SYSTEM FOR REGULATING THE DISPENSING OF COMMERCIAL AIRCRAFT PASSENGER OXYGEN SUPPLY

Abstract

The aircraft emergency oxygen supply system includes one or more sources of supplemental breathable oxygen, one or more inlet valves for one or more breathing devices, connected to the inlet valves, and one or more cabin air pressure transducers. A pressure controller controls the inlet valves in response to the one or more cabin air pressure transducers. One or more second pressure transducers may connected to conduits downstream of inlet valves to be monitored, and the pressure controller may also control operation of the inlet valves in response to the one or more second pressure transducers.

Claims

1-8. (canceled)

9. An emergency oxygen supply system for an aircraft with a pressurizable passenger cabin comprising: a first on-off inlet valve connected via a first conduit to a first source of supplemental breathable oxygen and not connected to a second source of supplemental breathable oxygen; a second on-off inlet valve connected via a second conduit to the second source of supplemental breathable oxygen and not connected to the first source of supplemental breathable oxygen, the first conduit and second conduit are separate; at least one first breathing device configured to receive supplemental breathable oxygen from the first source of supplemental breathable oxygen and not from the second source of supplemental breathable oxygen, and at least one second breathing device configured to receive supplemental breathable oxygen from the second source of supplemental breathable oxygen and not from the first source of supplemental breathable oxygen; a first manifold connected between the first on-off inlet valve and the at least one first breathing device, and a second manifold connected between the second on-off inlet valve and the second at least one breathing device; and a pressure controller that receives an cabin air pressure input signal and controls operation of the first and second on-off inlet valves by transmitting a single control signal to each of the first on-off inlet valve and the second on-off inlet valve based on the cabin air pressure input signal received from the at least one cabin air pressure transducer.

10. The emergency oxygen supply system of claim 9, wherein at least one of the first on-off inlet valve or the second on-off inlet valve include a solenoid valve.

11. The emergency oxygen supply system of claim 10, wherein the solenoid valve is a two-position solenoid valve.

12. The emergency oxygen supply system of claim 9, further comprising a pressure regulator that connects the first source of supplemental breathable oxygen with the first on-off inlet valve.

13. The emergency oxygen supply system of claim 9, wherein the at least one first breathing device includes a reservoir bag and a face mask attached to the reservoir bag.

14. The emergency oxygen supply system of claim 13, wherein the first manifold is between the first on-off inlet valve and the reservoir bag.

15. The emergency oxygen supply system of claim 9, wherein the pressure controller includes a plurality of simultaneously operating channels that provide the single control signal to each of the first on-off inlet valve and the second on-off inlet valve.

16. The emergency oxygen supply system of claim 9, wherein the pressure controller determines the single control signal so that a flow rate achieved by each dispensing orifice is equal to an intrinsic flow rate multiplied by a fraction of time that the corresponding first on-off inlet valve or second on-off inlet valve is open.

17. The emergency oxygen supply system of claim 9, wherein at least one of the first source of supplemental breathable oxygen or the second source of supplemental breathable oxygen does not include an altitude-compensating feature.

18. The emergency oxygen supply system of claim 9, wherein the pressure controller applies the single control signal for a fraction of operating time corresponding to an altitude of the aircraft.

19. An emergency oxygen supply system for an aircraft with a pressurizable passenger cabin comprising: a first on-off inlet valve connected via a first conduit to a first source of supplemental breathable oxygen and not connected to a second source of supplemental breathable oxygen; a second on-off inlet valve connected via a second conduit to the second source of supplemental breathable oxygen and not connected to the first source of supplemental breathable oxygen, the first conduit and second conduit are separate; at least one first breathing device connected with the first source of supplemental breathable oxygen and not connected with the second source of supplemental breathable oxygen; at least one second breathing device connected with the second source of supplemental breathable oxygen and not connected with the first source of supplemental breathable oxygen; a first manifold connected between the first on-off inlet valve and the at least one first breathing device, and a second manifold connected between the second on-off inlet valve and the second at least one breathing device; and a pressure controller that receives an cabin air pressure input signal and controls operation of the first and second on-off inlet valves by transmitting a single control signal to each of the first on-off inlet valve and the second on-off inlet valve based on the cabin air pressure input signal received from the at least one cabin air pressure transducer.

20. The emergency oxygen supply system of claim 19, wherein at least one of the first on-off inlet valve or the second on-off inlet valve include a solenoid valve.

21. The emergency oxygen supply system of claim 20, wherein the solenoid valve is a two-position solenoid valve.

22. The emergency oxygen supply system of claim 19, further comprising a pressure regulator that connects the first source of supplemental breathable oxygen with the first on-off inlet valve.

23. The emergency oxygen supply system of claim 19, wherein the at least one first breathing device includes a reservoir bag and a face mask attached to the reservoir bag.

24. The emergency oxygen supply system of claim 23, wherein the first manifold is between the first on-off inlet valve and the reservoir bag.

25. The emergency oxygen supply system of claim 19, wherein the pressure controller includes a plurality of simultaneously operating channels that provide the single control signal to each of the first on-off inlet valve and the second on-off inlet valve.

26. The emergency oxygen supply system of claim 19, wherein the pressure controller determines the single control signal so that a flow rate achieved by each dispensing orifice is equal to an intrinsic flow rate multiplied by a fraction of time that the corresponding first on-off inlet valve or second on-off inlet valve is open.

27. The emergency oxygen supply system of claim 19, wherein at least one of the first source of supplemental breathable oxygen or the second source of supplemental breathable oxygen does not include an altitude-compensating feature.

28. The emergency oxygen supply system of claim 19, wherein the pressure controller applies the single control signal for a fraction of operating time corresponding to an altitude of the aircraft.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0023] FIG. 1 is a schematic diagram of a first embodiment of the system for regulating the dispensing of commercial aircraft passenger oxygen supply, according to the present invention.

[0024] FIG. 2 is a schematic diagram of a second embodiment of the system for regulating the dispensing of commercial aircraft passenger oxygen supply, according to the present invention.

[0025] FIG. 3 is a schematic diagram of a third embodiment of the system for regulating the dispensing of commercial aircraft passenger oxygen supply, according to the present invention.

[0026] FIG. 4 is a schematic diagram of a fourth embodiment of the system for regulating the dispensing of commercial aircraft passenger oxygen supply, according to the present invention.

[0027] FIG. 5 is a schematic diagram of a variation of the fourth embodiment of FIG. 4.

[0028] FIG. 6 is a schematic diagram of a fifth embodiment of the system for regulating the dispensing of commercial aircraft passenger oxygen supply, according to the present invention.

[0029] FIG. 7 is a schematic diagram of a variation of the fifth embodiment of FIG. 6.

[0030] FIG. 8 is a schematic diagram of a sixth embodiment of the system for regulating the dispensing of commercial aircraft passenger oxygen supply, according to the present invention.

[0031] FIG. 9 is a schematic diagram of a seventh embodiment of the system for regulating the dispensing of commercial aircraft passenger oxygen supply, according to the present invention.

[0032] FIG. 10 is a schematic diagram of a eighth embodiment of the system for regulating the dispensing of commercial aircraft passenger oxygen supply, according to the present invention.

[0033] FIG. 11 is a schematic diagram of a ninth embodiment of the system for regulating the dispensing of commercial aircraft passenger oxygen supply, according to the present invention.

[0034] FIG. 12 is a schematic diagram of a variation of the ninth embodiment of FIG. 11.

[0035] FIG. 13 is a schematic diagram of a tenth embodiment of the system for regulating the dispensing of commercial aircraft passenger oxygen supply, according to the present invention.

[0036] FIG. 14 is a schematic diagram of a variation of the tenth embodiment of FIG. 13.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0037] Referring to the drawings, which are provided for purposes of illustration and by way of example, the present invention provides for an aircraft emergency oxygen supply system utilizing an electrically operated on-off inlet valve in combination with one or more suitable pressure transducers and one or more pressure controllers to supply supplemental oxygen appropriate for the prevailing cabin altitude, without dispensing more oxygen than is needed, minimizing the weight of the oxygen supply, and allowing efficient use of multiple control zones and oxygen sources within an aircraft.

[0038] In a first preferred embodiment of the emergency oxygen supply system 10 of the present invention, illustrated in FIG. 1, a plurality of sources of supplemental breathable oxygen 12a, 12b, 12c, such as a plurality of cylinders of compressed oxygen, for example, store a required supply of oxygen. Corresponding conduits 14a, 14b, 14c are connected to the plurality of sources of supplemental breathable oxygen, respectively, to provide a flow of oxygen, controlled by corresponding relatively simple on-off inlet valves 16a, 16b, 16c, respectively, to corresponding sets of breathing devices 18a, 18b, 18c typically including one or more individual reservoir bags and attached face masks, respectively. In one presently preferred aspect, the inlet valves are located in proximity to the corresponding plurality of sources of supplemental breathable oxygen. At least one pressure controller 20 is connected to the inlet valves and controls the operation of the inlet valves via a network of control lines 22, in response to an input signal received from a single cabin air pressure transducer P.sub.A (24) representing the cabin pressure and a corresponding altitude. This configuration results in a system that is lighter than one without altitude compensation, and simpler than one that uses conventional altitude compensation with a multiplicity of complex regulators.

[0039] In a second embodiment of the invention illustrated in FIG. 2, an emergency oxygen supply system 30 includes a plurality of sources of supplemental breathable oxygen 32a, 32b, 32c, such as a plurality of cylinders of compressed oxygen, for example, that store a required supply of oxygen. Corresponding conduits 34a, 34b, 34c are connected to the plurality of sources of supplemental breathable oxygen, respectively, to provide a flow of oxygen, controlled by corresponding relatively simple on-off inlet valves 36a, 36b, 36c, respectively, such as two-position solenoid valves, for example, to corresponding sets of breathing devices 38a, 38b, 38c, typically including one or more individual reservoir bags and attached face masks, respectively. In one presently preferred aspect, the inlet valves are located in proximity to the corresponding plurality of sources of supplemental breathable oxygen. At least one pressure controller, such as the pressure controller 40, is connected to the inlet valves and controls the operation of the inlet valves via a network of control lines 42 in response to a first input signal received from a first pressure transducer P.sub.A (44) representing the cabin pressure and a corresponding altitude, and in response to a second input signal received from a second pressure transducer P.sub.D (46) connected to one of the conduits at a location 48 downstream of one of the inlet valves to be monitored, representing the current gas pressure downstream of the monitored valve. From the input from the downstream pressure transducer P.sub.D, the controller compares a current gas pressure downstream (P.sub.D) with a desired delivery pressure. If the current downstream pressure is greater than or equal to the desired delivery pressure, the inlet valves remain closed. If the downstream pressure is lower than desired, the controller momentarily opens the valves, releasing added oxygen into the downstream portion of the oxygen distribution system and raising the downstream pressure.

[0040] Within this embodiment, the valves could be opened for an interval that is constant for each opening event, and the delivery would then be controlled solely by adjusting the duration of the time between pulses. Alternatively, both the length of the opening interval and the duration of the closed time between intervals could be each adjusted to achieve the overall result.

[0041] Since oxygen flows out of the system through the breathing devices, the pressure at the point where the downstream pressure is measured would vary somewhat as a function of time, dropping continuously when the valves are closed and increasing continuously when the valves are opened. The magnitude of the contained volume of the system downstream, relative to the volume rate of flow out of the system, would affect the magnitude of such variations. By suitably varying the time scale of the on and off intervals, the output pressure can be adjusted to suitably approximate a steady state.

[0042] Many oxygen systems for aircraft passengers utilize as the oxygen dispensing device the type of constant flow oxygen mask that is known as a phase dilution mask. Such masks are contemplated by SAE Aerospace Standard AS8025. The mask has a reservoir that collects oxygen delivered during the portions of the breathing cycle when the user is exhaling and during the pause between breaths, and this collected oxygen is then delivered at the beginning of the next inhalation. If the time scale of the variation in delivery pressure is short relative to the time scale of the breathing cycle, the output pressure would be considered to be approximating a steady state in a manner suitable for the purpose of supplying such a mask.

[0043] Thus, in the second embodiment of the invention, a simple inlet valve such as a two position solenoid valve can replace a more complicated and costly control valve. In association with this change in valve type, the controller is also correspondingly simpler because it is only required to generate a simple on or off signal.

[0044] In a third embodiment of the invention illustrated in FIG. 3, multiple simple inlet valves are placed at various locations within the oxygen distribution piping system, with a pressure transducer downstream of each valve. In this embodiment, the emergency oxygen supply system 50 includes a plurality of sources of supplemental breathable oxygen 52a, 52b, 52c, such as a plurality of cylinders of compressed oxygen, for example, that store a required supply of oxygen. Corresponding conduits 54a, 54b, 54c are connected to the plurality of sources of supplemental breathable oxygen, respectively, to provide a flow of oxygen, controlled by corresponding first relatively simple upstream on-off inlet valves V.sub.1 (56a), V.sub.3 (56b), V.sub.5 (56c), respectively, and corresponding second relatively simple downstream on-off inlet valves V.sub.2 (58a), V.sub.4 (58b), V.sub.6 (58c), respectively, such as two-position solenoid valves, for example, connected serially to corresponding sets of breathing devices 60a, 60b, 60c, each typically including one or more individual reservoir bags and attached face masks, respectively. At least one pressure controller, such as a single pressure controller 62, is connected to the inlet valves and controls the operation of the inlet valves via a network of control lines 63 in response to input signals received from a first pressure transducer P.sub.A (64), representing the cabin pressure and a corresponding altitude, and input signals received from a plurality of second pressure transducers P.sub.1 (66a), P.sub.3 (66b), P.sub.5 (66c), downstream from the upstream on-off valves V.sub.1, V.sub.3, V.sub.5, respectively, and input signals received from a plurality of second pressure transducers P.sub.2 (68a), P.sub.4 (68b), P.sub.6 (68c), downstream from the downstream on-off valves V.sub.2, V.sub.4, V.sub.6, respectively, representing the current gas pressure downstream of the monitored valves. Each valve and associated pressure transducer set is connected to the controller by a separate set of wires. The controller may have multiple independent channels, so that each valve and associated pressure transducer has a dedicated control channel. Alternatively, the pressure controller could be sequenced so that the signal from one downstream pressure transducer at a time is read, and its associated valve is pulsed if the pressure value detected is low enough to require this action.

[0045] In this embodiment, oxygen delivery pressure can be set to an optimum value zone by zone, without performance being limited by the differences in flow rates at various locations in the piping network that result from variations in pressure drops within different regions of the piping network.

[0046] In a fourth embodiment of the invention, illustrated in FIG. 4, an emergency oxygen supply system 70 includes a plurality of sources of supplemental breathable oxygen 72a, 72b, 72c, such as a very large number of separate, relatively small oxygen cylinders that are distributed throughout the airplane. In the limiting case of such an approach, each cabin occupant may be served by a separate one-person cylinder. Corresponding conduits 74a, 74b, 74c are connected to the plurality of sources of supplemental breathable oxygen, respectively, to provide a flow of oxygen, controlled by corresponding relatively simple on-off inlet valves 76a, 76b, 76c, respectively, such as two-position solenoid valves, for example, to corresponding individual breathing devices 78a, 78b, 78c typically including one or more individual reservoir bags and attached face masks, respectively. Since the piping between the small cylinders and the few breathing devices supplied with oxygen would be relatively simple, the pressure drops would all be essentially equal, so there would be little or no need to deliver excess oxygen to the average breathing device in a given zone in order to ensure the least favored breathing device in the zone is not under-supplied. Each oxygen vessel is fitted with a simple pressure reducing regulator 80a, 80b, 80c, respectively, with no altitude-compensating features included. In such an approach to oxygen system design that uses many small, separate cylinders, the controller should be very capable, either equipped with a very large number of simultaneously operating separate channels or capable of managing a very large number of signals in rapid sequence. Downstream of each valve, a manifold 82a, 82b, 82c, fitted with one or more dispensing orifices, is interposed between the corresponding valve and its associated reservoir bag, respectively. Each manifold orifice supplies one breathing device. If there are two or more dispensing orifices present, the oxygen manifold is configured such that all of these dispensing orifices experience the same upstream oxygen pressure.

[0047] At least one pressure controller, such as a single pressure controller 84, is connected to and controls the operation of the inlet valves via a network of control lines 86 in response to a first input signal received from a single pressure transducer P.sub.A (88), representing the cabin pressure and a corresponding altitude. The controller evaluates the pressure transducer signal and generates a single signal to all of the simple inlet valves. In this case, there is an intrinsic flow rate that would be achieved through each dispensing orifice if the simple inlet valves were continuously open. This intrinsic flow rate is a function of the output pressure from the pressure reducer and the properties of the dispensing orifices. Depending on the flow that is appropriate for the given altitude, the valve-operating signal is applied for a suitable fraction of the operating time. The flow rate achieved by each dispensing orifice is then equal to the intrinsic flow rate possible multiplied by the fraction of time the valve is open. For example, if the intrinsic flow rate possible when the valve is open continuously is 4 liters per minute and the valve is open 30% of the time, the flow rate achieved is 1.2 liters per minute.

[0048] As is illustrated in FIG. 5, in a variation of the fourth embodiment, in which the same elements from FIG. 4 are indicated by the same reference numbers as in FIG. 4, more than one cabin occupant may be served by each oxygen supply cylinder. Corresponding conduits 74a, 74b, 74c are connected to the plurality of sources of supplemental breathable oxygen, respectively, to provide a flow of oxygen, controlled by corresponding relatively simple on-off inlet valves 76a, 76b, 76c, respectively, such as two-position solenoid valves, for example, to corresponding sets of a plurality of breathing devices 89a, 89b, 89c, each typically including one or more individual reservoir bags and attached face masks, respectively. Each oxygen vessel is fitted with a simple pressure reducing regulator 80a, 80b, 80c, respectively, with no altitude-compensating features included. Downstream of each valve, a manifold 82a, 82b, 82c, fitted with one or more dispensing orifices, is interposed between the corresponding valve and its associated reservoir bag, respectively. Each manifold orifice supplies more than one breathing device. At least one pressure controller, such as a single pressure controller 84, is connected to the inlet valves and controls the operation of the inlet valves via a network of control lines 86 in response to a first input signal received from a single pressure transducer P.sub.A (88), representing the cabin pressure and a corresponding altitude.

[0049] In a fifth embodiment of the invention, illustrated in FIG. 6, an emergency oxygen supply system 90 includes a plurality of sources of supplemental breathable oxygen 92a, 92b, 92c, such as a very large number of separate, relatively small oxygen cylinders distributed throughout the airplane. As is shown in FIG. 6, each cabin occupant may be served by a separate one-person cylinder, although more than one person may be served by each oxygen supply cylinder, as is further described below. Corresponding conduits 94a, 94b, 94c are connected to the plurality of sources of supplemental breathable oxygen, respectively, to provide a flow of oxygen, controlled by corresponding relatively simple on-off inlet valves 96a, 96b, 96c, respectively, such as two-position solenoid valves, for example, to corresponding individual breathing devices 98a, 98b, 98c typically including one or more individual reservoir bags and attached face masks, respectively. In this embodiment, a pressure reducer at the outlet of the local oxygen vessel is eliminated. Since the piping between the small cylinders and the few breathing devices supplied with oxygen would be relatively simple, the pressure drops would all be essentially equal, so there would be little or no need to deliver excess oxygen to the average breathing device in a given zone in order to ensure the least favored breathing device in the zone is not under-supplied. Downstream of each inlet valve, a manifold 99a, 99b, 99c, fitted with one or more dispensing orifices, is interposed between the corresponding inlet valve and its associated reservoir bag, respectively. As is shown in FIG. 6, each manifold orifice supplies one breathing device, although each manifold may supply more than one breathing device, as is described below. If there are two or more dispensing orifices present, the oxygen manifold is configured such that all of these dispensing orifices experience the same upstream oxygen pressure.

[0050] At least one pressure controller, such as a single pressure controller 100, is connected to the inlet valves and controls the operation of the inlet valves via a network of control lines 102 in response to a first input signal received from a single pressure transducer P.sub.A (104), representing the cabin pressure and a corresponding altitude. The controller evaluates the pressure transducer signal and generates a single signal to all of the simple inlet valves. In this case, there is an intrinsic flow rate that would be achieved through each dispensing orifice if the simple inlet valves were continuously open. This intrinsic flow rate is a function of the output pressure from the pressure reducer and the properties of the dispensing orifices. Depending on the flow that is appropriate for the given altitude, the valve-operating signal is applied for a suitable fraction of the operating time. The flow rate achieved by each dispensing orifice is then equal to the intrinsic flow rate possible multiplied by the fraction of time the inlet valve is open. For example, if the intrinsic flow rate possible when the valve is open continuously is 4 liters per minute and the valve is open 30% of the time, the flow rate achieved is 1.2 liters per minute.

[0051] As is illustrated in FIG. 7, in a variation of the fifth embodiment, in which the same elements from FIG. 6 are indicated by the same reference numbers as in FIG. 6, more than one cabin occupant may be served by each oxygen supply cylinder. Corresponding conduits 94a, 94b, 94c are connected to the plurality of sources of supplemental breathable oxygen, respectively, to provide a flow of oxygen, controlled by corresponding relatively simple on-off inlet valves 96a, 96b, 96c, respectively, such as two-position solenoid valves, for example, to corresponding sets of breathing devices 106a, 106b, 106c, each typically including one or more individual reservoir bags and attached face masks, respectively. Downstream of each inlet valve, a manifold 99a, 99b, 99c, fitted with one or more dispensing orifices, is interposed between the corresponding inlet valve and its associated reservoir bag, respectively. Each manifold orifice supplies more than one breathing device, and each oxygen manifold is configured such that all of its dispensing orifices experience the same upstream oxygen pressure. At least one pressure controller, such as a single pressure controller 100, is connected to the inlet valves and controls the operation of the inlet valves via a network of control lines 102 in response to a first input signal received from a single pressure transducer P.sub.A (104) representing the cabin pressure and a corresponding altitude. Interposed between each oxygen vessel and its associated manifold containing the dispensing orifices, a simple electrical inlet valve is installed. An intrinsic flow rate can be achieved at any given point in time through each dispensing orifice when the simple inlet valve is open continuously. However, this flow rate changes as the pressure in the oxygen storage vessel upstream of the dispensing orifice decays with the passage of time during operation of the equipment. The flow rate is a function of the operating time history and the pressure decay properties of the oxygen storage units, as well as the properties of the dispensing orifices themselves. In this context, the operating time refers to the time the inlet valve remains open, which is not necessarily equal to the total elapsed time since the beginning of a decompression incident causing supplemental oxygen to be used.

[0052] In the fifth embodiment, a single pressure transducer senses the cabin pressure altitude. The controller contains information that mathematically describes the way in which the pressure in the oxygen storage vessel decays as a function of operating time. The controller also measures and retains information about the operating time history during the period of use. The controller evaluates the pressure transducer signal and the operating time history and generates a single signal to all of the simple inlet valves. Depending on the flow that is appropriate for the combination of given altitude and given previous operating time history, the valve-operating signal is applied for a suitable fraction of the operating time. The flow rate achieved by each dispensing orifice is then equal to the intrinsic flow rate possible multiplied by the fraction of time the inlet valve is open. While this embodiment requires greater calculating capabilities in the controller, it eliminates a large number of pressure reducing regulators as well as a large number of pressure transducers and their wiring.

[0053] In a sixth preferred embodiment of the emergency oxygen supply system 110 of the present invention, illustrated in FIG. 8, a source of supplemental breathable oxygen 112, such as one or more cylinders of compressed oxygen, for example, serves to store a required supply of oxygen. A corresponding conduit 114 is connected to the source of supplemental breathable oxygen to provide a flow of oxygen, controlled by a relatively simple on-off inlet valve 116, to a set 117 of one or more breathing devices 118a, 118b, 118c, 118d, typically including one or more individual reservoir bags and attached face masks, respectively. In one presently preferred aspect, the inlet valve is located in proximity to the source of supplemental breathable oxygen. A single pressure controller 120 is connected to and controls the operation of the inlet valve via control line 122 in response to an input signal received from a single cabin air pressure transducer P.sub.A (124), representing the cabin pressure and a corresponding altitude. This configuration results in a system that is lighter than one without altitude compensation, and simpler than one that uses conventional altitude compensation with a multiplicity of complex regulators. This configuration also allows for a zoned-system architecture, with one or more pressure controllers and their corresponding sources of supplemental breathable oxygen, inlet valves, breathing devices and cabin air pressure transducers placed in various locations within the aircraft.

[0054] In a seventh embodiment of the invention illustrated in FIG. 9, an emergency oxygen supply system 130 includes a source of supplemental breathable oxygen 132, such as one or more cylinders of compressed oxygen, for example, to store a required supply of oxygen. A conduit 134 is connected to the source of supplemental breathable oxygen to provide a flow of oxygen, controlled by a relatively simple on-off inlet valve 136, such as a two-position solenoid valve, for example, to a corresponding set 137 of breathing devices 138a, 138b, 138c, 138d, typically including one or more individual reservoir bags and attached face masks, respectively. In one presently preferred aspect, the inlet valve is located in proximity to the source of supplemental breathable oxygen. A single pressure controller 140 is connected to and controls the operation of the inlet valve via a control line 142 in response to a first input signal received from a first pressure transducer P.sub.A (144), representing the cabin pressure and a corresponding altitude, and in response to a second input signal received from a second pressure transducer P.sub.D (146) connected the conduits at a location 148 downstream of the inlet valve to be monitored, representing the current gas pressure downstream of the monitored inlet valve. From the input from the downstream pressure transducer P.sub.D, the controller compares a current gas pressure downstream (P.sub.D) with a desired delivery pressure. If the current downstream pressure is greater than or equal to the desired delivery pressure, the simple inlet valve remains closed. If the downstream pressure is lower than desired, the controller momentarily opens the inlet valve, releasing added oxygen into the downstream portion of the oxygen distribution system and raising the downstream pressure.

[0055] Within this embodiment, the inlet valve could be opened for an interval that is constant for each opening event, and the delivery would then be controlled solely by adjusting the duration of the time between pulses. Alternatively, both the length of the opening interval and the duration of the closed time between intervals could be each adjusted to achieve the overall result. Since oxygen flows out of the system through the breathing devices, the pressure at the point where the downstream pressure is measured would vary somewhat as a function of time, dropping continuously when the inlet valve is closed and increasing continuously when the inlet valve is opened. The magnitude of the contained volume of the system downstream, relative to the volume rate of flow out of the system, would affect the magnitude of such variations. By suitably varying the time scale of the on and off intervals, the output pressure can be adjusted to suitably approximate a steady state.

[0056] Many oxygen systems for aircraft passengers utilize as the oxygen dispensing device the type of constant flow oxygen mask that is known as a phase dilution mask. Such masks are contemplated by SAE Aerospace Standard AS8025. The mask has a reservoir that collects oxygen delivered during the portions of the breathing cycle when the user is exhaling and during the pause between breaths, and this collected oxygen is then delivered at the beginning of the next inhalation. If the time scale of the variation in delivery pressure is short relative to the time scale of the breathing cycle, the output pressure would be considered to be approximating a steady state in a manner suitable for the purpose of supplying such a mask.

[0057] Thus, in the seventh embodiment of the invention, a simple inlet valve such as a two position solenoid valve can replace a more complicated and costly control valve. In association with this change in valve type, the controller is also correspondingly simpler because it is only required to generate a simple on or off signal. This configuration also allows for a zoned-system architecture, with one or more pressure controllers and their corresponding sources of supplemental breathable oxygen, inlet valves, breathing devices and cabin air pressure transducers placed in various locations within the aircraft.

[0058] In an eighth embodiment of the invention illustrated in FIG. 10, multiple simple inlet valves are placed at various locations within the oxygen distribution piping system, with a pressure transducer downstream of each inlet valve. In this embodiment, the emergency oxygen supply system 150 includes a source of supplemental breathable oxygen 152, such as one or more cylinders of compressed oxygen, for example, which serves to store a required supply of oxygen. A conduit 154 is connected to the source of supplemental breathable oxygen to provide a flow of oxygen, controlled by a first relatively simple upstream on-off inlet valve V.sub.1 (156), and a second relatively simple downstream on-off inlet valve V.sub.2 (158), such as a two-position solenoid valve, for example, connected serially to a set 159 of breathing devices 160a, 160b, 160c, typically including one or more individual reservoir bags and attached face masks. A single pressure controller 162 is connected to the inlet valves and controls the operation of the inlet valves via control lines 163a, 163b in response to input signals received from a first pressure transducer P.sub.A (164), representing the cabin pressure and a corresponding altitude, input signals received from a second pressure transducer P.sub.1 (166a), downstream from the upstream on-off valve V.sub.1, and a third pressure transducer P.sub.2 (168a), downstream from the downstream on-off valve V.sub.2, representing the current gas pressure downstream of the monitored valves. Each valve and associated pressure transducer set is connected to the controller by a separate set of wires. The controller may have multiple independent channels, so that each valve and associated pressure transducer has a dedicated control channel. Alternatively, the controller could be sequenced so that the signal from one downstream pressure transducer at a time is read, and its associated valve is pulsed if the pressure value detected is low enough to require this action.

[0059] In this embodiment, oxygen delivery pressure can be set to an optimum value zone by zone, without performance being limited by the differences in flow rates at various locations in the piping network that result from variations in pressure drops within different regions of the piping network. This configuration also allows for a zoned-system architecture, with one or more pressure controllers and their corresponding sources of supplemental breathable oxygen, inlet valves, breathing devices and cabin air pressure transducers placed in various locations within the aircraft.

[0060] In a ninth embodiment of the invention, illustrated in FIG. 11, an emergency oxygen supply system 170 includes a source of supplemental breathable oxygen 172, such as one or more oxygen cylinders. In the limiting case of such an approach, each cabin occupant may be served by a separate one-person cylinder. A conduit 174 is connected to the source of supplemental breathable oxygen to provide a flow of oxygen, controlled by a relatively simple on-off inlet valve 176, such as a two-position solenoid valve, for example, to an individual breathing device 178, typically including a reservoir bag and an attached face mask. Such one-person, small oxygen cylinders and associated apparatus for the emergency oxygen supply system can be distributed throughout the passenger cabin area of an airplane. Each oxygen vessel is fitted with a simple pressure reducing regulator 180, with no altitude-compensating features included. Downstream of the inlet valve, a manifold 182 is interposed between the inlet valve and its associated reservoir bag.

[0061] A single pressure controller 184 is connected to and controls the operation of the inlet valve via a control line 186 in response to a first input signal received from a single pressure transducer P.sub.A (188), representing the cabin pressure and a corresponding altitude. The controller evaluates the pressure transducer signal and generates a single signal to the simple inlet valve. In this case, there is an intrinsic flow rate that would be achieved through each dispensing orifice if the simple inlet valve were to be continuously open. This intrinsic flow rate is a function of the output pressure from the pressure reducer and the properties of the dispensing orifices. Depending on the flow that is appropriate for the given altitude, the valve-operating signal is applied for a suitable fraction of the operating time. The flow rate achieved by the dispensing orifice is then equal to the intrinsic flow rate possible multiplied by the fraction of time the inlet valve is open. For example, if the intrinsic flow rate possible when the inlet valve is open continuously is 4 liters per minute and the valve is open 30% of the time, the flow rate achieved is 1.2 liters per minute. This configuration also allows for a zoned-system architecture, with one or more pressure controllers and their corresponding sources of supplemental breathable oxygen, inlet valves, breathing devices and cabin air pressure transducers placed in various locations within the aircraft.

[0062] As is illustrated in FIG. 12, in a variation of the ninth embodiment, in which the same elements from FIG. 11 are indicated by the same reference numbers as in FIG. 11, more than one cabin occupant may be served by each source of supplemental oxygen 172 of the emergency oxygen supply system 170. A conduit 174 is connected to the source of supplemental breathable oxygen to provide a flow of oxygen, controlled by a relatively simple on-off inlet valve 176, such as a two-position solenoid valve, for example, to a set 178 of breathing devices 179a, 179b, 179c, 179d, each typically including one or more individual reservoir bags and attached face masks. Each oxygen vessel is fitted with a simple pressure reducing regulator 180 with no altitude-compensating features included. Downstream of the inlet valve, a manifold 182, fitted with one or more dispensing orifices, is interposed between the inlet valve and its associated reservoir bag. Each manifold orifice typically supplies more than one oxygen mask. A single pressure controller 184 is connected to and controls the operation of the inlet valve via a control line 186 in response to a first input signal received from a single pressure transducer P.sub.A (188), representing the cabin pressure and a corresponding altitude. This configuration also allows for a zoned-system architecture, with one or more pressure controllers and their corresponding sources of supplemental breathable oxygen, inlet valves, breathing devices and cabin air pressure transducers placed in various locations within the aircraft.

[0063] In a tenth embodiment of the invention, illustrated in FIG. 13, an emergency oxygen supply system 190 includes a source of supplemental breathable oxygen 192, such as a relatively small oxygen cylinder. Such one-person, small oxygen cylinders and associated apparatus for the emergency oxygen supply system can be distributed throughout the passenger cabin area of an airplane. As is shown in FIG. 13, each cabin occupant may be served by a separate one-person cylinder, although more than one person may be served by each oxygen supply cylinder, as is further described below. A conduit 194 is connected to the source of supplemental breathable oxygen to provide a flow of oxygen, controlled by a relatively simple on-off inlet valve 196, such as a two-position solenoid valve, for example, to an individual breathing device 198, typically including a reservoir bag and an attached face mask. In this embodiment, a pressure reducer at the outlet of the local oxygen vessel is eliminated. Downstream of the inlet valve, a manifold 197 is interposed between the inlet valve and its associated reservoir bag.

[0064] A single pressure controller 200 is connected to the inlet valve and controls the operation of the inlet valve via a control line 202 in response to an input signal received from a single pressure transducer P.sub.A (204), representing the cabin pressure and a corresponding altitude. The controller evaluates the pressure transducer signal and generates a signal to the simple inlet valve. In this case, there is an intrinsic flow rate that would be achieved through each dispensing orifice if the simple inlet valves were continuously open. This intrinsic flow rate is a function of the output pressure from the pressure reducer and the properties of the dispensing orifices. Depending on the flow that is appropriate for the given altitude, the valve-operating signal is applied for a suitable fraction of the operating time. The flow rate achieved by each dispensing orifice is then equal to the intrinsic flow rate possible multiplied by the fraction of time the inlet valve is open. For example, if the intrinsic flow rate possible when the inlet valve is open continuously is 4 liters per minute and the inlet valve is open 30% of the time, the flow rate achieved is 1.2 liters per minute. This configuration also allows for a zoned-system architecture, with one or more pressure controllers and their corresponding sources of supplemental breathable oxygen, inlet valves, breathing devices and cabin air pressure transducers placed in various locations within the aircraft.

[0065] As is illustrated in FIG. 14, in a variation of the tenth embodiment, in which the same elements from FIG. 13 are indicated by the same reference numbers as in FIG. 13, more than one cabin occupant may be served by each source of supplemental breathing oxygen 192 of the emergency oxygen supply system 190. A conduit 194 is connected to the source of supplemental breathable oxygen to provide a flow of oxygen, controlled by a relatively simple electrical on-off inlet valve 196, such as a two-position solenoid valve, for example, to a corresponding set 198 of breathing devices 199a, 199b, 199c, 199d, typically including one or more individual reservoir bags and attached face masks, respectively. Downstream of the inlet valve, a manifold 197, fitted with one or more dispensing orifices, is interposed between the inlet valve and its associated reservoir bag. A single pressure controller 200 is connected to the inlet valve and controls the operation of the inlet valve via a network of control lines 202 in response to a first input signal received from a single pressure transducer P.sub.A (204) representing the cabin pressure and a corresponding altitude. An intrinsic flow rate can be achieved at any given point in time through each dispensing orifice when the simple inlet valve is open continuously. However, this flow rate changes as the pressure in the oxygen storage vessel upstream of the dispensing orifice decays with the passage of time during operation of the equipment. The flow rate is a function of the operating time history and the pressure decay properties of the oxygen storage unit, as well as the properties of the dispensing orifices themselves. In this context, the operating time refers to the time the valve remains open, which is not necessarily equal to the total elapsed time since the beginning of a decompression incident causing supplemental oxygen to be used. This configuration also allows for a zoned-system architecture, with one or more pressure controllers and their corresponding sources of supplemental breathable oxygen, inlet valves, breathing devices and cabin air pressure transducers placed in various locations within the aircraft.

[0066] The single pressure transducer senses the cabin pressure altitude. The controller contains information that mathematically describes the way in which the pressure in the oxygen storage vessel decays as a function of operating time. The controller also measures and retains information about the operating time history during the period of use. The controller evaluates the pressure transducer signal and the operating time history and generates a single signal to the simple inlet valve. Depending on the flow that is appropriate for the combination of given altitude and given previous operating time history, the valve-operating signal is applied for a suitable fraction of the operating time. The flow rate achieved by each dispensing orifice is then equal to the intrinsic flow rate possible multiplied by the fraction of time the valve is open.

[0067] As an illustrative example, assume that the cabin pressure altitude is such that it is desired to deliver a flow rate of 2 liters per minute. Initially, the combination of contained pressure within the cylinder and the orifice characteristics would allow a flow of 5 liters per minute if the valve were open continuously. Because appropriate data are stored in the controller, the controller initially opens the valve 40% of the time, resulting in an appropriate 2 liter per minute flow rate. After some period of operating time has elapsed, the contents within the cylinder are partially discharged, lowering the contained pressure to an extent that a flow of 3 liters per minute would be possible if the valve were continuously open. By tracking the history of how long the valve has been open and using this stored information in combination with other stored information about the properties of the equipment, the controller can calculate that this condition prevails. The controller then opens the valve 67% of the time to continue delivering a flow rate of 2 liters per minute.

[0068] In many gaseous oxygen systems, at the start of operation a surge of oxygen is delivered for a few seconds to provide sufficient pressure to operate pneumatic latches that release the doors of the compartments where the oxygen masks are stowed prior to need. It will be apparent that within the teachings of this invention such a surge could be provided by the controller if desired.

[0069] Another way of opening the doors of the compartments is by an electrical latch. Usually, power for the latch circuit would be supplied independently of the power supplied to the electrical valves used in my invention. However, the electrical latches could be wired into the same circuit as these valves. In that case, the latches would draw power each time the valve was powered. This added power consumption might be an acceptable trade-off for elimination of the weight associated with the wires of a second power circuit for the latches.

[0070] A latch may also be equipped with a feature such that energizing the latch to release the doors also performs an action that opens a contact within the latch, interrupting continuity through the latch so that the latch cannot draw power again until a contact position is reset. In this case, the latch draws power needed to release the door only the first time the circuit is energized, but the door latch does not draw power when subsequent power pulses are applied to the circuit. A suitable series-parallel circuit would permit the valve to continue to operate without continuity through the latch.

[0071] In many oxygen systems, some redundant components are sometimes installed to enhance the overall system reliability. This practice could be followed within the scope of my invention. For example, although the embodiments as described above have mentioned the use of a single pressure transducer to sense cabin altitude pressure, adding a second redundant transducer would lie within the intended scope of my invention. Similarly, the use of wiring arrangements that provide redundant connections to protect against possible deactivation of the equipment due to damage to the wiring would lie within the intended scope of my invention.

[0072] It will be apparent from the foregoing that, while particular forms of the invention have been illustrated and described, various modifications can be made without departing from the spirit and scope of the invention. Accordingly, it is not intended that the invention be limited, except as by the appended claims.