Fluid supply systems

• US 4,412,419 A
• Filed: 09/25/1981
• Issued: 11/01/1983
• Est. Priority Date: 09/18/1978
• Status: Expired due to Fees

• Current Assignee: British Aerospace, Inc. (BAE Systems Plc)
• Original Assignee: British Aerospace, Inc. (BAE Systems Plc)
• Inventors: Thomas, Alan V., Bone, Geoffrey E.
• Primary Examiner(s): Burns, Wendell E.
• Application Number:
  US06/305,669
• Time in Patent Office: 767 Days
• Field of Search: 60/634, 60/375, 60/632
• US Class Current: 60/634
• CPC Class Codes: F15B 1/08 using a gas cushion; Gas charging devices; Indicators or floats therefor
• CPC Class Codes: F15B 1/26 Supply reservoir or sump assemblies
• CPC Class Codes: F15B 11/0725 with the driving energy being derived from a pneumatic system, a subsequent hydraulic system displacing or controlling the output element
• CPC Class Codes: F15B 15/19 Pyrotechnical actuators
• CPC Class Codes: F15B 2201/205 using gas
• CPC Class Codes: F15B 2201/3153 the flexible separating means being bellows
• CPC Class Codes: F15B 2201/411 having valve means
• CPC Class Codes: F15B 2201/51 Pressure detection
• CPC Class Codes: F42B 3/04 for producing gas under pressure generators of inflation fluid especially adapted for vehicle air bags B60R21/26

Abstract

The invention relates to a fluid supply system and seeks to provide a simpler, safer but reliable system than at present known. The fluid supply system comprises a multi-charge solid propellant gas generator and a fluid explusion unit integrated into a single unit, the gas generator being provided in a cap (8) for a chamber (1) having a gas portion (3) and a fluid portion (2) and a movable partition (4) between these two portions operable to expel fluid from the chamber when the gas generator is rendered operative. The system also comprises ignition control means (22) operable to control the ignition of the solid propellant charges (13) when required to give a fully controllable system output.

The system can be designed for supplying under pressure fluids such as hydraulic oil, fuels, oxidents and water and is particularly useful in aerospace applications.

Claims

1. A fluid supply system comprising a chamber having a portion for containing a working fluid, a portion for containing a gas for pressurizing the working fluid, a movable partition separating the fluid portion from the gas portion of the chamber, an inlet for the gas and an outlet for the working fluid, a member operable to close the inlet and carrying solid propellant charge means, and ignition control means for the solid propellant charge means, characterized in that the solid propellant charge means comprise a plurality of individual charges, and in that the ignition control means is operable to ignite each charge as and when required to produce a pressurized gas which enters the gas portion of the chamber and moves the partition in the chamber to pressurize the working fluid and expel the same through the outlet, the ignition control means comprising pulse generating means, counter means responsive to the output of the pulse generating means, gate means responsive to the output of the counter means, and ignition circuits responsive to the respective outputs of the gate means, whereby the solid propellant charges are ignited serially.

2. A system according to claim 1, characterized in that the ignition control means further comprises a pressure sensor operable to sense the pressure in the fluid or gas portion of the chamber and operate switch means if the sensed pressure is below a predetermined value, the switch means then initiating the remainder of the ignition control means, and in that the counter means remains energized but the pulse generating means does not when the switch means is deactuated so that serial ignition of the solid propellant charges is resumed immediately the switch means is reactuated.

3. A system according to claim 1 or 2, characterized in that the pulse generating means comprises an oscillator.

4. A system according to claim 3, characterized in that each solid propellant charge is in the form of a capsule removably attached to the member carrying the same and comprising a container in which are mounted a slug of solid propellant and an igniter for the propellant, a frangible member being provided to separate the charge from the gas portion of the chamber.

5. A system according to claim 3, characterized in that each charge is embodied with the member carrying the same and comprises a slug of solid propellant and an igniter for the propellant, a frangible member being provided to separate the charge from the gas portion of the chamber.

6. A system according to claim 3, characterized in that each charge comprises an annular slug of solid propellant and an igniter for the propellant, the slugs being stacked one next to another and separated by an apertured member and each slug being separated from the gas portion of the chamber by a frangible member.

7. A system according to claim 6, characterized in that the apertures in the members separating the slugs of propellant are aligned with each other and with the bore formed by the stacked slugs to permit gas generated by an one charge to flow into the gas portion of the chamber.

8. A system according to claim 4, characterized in that each frangible member comprises a heat reflective layer to reduce radiative heat transfer from the gas portion of the chamber to the unignited charges, and an insulative layer to reduce conductive heat transfer.

9. A system according to claim 5, characterized in that each frangible member comprises a heat reflective layer to reduce radiative heat transfer from the gas portion of the chamber to the unignited charges, and an insulative layer to reduce conductive heat transfer.

10. A system according to claim 7, characterized in that each frangible member comprises a heat reflective layer to reduce radiative heat transfer from the gas portion of the chamber to the unignited charges, and an insulative layer to reduce conductive heat transfer.

11. A system according to claim 10, characterized in that the reflective layer is metallic and the insulative layer is ceramic.

12. A system according to claim 11 characterized in that the outlet of the chamber is fitted with a release valve which is automatically opened on energization of the ignition control means.

14. A system according to claim 13 or 1, wherein the gas inlet occupies one end of the chamber and the member carrying the solid propellant charges is in the form of an end cap.

15. A system according to claim 13 or 1, wherein each solid propellant charge is in the form of a capsule removably attached to the member carrying the same and comprising a container in which are mounted a slug of solid propellant and an igniter for the propellant, a frangible member being provided to separate the charge from the gas portion of the chamber.

16. A system according to claim 13 or 1, wherein each charge is embodied with the member carrying the same and comprises a slug of solid propellant and an igniter for the propellant, a frangible member being provided to separate the charge from the gas portion of the chamber.

17. A system according to claim 15, wherein each frangible member is a disc.

18. A system according to claim 13 or 1, wherein each charge comprises an annular slug of solid propellant and an igniter for the propellant, the slugs being stacked one next to another and separated by an apertured member and each slug being separated from the gas portion of the chamber by a frangible member.

19. A system according to claim 18, wherein each frangible member is in the form of a ring fitting within the bore of the associated slug of propellant.

20. A system according to claim 18, wherein the apertures in the members separating the slugs of propellant are aligned with each other and with the bore formed by the stacked slugs to permit gas generated by any one charge to flow into the gas portion of the chamber.

21. A system according to claim 18, wherein the apertured members are located by rings surrounding the slugs of propellant.

22. A system according to claim 15, wherein each frangible member comprises a heat reflective layer to reduce radiative heat transfer from the gas portion of the chamber to the unignited charges, and an insulative layer to reduce conductive heat transfer.

23. A system according to claim 22, wherein the reflective layer is metallic and the insulative layer is ceramic.

27. A system according to claim 25, 26, 1 or 2, wherein each igniter circuit comprises an amplifier.

28. A system according to claim 13 or 1, wherein the movable partition in the chamber comprises a bellows sealed to the chamber.

29. A system according to claim 13 or 1 wherein the movable partition in the chamber comprises a piston.

13. A fluid supply system comprising a chamber having a portion for containing a working fluid, a portion for containing a gas for pressurising the working fluid, a movable partition separating the fluid portion from the gas portion of the chamber, an inlet for the gas and an outlet for the working fluid, the inlet being closable by a member carrying a plurality solid propellant charges, the system further comprising ignition control means for the solid propellant charges and being such that in operation a charge is ignited to produce a pressurised gas which enters the gas portion of the chamber and moves the partition in the chamber to pressurise the working fluid and expel the same through the chamber outlet, each charge being ignited as and when required.

24. A system according to claim 13, wherein the ignition control means comprise a pressure sensor operable to sense the pressure in the fluid or gas portion of the chamber and operate switch means if the sensed pressure is below a predetermined value, the switch means then initiating the remainder of the ignition control means.

25. A system according to claim 24, wherein the ignition control means further comprises an oscillator rendered operative when the switch means is actuated, a counter responsive to the output of the oscillator, gate means responsive to the output of the counter and ignition circuits responsive to the respective outputs of the gate means, whereby the solid propellant charges are ignited serially.

26. A system according to claim 25, wherein the counter remains energised but the oscillator does not when the switch means is deactuated so that serial ignition of the solid propellant charges is resumed immediately the switch means are re-actuated.