Buoyancy system for an aircraft

Patent metadata

Field	Value
Publication number	US-9533757-B2
Application number	US-201414513508-A
Country	US
Kind code	B2
Filing date	Oct 14, 2014
Priority date	Oct 16, 2013
Publication date	Jan 3, 2017
Grant date	Jan 3, 2017

Abstract

A buoyancy system ( 10 ) for an aircraft ( 1 ), the buoyancy system ( 10 ) being provided with at least one inflatable float ( 15 ). The buoyancy system ( 10 ) has at least one inflator ( 25 ) and at least one actuator ( 30 ) interposed between the inflator ( 25 ) and a float ( 15 ), the actuator ( 30 ) having a cylinder ( 35 ) and a rod ( 40 ) partially received in the cylinder ( 35 ). The rod ( 40 ) is secured to a piston ( 50 ) defining a first chamber ( 61 ) within the cylinder ( 35 ) and in fluid flow communication with the inflator ( 25 ), and a second chamber ( 62 ) within the rod ( 40 ) and in fluid flow communication with the float ( 15 ), and the piston ( 50 ) has a channel ( 63 ) to put the first chamber ( 61 ) into fluid flow communication with the second chamber ( 62 ), the deployment device ( 20 ) having a shutter ( 70 ) for shutting the channel ( 63 ).

First claim

What is claimed is:

1. A buoyancy system for an aircraft, the buoyancy system comprising:
an inflatable float; and
a deployment device comprising an inflator and an actuator interposed between the inflator and the float, the actuator having a cylinder and a rod secured to the float, the rod being inserted in part in the cylinder and being slidable relative to the cylinder, the rod being secured to a piston, the piston co-operating with the cylinder to define a first chamber within the cylinder and co-operating with the rod to define a second chamber within the rod, the first chamber being in fluid flow communication with the inflator, while the second chamber is in fluid flow communication with the float, the piston having a channel for putting the first chamber into fluid flow communication with the second chamber;
the deployment device having a shutter for shutting the channel in a retracted position of the actuator so that gas fed to the first chamber causes the actuator to extend by the rod moving in translation and for not shutting the channel in an extended position of the actuator after the movement in translation, in order to enable the gas to inflate the float.

2. The buoyancy system according to claim 1 , wherein the shutter includes a finger extending in the cylinder, the finger penetrating into the channel when the actuator is retracted.

3. The buoyancy system according to claim 2 , wherein the finger is secured to an end wall of the cylinder.

4. The buoyancy system according to claim 1 , wherein the actuator includes an abutment to limit the extent to which the rod can be extended out from the cylinder.

5. The buoyancy system according to claim 1 , wherein the deployment device includes a strap fastened to the float in order at least to limit the freedom of movement of the float relative to the actuator.

6. The buoyancy system according to claim 5 , wherein the strap extends between the cylinder and an outer envelope of the float.

7. The buoyancy system according to claim 1 , wherein the deployment device includes at least one apron sheet fastened to the float in order at least to limit entry of water into a cabin facing the float.

8. The buoyancy system according to claim 1 , wherein the float is hollow and has a hollow float center, and the rod includes an elongate portion slidably received in the cylinder and followed by an angled portion passing through the hollow float center.

9. An aircraft provided with a fuselage, wherein the aircraft includes the buoyancy system according to claim 1 , the cylinder being fastened to the fuselage.

10. The aircraft of claim 9 , wherein the cylinder is secured inside a compartment in the fuselage on a first side of the fuselage.

11. The aircraft of claim 9 , further comprising a second inflatable float in fluid connection with a second deployment device, the second inflatable float being disposed on a second side, opposite a first side, of the fuselage.

12. A buoyancy system for an aircraft, the buoyancy system comprising:
an inflatable container defined by an outer envelope enabled to hold pressurized gas; and
a deployment device having an inflator and an actuator, the actuator being interposed between the inflator and the container, the actuator having a cylinder, a piston, and a rod, the rod having a first end section and a second end section, the first end section of the rod being disposed in the cylinder and slidable relative to the cylinder, the second end section of the rod being secured to the container, and the first end section of the rod being secured to a piston;
the piston cooperating with the cylinder and the rod to define a first chamber within the cylinder and a second chamber within the rod, the second chamber being interposed between the piston and the container;
the piston further comprising a channel fluidly communicating the first chamber with the second chamber; and
the first chamber fluidly communicating with the inflator and the second chamber fluidly communicating with the container such that entry of pressurized gas into the first chamber moves the actuator in translation from a retracted position to an extended position, allowing pressurized gas to inflate the container.

13. The buoyancy system of claim 12 , further comprising pipework fluidly communicating the first chamber with the inflator.

14. The buoyancy system of claim 12 , further comprising pipework fluidly communicating the second chamber with the container.

15. The buoyancy system of claim 12 , where the inflator is configured to remove pressurized gas from the container to retract the container.

16. The buoyancy system of claim 12 , further comprising a shutter for selectively shutting and opening the channel within the piston.

17. A buoyancy system for an aircraft, the buoyancy system comprising:
an inflatable envelope capable of holding pressurized gas; and
a deployment device in fluid communication with the envelope, the deployment device having an inflator and an actuator disposed between the inflator and the envelope, the actuator having a cylinder, a piston, and a rod having a first end section and a second end section, the first end section of the rod slidingly disposed within the cylinder, the second end section of the rod being connected with the envelope, and the first end section of the rod being connected with a piston;
the piston cooperating with the cylinder and the rod to define a first chamber within the cylinder and a second chamber within the rod, the second chamber disposed between the piston and the envelope;
the piston fluidly communicating the first chamber with the second chamber, with the first chamber fluidly communicating with the inflator and the second chamber fluidly communicating with the envelope.

18. The buoyancy system according to claim 17 , wherein the deployment device extends the actuator in order to cause the rod to move in translation relative to the cylinder as a result of the envelope being inflated.

19. The buoyancy system of claim 17 , further comprising pipework fluidly communicating the first chamber with the inflator.

20. The buoyancy system of claim 17 , further comprising pipework fluidly communicating the second chamber with the envelope.

Assignees

• Airbus Helicopters

Inventors

• Delorme Louis
• Lamarche Nicolas
• Ayache David
• Certain Bernard

Classifications

• B64D2201/00

  Airbags mounted in aircraft for any use · CPC title

• B64D25/00

  Emergency apparatus or devices, not otherwise provided for · CPC title

• B64C2025/325

  specially adapted for helicopters · CPC title

• B64C25/56 Primary

  inflatable · CPC title