Flight recorder deployment mechanism

• US 9,296,489 B2
• Filed: 03/13/2014
• Issued: 03/29/2016
• Est. Priority Date: 03/14/2013
• Status: Active Grant

• Current Assignee: DRS C3 & Aviation Co. (Michigan) (Leonardo S.p.A.)
• Original Assignee: DRS C3 & Aviation Co. (Michigan) (Leonardo S.p.A.)
• Inventors: van den Heuvel, Blake, Kaufmann, Ari, Woozley, Mark, Sterrantino, Peter
• Primary Examiner(s): Lee, Benjamin P
• Application Number:
  US14/208,179
• Publication Number:
  US 20140263839A1
• Time in Patent Office: 747 Days
• Field of Search: 244/1.R, 701/14, 701/35, 701/33.4, 312/223.2, 312/223.3, 361/679.01, 455/96, 455/98
• US Class Current: 1/1
• CPC Class Codes: B64D 1/02 Dropping, ejecting, or releasing articles jettisonable fuel reservoirs B64D37/12
• CPC Class Codes: B64D 2045/0065 Black boxes, devices automatically broadcasting distress signals
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00

Abstract

Embodiments of the invention are directed to a release device that uses an electro-mechanical mechanism instead of an explosive to deploy a deployable unit such as a flight data recorder. In one embodiment of the invention, a solenoid is activated that causes a piston surrounded by the solenoid to move which moves a pin attached to the piston and allows a spring to decompress and deploy a deployable unit. In some embodiments, a release actuator mechanism, a pneumatic actuator mechanism, a shape memory alloy or a combination thereof may be used to affect deployment of the deployable unit.

Claims

1. A release device for a deployable unit, the release device comprising:

a biasing element for interfacing with the deployable unit; and

an electrical device operationally coupled to the biasing element,

wherein the release device is free of an explosive,

wherein the deployable unit is a deployable flight recorder, the biasing element is a spring and the electrical device comprises a solenoid, and wherein the release device further comprises;

a piston within the solenoid; and

a pin coupled to the piston,

wherein the pin is at least partially surrounded by the spring,

wherein the pin comprises a plurality of ridges, and wherein the release device further comprises a plurality of ball bearings in contact with at least one ridge in the plurality of ridges.

2. The release device of claim 1, wherein the release device further comprises a housing comprising a channel which receives the pin.

3. The release device of claim 1, wherein the deployable unit comprises one or more catches and wherein at least one catch engages with at least one of the plurality of ball bearings to keep the spring compressed.

4. The release device of claim 1, further comprising a wire coupled to the solenoid, wherein the wire is configured to receive an electrical activation signal.

5. The release device of claim 1, wherein the release device comprises a shape memory alloy.

6. The release device of claim 1, wherein the electrical device comprises an electrical switch.

7. The release device of claim 1, wherein the electrical device comprises a solenoid, a switch or a relay.

8. An assembly comprising:

the release device of claim 1; and

the deployable unit.

9. A system comprising the assembly of claim 8;

and

an aircraft coupled to the assembly.

10. A method for deploying a deployable unit, the method comprising:

receiving an electrical activation signal, by an electrical device, in response to an unexpected event; and

in response to receiving the electrical activation signal, by the electrical device, activating a biasing element interfacing with the deployable unit to allow the biasing element to expand to an extended configuration from a retracted configuration and deploy the deployable unit without the use of explosives, and

wherein the method further comprises;

moving a piston operationally coupled to the electrical device;

moving a pin coupled to the piston; and

withdrawing one or more ball bearings engaged with the pin from apertures in a housing and a catch in the deployable unit.

11. The method of claim 10, further comprising:

prior to receiving the electrical activation signal, compressing the biasing element to keep the deployable unit in an undeployed state.

12. The method of claim 10, wherein the electrical device comprises a solenoid, the biasing element is a spring and the deployable unit is a deployable flight recorder.

13. The method of claim 10, wherein the biasing element comprises a shape memory alloy.