Servo operated anti-G suit pressurization system

• US 4,534,338 A
• Filed: 05/24/1984
• Issued: 08/13/1985
• Est. Priority Date: 05/24/1984
• Status: Expired due to Fees

• Current Assignee: The United States of America As Represented By The Secretary of Agriculture
• Original Assignee: the united states of america as represented by the secretary of the navy
• Inventors: Crosbie, Richard J., Edwards, Paul R.
• Primary Examiner(s): Kaplan, G. L.
• Assistant Examiner(s): LEADER, WILLIAM T
• Application Number:
  US06/613,497
• Time in Patent Office: 446 Days
• Field of Search: 128/1 A, 128/30.2, 128/40, 137/38, 137/39
• US Class Current: 600/19
• CPC Class Codes: B64D 10/00 Flight suits helmets in general A42B3/00; breathing helmets A62B18/00
• CPC Class Codes: B64D 2010/002 Anti-g suits or garments
• CPC Class Codes: Y10T 137/0753 Control by change of position or inertia of system

Abstract

A servo operated system for controlling pressurization of an aircraft pils anti-G suit during high energy maneuvers has a servo operated control valve and a feedback loop controller for minimizing pressure lag in the suit. The controller has dual modes of operation: one for normal flight conditions and one for combat flight conditions. The normal flight mode provides nominal G-protection while the combat mode provides faster response by prepressurizing the anti-G suit to a bias level and lowering the G-force threshold. While in the combat mode, the crewman may select an adjustable pulsating signal to be superimposed on the prepressurization level to obtain additional comfort. Alternatively, he may select a superimposed pulsating signal which is synchronized with his own heartbeat to reinforce the pumping action of the heart.

Claims

1. In an aircraft, a system for rapidly pressurizing and controlling pressurization of an aircrewman'"'"'s anti-G suit, of the type, having a plurality of inflatable air bladders, comprising:

an accelerometer for providing a signal representative of G-forces incident along the vertical axis of the aircraft;

means for switching between two system operating modes, the first operating mode providing a first set of input signals, and the second operating mode providing a second set of input signals different from the first set;

multiple input control means responsive to the G-force signal and the first or second set of input signals for providing a control signal;

a control valve responsive to the control signal and formed to be connected for controlling the volume of air supplied to the anti-G suit; and

means responsive to the air pressure supplied to the anti-G suit and formed to be connected at the outlet of said control valve, for providing a feedback signal connectable through said switching means to said control means.

2. A system as recited in claim 1 wherein the mode switching means comprises:

a gang operated, multi-pole, double throw switch;

first means connected to said switch for providing a threshold signal representative of a threshold G-force;

second means connected to said switch for providing an adjustable prepressurized signal in the second operating mode; and

third means connected to said switch for providing an adjustable modulating signal in the second operating mode.

3. A system as recited in claim 2 wherein the threshold signal has one valve in the first operating mode and a lower value in the second operating mode.

4. A system as recited in claim 3 wherein the adjustable prepressurization signal means comprises:

a direct current voltage source; and

means for adjusting the amplitude of said voltage source.

5. A system as recited in claim 4 wherein the modulating signal means comprises:

a signal generator for providing a periodic pulsed signal; and

means for adjusting the amplitude of the periodic pulsed signal.

6. A system as recited in claim 5 wherein the modulating signal means further comprises:

an amplifier connected to receive a signal indicative of the aircrewman'"'"'s pulse for providing an amplified EKG signal;

means for adjusting the amplitude the EKG signal; and

means for selectively connecting said signal generator or said amplifier to said mode switching means.

7. A system as recited in claim 6 wherein the multiple input control means comprises:

comparator means connected to receive the G-force representative signal and the threshold signal for transmitting the G-force signal when it exceeds the threshold signal value; and

a differential amplifier connected to receive the G-force signal, the prepressurized signal, the modulating signal, and the feedback signal, for providing the control signal.

8. A system as recited in claim 7 further comprising a pressure relief valve for preventing pressurization of the anti-G suit above a predetermined level.

9. An anti-G suit pressurization system as recited in claim 8 further comprising:

means for providing sequential pressurization of the air bladders in the anti-G suit.

10. A system as recited in claim 1 wherein the control valve comprises:

a pneumatically actuated volume booster valve formed to be connected in the air supply line to the anti-G suit;

a servo-valve responsive to the control signal and formed to provide a pneumatic signal from the air supply to said volume booster valve; and

means for regulating and filtering the air supply to said servo-valve.

11. A system as recited in claim 1 wherein the feedback signal means comprises:

a pressure transducer formed to be connected at the outlet side of said control valve, and having its signal side connectable through said mode switching means to said multiple input control means in the first operating mode; and

a time delay circuit connected to the signal side of said pressure transducer, said time delay circuit being connectable through said mode switching means to said multiple input control means in the second operating mode, whereby a pressure feedback signal is provided to said control means.