Breathing and acceleration protection apparatus for aircraft crew members

Claim 2

A breathing and acceleration protection apparatus for the crew of fighter aircraft, having a source of pressurized gas, anti-g regulator valve means having an input connected to said source and an output constructed to be connected to inflatable trouser pockets of a g-suit carried by a member of said crew, and a demand regulator arranged to deliver respiratory gas to said crew member, wherein said anti-g regulator valve means include an inertia body movable along a predetermined direction responsive to acceleration along said direction, valve means controlled by said inertia body and controlling the pressure in said pockets as an increasing function of the acceleration, and additional means responsive to the aircraft altitude for setting a pressure in said pockets at a value which increases with altitude in the absence of acceleration.

Claim 3

An apparatus according to claim 1, wherein said additional means comprises a capsule subjected to the pressure in the aircraft cabin and controlling communication between said cabin and a pilot chamber of said valve means.

Claim 4

An apparatus according to claim 1, wherein said additional means comprises a relay chamber having an inlet continuously communicating with a pilot chamber of a main valve controlling flow of gas from said source to said pockets, and two outlets, a double action valve in said relay chamber arranged for communicating said inlet to that of the outlets where the higher pressure prevails, one of said outlets being connected to said valve means and the other of said outlets being connected to the outlet of the demand regulator.

Claim 5

An apparatus according to claim 1, wherein the inertia body is suspended by a diaphragm placed perpendicular to the axis of the accelerations to be detected and in a plane passing approximately through the center of gravity of the mass.

Claim 6

An apparatus according to claim 4, wherein said body is formed with a surface situated perpendicularly to the direction of the accelerations to be detected, passing through the center of gravity of the body and arranged for cooperation with a fixed seat and is biased away from said seat by resilient return means.

Claim 7

An apparatus according to claim 1, wherein said source is a source of pressurized oxygen and said anti-g regulator comprises an ejector nozzle for diluting the oxygen flow with air coming from the aircraft cabin.

Claim 8

An apparatus according to claim 1, further comprising means for increasing the respiratory gas pressure responsive to acceleration.

Claim 9

An apparatus according to claim 7, wherein the overpressure is controlled by an additional inertia body arranged to cause an overpressure less than that controlled by the inertia body of the anti-g regulator.

Claim 10

An apparatus according to claim 1, further comprising at least one double action valve for mixing orders coming from different regulating members determining the pressure in the pockets of the protective trousers.

Claim 11

An apparatus according to claim 1, wherein said anti-g regulator valve means further comprises means for providing a predetermined preinflation of the trouser pockets responsive to an electrical order from the flight controls when the latter are placed in a position which will cause an acceleration.

Claim 12

A breathing and acceleration protection apparatus for the crew of fighter aircraft, having a source of pressurized gas, anti-g regulator valve means having an input connected to said source and an output constructed to be connected to inflatable trouser pockets of a g-suit carried by a member of said crew, and a demand regulator arranged to deliver respiratory gas to said crew member, wherein said anti-g regulator valve means includes: a main valve having a movable member controlling communication between said source and said trouser pockets and limiting a control chamber connected to said source via a restricted passage, said movable member opening a communication between said source and pockets upon a decrease of the pressure in said control chamber, a pilot valve controlling the pressure in said control chamber responsive to the gas pressure in a relay chamber formed with an inlet continuously communicated with said pilot valve and with two outlets, double action valve means in said relay chamber for automatically communicating said inlet to that of said outlets in which the higher gas pressure prevails, acceleration responsive means connected to the first of said outlets, controlling communication between said outlet and a low pressure, and arranged to close said communication upon occurrence of an acceleration in a predetermined direction, and a line for communicating the second of said outlets to a respiratory gas circuit in said demand regulator, wherein a pressure in excess of the ambient atmosphere prevails under high altitude conditions.

Claim 13

A breathing and acceleration protection apparatus for the crew of fighter aircraft, having a source of pressurized gas, anti-g regulator valve means having an input connected to said source and an output constructed to be connected to inflatable trouser pockets of a g-suit carried by a member of said crew, and a demand regulator arranged to deliver respiratory gas to said crew member, wherein said anti-g regulator valve means includes: a main valve having a movable member controlling communication between said source and said trouser pockets and limiting a control chamber connected to said source via a restricted passage, said movable member opening a communication between said source and pockets upon a decrease of the pressure in said control chamber, a pilot valve controlling the pressure in said control chamber responsive to the gas pressure in a relay chamber formed with an inlet continuously communicated with said pilot valve and with two outlets, double action valve means in said relay chamber for automatically communicating said inlet to that of said outlets in which the higher gas pressure prevails, acceleration responsive means connected to the first of said outlets, controlling communication between said outlet and a low pressure, and arranged to close said communication upon occurrence of an acceleration in a predetermined direction, and a line for communicating the second of said outlets to a respiratory gas circuit in said demand regulator, wherein a pressure in excess of the ambient atmosphere prevails under high altitude conditions.

Claim 14

An apparatus according to claim 11, further comprising a pressurized waistcoat for said crew member, wherein said breathing regulator is constructed for pressurizing pockets in said waistcoat and said inflatable trouser pockets upon occurence of high altitude conditions.

Claim 15

An apparatus according to claim 1 or 12, comprising a main supply source of oxygen carried by the aircraft, and an emergency oxygen source carried by an ejectable seat of the crew member, having means for inhibiting supply of the trouser pockets responsive to acceleration after ejection.

Claim 16

A breathing and acceleration protection apparatus for the crew of fighter aircraft, having: a source of pressurized gas, anti-g regulator valve means having an input connected to said source and an output constructed to be connected to inflatable trouser pockets of a g-suit arranged to be carried by a member of said crew, and a demand regulator arranged to deliver respiratory gas to said crew member, wherein said anti-g regulator valve means include a pressure controlled main valve, an inertia body movable along a predetermined direction responsive to acceleration along said direction, a second valve controlled by said inertia body and associated with said main valve so that said main valve controls the pressure in said pockets as an increasing function of the acceleration sensed by said inertia body, and additional means responsive to the aircraft altitude and associated with said main valve so that said main valve sets a minimum pressure in said pockets at a value which increases with altitude.

Claim 17

A breathing and acceleration protection apparatus for the crew of fighter aircraft, having: a source of pressurized gas, anti-g regulator valve means having an input connected to said source and an output constructed to be connected to inflatable trouser pockets of a g-suit arranged to be carried by a member of said crew, and a demand regulator arranged to deliver respiratory gas to said crew member, wherein said anti-g regulator valve means include a pressure controlled main valve, an inertia body movable along a predetermined direction responsive to acceleration along said direction, a second valve controlled by said inertia body and associated with said main valve so that said main valve controls the pressure in said pockets as an increasing function of the acceleration sensed by said inertia body, and additional means responsive to the aircraft altitude and associated with said main valve so that said main valve sets a minimum pressure in said pockets at a value which increases with altitude.