Flight recorder deployment mechanism

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.

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.   
     
     
         2 . The release device of  claim 1 , 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.   
     
     
         3 . (canceled) 
     
     
         4 . The release device of  claim 2 , wherein the release device further comprises a housing comprising a channel which receives the pin. 
     
     
         5 . (canceled) 
     
     
         6 . The release device of  claim 2 , further comprising a wire coupled to the solenoid, wherein the wire is configured to receive an electrical activation signal. 
     
     
         7 . The release device of  claim 1 , wherein the release device comprises a shape memory alloy. 
     
     
         8 . The release device of  claim 1  wherein the electrical device comprises an electrical switch. 
     
     
         9 . The release device of  claim 1 , wherein the biasing element comprises a pneumatic actuator device coupled to the electrical device. 
     
     
         10 . The release device of  claim 9 , wherein the pneumatic actuator device comprises a compressed air device. 
     
     
         11 . The release device of  claim 9 , wherein the pneumatic actuator device comprises an inert gas device. 
     
     
         12 . The release device of  claim 1 , wherein the electrical device comprises a solenoid, a switch or a relay. 
     
     
         13 . The release device of  claim 1  wherein the biasing element is a spring. 
     
     
         14 . An assembly comprising:
 the release device of  claim 1 ; and   the deployable unit.   
     
     
         15 . A system comprising the assembly of  claim 14 ; and an aircraft coupled to the assembly. 
     
     
         16 . 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.   
     
     
         17 . The method of  claim 16 , further comprising:
 prior to receiving the electrical activation signal, compressing the biasing element to keep the deployable unit in an undeployed state.   
     
     
         18 . (canceled) 
     
     
         19 . The method of  claim 16 , wherein the electrical device is a solenoid, the biasing element is a spring and the deployable unit is a deployable flight recorder. 
     
     
         20 . The method of  claim 16 , wherein the biasing element comprises a shape memory alloy.