks of previous installations are eliminated, at least to a large extent and the individual equipment of the pilot is simplified.
  • the invention provides an installation having means intended to establish in said pockets a pressure which is an increasing function of the altitude independently of the acceleration.
  • Figure 1 shows in an extremely schematic and simplified manner the part of an installation which is intended to control the pressure in the pants pockets of the protective clothing against accelerations.
  • the installation is supplied by a line 10
  • the supply of gas under pressure This gas will for example be oxygen from an on-board liquid oxygen converter, or air, under a pressure of a few bars (5 bars for example).
  • the pants pockets are connected to the installation by a flexible pipe 11.
  • the installation represented in FIG. 1 (where the scale is not respected) comprises a certain number of organs which are conventional and will therefore only be brief.
  • These members include a main valve 2 consisting of a fixed seat and a diaphragm. In the rest position, the membrane is applied to the seat and separates the lines 10 and 11.
  • a starting chamber 13 delimited by the rear of the membrane and the case in which it is placed is subjected to the pressure prevailing in line 10
  • the membrane is applied to its seat and closes the passage in the seat.
  • pilot valve 15 The pressure prevailing in the chamber 13, connected to the pipe 10 by a calibrated orifice 14, is controlled by a pilot valve 15.
  • This pilot valve comprises sensitive regulation membrane 16 controlling a closure element 17 which cooperates with a fixed seat to connect the chamber 13 with the pipe 11.
  • the pressure prevailing at the rear of the sensitive membrane 16 is in turn determined by control and safety valves.
  • a valve 19 allows the air contained in the pockets to escape the atmosphere, in the direction indicated by the arrow F ', when the pressure applied to the rear of the membrane 16 decreases.
  • the control valve as a function of the acceleration is actuated by a flyweight improved compared to those previously known.
  • This feeder ( Figure 2) has a mass 20 of a few tens of grams contained in a chamber 21 formed in a 'fixed housing and connected to the atmosphere.
  • the mass 20 is carried by a membrane 22, the periphery of which is fixed to the housing.
  • This membrane is arranged transversely to. sense Has accelerations to detect. limits the movements of the mass 20 from the seat 24 to a length which is very slightly greater than the lift required.
  • the membrane may be made of molded silicone and be fixed to the mass either by overmolding or by fitting.
  • the orifice delimited by the seat will generally have a very small diameter, from 2 to 3 mm for example. We see that the entire case can be miniaturized, especially if the seat 24 is formed by a sapphire which can be pierced with a hole of very small diameter.
  • the stiffness of the spring may be such that the mass 20 only applies to the seat 24 from an acceleration of approximately 2 g.
  • the pressure prevailing behind the membrane 16 of the pilot valve can also be modified as a function of the altitude.
  • the installation comprises a sealed altimetric capsule 26, subjected to the pressure prevailing in the cabin, one end of which is carried by a fixed housing and the other end of which carries a closure element 27 provided with a extender 28.
  • the shutter member 27 releases an opening in the housing.
  • the capsule 26 expands and the member 27 tends to separate the interior of the housing from a relay chamber 29.
  • the passage in the seat 24 communicates with the rear of the diaphragm 16 of the pilot valve only via this relay chamber.
  • the relay chamber 29 contains a double valve 30 which an elastic return blade 31 keeps at rest in a position where it separates the relay room of the capsule housing and, on the other hand, connects the relay chamber 29 to the passage in the seat 24 ' (FIG. 1).
  • the extension pusher 28 pushes back the double valve 30 and separates the chamber: relay 29 from the passage in the seat 24.
  • the operating surface on the shutter 27 of the pressure prevailing in the relay chamber 29 is chosen so that the pressure in this chamber is established at a value which is a function of the pressure in the cabin, therefore of the altitude.
  • the installation also includes a calibrated leak orifice 32 connecting the line 10 to the relay chamber and to the rear of the membrane 16.
  • the gas flow admitted by the valve 12 is not sent directly into the pockets of the protective pants.
  • This gas is used as the driving fluid in an ejector 34 supplied with air coming from the cabin via a non-return valve 35.
  • the primary flow is considerably lower than the flow to be supplied to the pants, which makes it possible to miniaturize the installation and in particular its moving parts.
  • the consumption of gas from line 10 is considerably reduced, which is particularly important in the case where this gas consists of oxygen which also supplies the respiratory device: the ratio of the flow rates of entrained air and entrainment gas can be from 8 to 1.
  • the flow peaks are considerably reduced and become compatible with the possibilities of liquid oxygen converters.
  • FIG. 1 in dashes, means for pre-inflating the pockets of the protective pants even before the weight is subjected to acceleration.
  • These means comprise a solenoid valve 36 and an electrical control circuit 37.
  • This arrangement is particularly convenient to implement if the aircraft is provided with a control system with electric transmission of orders. In this case, in fact, it suffices to take the electrical signal from the transmission and to process it.
  • the mode of treatment used will depend on the one hand, on the acrodynamic and control characteristics of the airplane, on the other hand, situation parameters, such as for example the speed, the altitude, etc.
  • the electrical circuit will in general essentially comprise a timer which, on reception of a signal indicating that the steering position will cause acceleration in direction A, will apply to the solenoid valve 36 an opening signal for a duration predetermined, corresponding to the establishment of an appropriate pressure (typically seconds).
  • FIG. 3 shows the variation in the volume V of these pockets as a function of the pressure p relative to the atmosphere.
  • Pre-inflation can be carried out, as shown in Figure 1, using a timer system which indirectly limits the pressure reached.
  • One can also use a calibrated valve associated with bmwvanhe 36. closing the supply as soon as the pressure reaches the value 'through the point 39, which may for example correspond to a pressure of about two-thirds of the final pressure.
  • the electric control will be provided to not interfere come only if the steering control announces an acceleration above the threshold normally. expected for conventional anti-g valves, of the order of 2 g in general
  • FIG. 4 that shown diagrammatically in FIG. 4 (where only the elements belonging to a circuit different from that of FIG. 1 have been shown) does not include a double-acting valve, Point 38, to which the valve is connected safety 18, the rear chamber of the pilot valve 15, the return valve 19 and the throttled orifice 32, is connected directly to the seat 24. But the chamber 21 is not connected to the atmosphere, but to the occupied chamber by the capsule 29 This last chamber is in turn connected to the atmosphere.
  • FIG. 4 also shows a conventional pre-flight verification assembly, with which the device of FIG. 1 can also be fitted.
  • This verification device is placed at the outlet 39 of the chamber occupied by the altimetric capsule 26 and l 'atmosphere. In the case of Figure 1, it would be placed between the chamber 21 and the atmosphere. It includes a push button 40 pushed by a spring in a position where it lets the outlet 39 communicate with the atmosphere. By pressing this button, the operator separates the outlet 39 from the atmosphere, the pressure increases behind the diaphragm 16 of the pilot valve and the pockets of the protective pants inflate to a pressure level fixed by the check valve 41.
  • the device comprises a first calibrated orifice 43 connecting the normal supply line 10 to the passage formed in the seat 24 of the counterweight and a second calibrated orifice 44 connecting the emergency pipe 42 to the connecting passage between the chamber occupied by the capsule 26 and the double valve 30.
  • the latter is not provided with a return spring.
  • the main valve 12 is supplied from the normal pipe 10.
  • the normal pipe 10 is generally supplied by a liquid oxygen converter 46 carried by the aircraft.
  • the emergency line 42 is provided with a compressed gas cylinder 47: provided with a pressure reducer 48, carried by the seat.
  • a non-return valve 49 allows the converter 46 to also supply the emergency line 42, except in the event of ejection.
  • the converter 46 feeds the pockets of the anointing pants anti-g). It also feeds the pilot's mask or helmet and the jacket pockets (respiratory functions and pressurization).
  • the altimetric capsule 26 can be replaced by a pressure tap from the regulator, the request which supplies breathing gas to the wearer of the pants.
  • the tap can be made on the high pressure stage of the regulator, with intermediate pressure reduction. It can also be done on exit from use.
  • the double valve 30 avoids any action of the counterweight 20 on the pressure of the respiratory mixture.
  • the regulator is for example of the type described in patent FR 74 34826, published under the number 2 288 346 .
  • the control of the pressure in the pockets of the pants has hitherto been mainly described to fulfill the functions of anti-g protection and pressurization.
  • the respiratory mixture regulator of the installation is advantageously designed to cooperate with the anti-g regulator for protection against acceleration. to clarify more.
  • the respiratory regulator 54 is advantageously designed to create an overpressure in the event of acceleration. For this, one can either add to the regulator 54 a counterweight, or send it a signal l coming from the regulator 53.
  • a counterweight or send it a signal l coming from the regulator 53.
  • the arrangement shown diagrammatically in FIG. 7 can be adopted.
  • the compartment situated behind the request membrane 58 is connected in a conventional manner by a caliber 57 leak to the oxygen supply and, by a passage controlled by an altimetric capsule 58. to the atmosphere of the cabin.
  • a flyweight 59 is interposed, designed to give an overpressure as a function of the acceleration significantly less increasing than that controlled by the flyweight 20. Because the overpressures controlled by the flyweight 59 will always remain weak, there is little inconvenience in adding the orders of the counterweight and the capsule. However, an assembly with mixing of orders by double valve comparable to that of FIGS. 1 and 5 is possible.

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  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Fluid Mechanics (AREA)
  • General Physics & Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Health & Medical Sciences (AREA)
  • General Health & Medical Sciences (AREA)
  • Pulmonology (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Respiratory Apparatuses And Protective Means (AREA)
EP19780400042 1977-07-01 1978-06-29 Einrichtung für Atmungsunterstützung und für Beschirmung gegen Beschleunigungseffekte in Kriegsflugzeugen Expired EP0000312B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR7720345A FR2395890A1 (fr) 1977-07-01 1977-07-01 Installation respiratoire et de protection contre l'acceleration pour avions de combat
FR7720345 1977-07-01

Publications (2)

Publication Number Publication Date
EP0000312A1 true EP0000312A1 (de) 1979-01-10
EP0000312B1 EP0000312B1 (de) 1982-07-14

Family

ID=9192874

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19780400042 Expired EP0000312B1 (de) 1977-07-01 1978-06-29 Einrichtung für Atmungsunterstützung und für Beschirmung gegen Beschleunigungseffekte in Kriegsflugzeugen

Country Status (4)

Country Link
US (1) US4230097A (de)
EP (1) EP0000312B1 (de)
DE (1) DE2861948D1 (de)
FR (1) FR2395890A1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3016417A1 (de) * 1979-05-02 1980-11-13 Intertechnique Sa Gasstroemungssteuereinrichtung
EP0448258A1 (de) * 1990-03-13 1991-09-25 Normalair-Garrett (Holdings) Limited Versorgungsvorrichtung für Flugzeugbesatzung

Families Citing this family (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2551421B1 (fr) * 1983-08-31 1985-12-13 Intertechnique Sa Dispositif de protection contre les accelerations
US4638791A (en) * 1985-07-22 1987-01-27 The Boeing Company Apparatus and methods for providing rapid protection from accelerative forces experienced by aircraft crew members
US4736731A (en) * 1986-02-24 1988-04-12 The United States Of America As Represented By The Secretary Of The Air Force Rapid acting electro-pneumatic anti-G suit control valve
US4799476A (en) * 1986-09-29 1989-01-24 The Boeing Company Universal life support system
FR2614208B1 (fr) * 1987-04-22 1989-09-08 Intertechnique Sa Harnais de masque respiratoire et masque en comportant application.
US6039045A (en) * 1987-04-22 2000-03-21 Intertechnique Head harness for respiratory mask
US4915106A (en) * 1988-02-26 1990-04-10 Puritan-Bennett Corporation Crew oxygen mask with pneumatic comfort adjustment
FR2650248A1 (fr) * 1989-07-26 1991-02-01 Intertechnique Sa Dispositif de protection de membre d'equipage d'aeronef contre l'acceleration
US5127896A (en) * 1989-09-05 1992-07-07 Mcdonnell Douglas Corporation Anthropomorphic tank suit
GB8921344D0 (en) * 1989-09-21 1989-11-08 Normalair Garrett Ltd Aircraft aircrew life support apparatus
DE3941684C1 (de) * 1989-12-18 1991-07-18 Dornier Luftfahrt Gmbh, 8031 Wessling, De
US5050240A (en) * 1990-05-14 1991-09-24 Kaiser Aerospace And Electronics Corporation Air cushion helmet support and ventilation system with air pressure regulator
GB9013630D0 (en) * 1990-06-19 1990-08-08 Normalair Garrett Ltd Aircraft aircrew life support apparatus
US5153938A (en) * 1991-06-19 1992-10-13 Mcdonnell Douglas Corporation Acceleration protection ensemble and method
US5277693A (en) * 1993-01-04 1994-01-11 The United States Of America As Represented By The Secretary Of The Air Force Flight activated anti-G valve (FAAGV)
US5704073A (en) 1995-08-01 1998-01-06 Figgie International Inc. Quick donning goggles for use with breathing mask
US5816244A (en) * 1996-05-14 1998-10-06 Nellcor Puritan Bennett Incorporated Modular structural system for personal service and oxygen dispensing system modules for use in transport aircraft with improved latch and testing capability
US5954052A (en) * 1997-05-21 1999-09-21 Nellcor Puritan-Bennett Safety stowage apparatus for crew oxygen masks
FR2767304B1 (fr) 1997-08-13 1999-10-22 Intertechnique Sa Dispositif de protection contre les accelerations
US6450943B1 (en) 2000-01-18 2002-09-17 Litton Systems, Inc. Apparatus for and method of combating the gravity push-pull effect experienced by an airman wearing a flight suit
US6820616B1 (en) * 2001-08-01 2004-11-23 Scot Incorporated Combined aircrew systems tester (CAST)
US7401787B1 (en) 2004-11-12 2008-07-22 Juan Conte Inflatable combat arena game
EP3421099B1 (de) * 2006-04-20 2019-12-11 Zodiac Aerotechnics Atemgerät für ein flugzeugbesatzungsmitglied
BR112013006163C8 (pt) * 2010-09-23 2019-10-22 Intertechnique Sa regulador de oxigênio para fornecer gás de respiração em uma aeronave
US9016278B2 (en) * 2011-07-25 2015-04-28 Zodiac Aerotechnics Regulation valve for a life support system
CN104399195B (zh) * 2014-11-28 2017-11-17 航宇救生装备有限公司 供氧压力调节装置

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1249698B (de) *
GB890623A (en) * 1958-12-29 1962-03-07 Bendix Corp Improvements in or relating to inflatable acceleration-protection garments and pressure controlling valves therefor
FR1520187A (fr) * 1967-04-21 1968-04-05 British Oxygen Co Ltd Régulateur de débit
GB1113235A (en) * 1964-10-08 1968-05-08 Hymatic Eng Co Ltd Improvements relating to acceleration-responsive valve assemblies
GB1217196A (en) * 1967-11-29 1970-12-31 Vapor Corp Pressure regulator
US3672384A (en) * 1969-09-18 1972-06-27 Aga Ab Breathing gas regulator for aviators

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3158149A (en) * 1959-06-29 1964-11-24 Reuben F Gray Acceleration protective apparatus
US3734078A (en) * 1971-05-12 1973-05-22 Bendix Corp Means for anticipating anti-g force in a moving vehicle

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1249698B (de) *
GB890623A (en) * 1958-12-29 1962-03-07 Bendix Corp Improvements in or relating to inflatable acceleration-protection garments and pressure controlling valves therefor
GB1113235A (en) * 1964-10-08 1968-05-08 Hymatic Eng Co Ltd Improvements relating to acceleration-responsive valve assemblies
FR1520187A (fr) * 1967-04-21 1968-04-05 British Oxygen Co Ltd Régulateur de débit
GB1217196A (en) * 1967-11-29 1970-12-31 Vapor Corp Pressure regulator
US3672384A (en) * 1969-09-18 1972-06-27 Aga Ab Breathing gas regulator for aviators

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3016417A1 (de) * 1979-05-02 1980-11-13 Intertechnique Sa Gasstroemungssteuereinrichtung
EP0448258A1 (de) * 1990-03-13 1991-09-25 Normalair-Garrett (Holdings) Limited Versorgungsvorrichtung für Flugzeugbesatzung

Also Published As

Publication number Publication date
DE2861948D1 (en) 1982-09-02
EP0000312B1 (de) 1982-07-14
FR2395890A1 (fr) 1979-01-26
FR2395890B1 (de) 1983-07-29
US4230097A (en) 1980-10-28

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