Abstract: A fire suppression system may comprise a shape memory actuation system. The shape memory actuation system may be configured as a retainer that retains a plug and/or a disk. The shape memory actuation system may be a shape memory plug that is configured to discharge from a vessel exhaust port. The shape memory actuation system may be deployable in response to an electrical stimulus (e.g., resistive heating causing the shape memory alloy to have a temperature exceeding a transition temperature).

Abstract: A pneumatic detection system and a method of forming the pneumatic detection system are described. The system includes a sealed tube, a refrigerant disposed within the sealed tube, and a switch configured to be activated based on a specified pressure being reached within the sealed tube.

Abstract: In various embodiments, a fire suppression system includes a high rate discharge system and a low rate discharge system. The low rate discharge system may comprise components that are capable of varying mass flow of a fire suppression agent in term of the ambient conditions of the aircraft structure. In this regard, the low rate discharge system may comprise a valve that is configured to sense at least one of the ambient pressure and ambient temperature of an aircraft structure.

Abstract: According to one aspect, a fire extinguisher includes a fire extinguisher reservoir and a fire extinguisher outlet burst disc that forms a discharge barrier between the fire extinguisher reservoir and a discharge head to retain a pressurized fire extinguishing agent at an internal fire extinguisher pressure within the fire extinguisher reservoir. A cutter is detained within the fire extinguisher proximate the fire extinguisher outlet burst disc. An interior container within the fire extinguisher reservoir has a container pressure and is sealed with a container burst disc. An activation device having a piercing member is operable to pierce the container burst disc and diffuse the container pressure to create a pressure differential relative to the internal fire extinguisher pressure at the cutter, thereby driving the cutter through the fire extinguisher outlet burst disc to release the pressurized fire extinguishing agent through the discharge head.

Abstract: In various embodiments, a fire suppression system includes a high rate discharge system and a low rate discharge system. The low rate discharge system may comprise components that are capable of varying mass flow of a fire suppression agent in term of the ambient conditions of the aircraft structure. In this regard, the low rate discharge system may comprise a valve that is configured to sense at least one of the ambient pressure and ambient temperature of an aircraft structure.

Abstract: A fire suppression system may comprise a shape memory actuation system. The shape memory actuation system may be configured as a retainer that retains a plug and/or a disk. The shape memory actuation system may be a shape memory plug that is configured to discharge from a vessel exhaust port. The shape memory actuation system may be deployable in response to an electrical stimulus (e.g., resistive heating causing the shape memory alloy to have a temperature exceeding a transition temperature).

Abstract: In various embodiments, a fire suppression system includes a high rate discharge system and a low rate discharge system. The low rate discharge system may comprise components that are capable of varying mass flow of a fire suppression agent in term of the ambient conditions of the aircraft structure. In this regard, the low rate discharge system may comprise a valve that is configured to sense at least one of the ambient pressure and ambient temperature of an aircraft structure.

Abstract: A fire suppression system may comprise a shape memory actuation system. The shape memory actuation system may be configured as a retainer that retains a plug and/or a disk. The shape memory actuation system may be a shape memory plug that is configured to discharge from a vessel exhaust port. The shape memory actuation system may be deployable in response to an electrical stimulus (e.g., resistive heating causing the shape memory alloy to have a temperature exceeding a transition temperature).

Abstract: According to one aspect, a fire extinguisher includes a fire extinguisher reservoir and a fire extinguisher outlet burst disc that forms a discharge barrier between the fire extinguisher reservoir and a discharge head to retain a pressurized fire extinguishing agent at an internal fire extinguisher pressure within the fire extinguisher reservoir. A cutter is detained within the fire extinguisher proximate the fire extinguisher outlet burst disc. An interior container within the fire extinguisher reservoir has a container pressure and is sealed with a container burst disc. An activation device having a piercing member is operable to pierce the container burst disc and diffuse the container pressure to create a pressure differential relative to the internal fire extinguisher pressure at the cutter, thereby driving the cutter through the fire extinguisher outlet burst disc to release the pressurized fire extinguishing agent through the discharge head.

Abstract: A pneumatic detection system and a method of forming the pneumatic detection system are described. The system includes a sealed tube, a refrigerant disposed within the sealed tube, and a switch configured to be activated based on a specified pressure being reached within the sealed tube.

Abstract: A fire suppression system may comprise a shape memory actuation system. The shape memory actuation system may be configured as a retainer that retains a plug and/or a disk. The shape memory actuation system may be a shape memory plug that is configured to discharge from a vessel exhaust port. The shape memory actuation system may be deployable in response to an electrical stimulus (e.g., resistive heating causing the shape memory alloy to have a temperature exceeding a transition temperature).

Abstract: In various embodiments, a fire suppression system includes a high rate discharge system and a low rate discharge system. The low rate discharge system may comprise components that are capable of varying mass flow of a fire suppression agent in term of the ambient conditions of the aircraft structure. In this regard, the low rate discharge system may comprise a valve that is configured to sense at least one of the ambient pressure and ambient temperature of an aircraft structure.

Abstract: An integrated switch to indicate pressure changes in an environment includes a housing with a cavity between a first retainer portion and a second retainer portion, a first diaphragm held in the cavity of the housing to indicate fault conditions, and a second diaphragm held in the cavity of the housing to indicate alarm conditions.

Abstract: An integrated switch to indicate pressure changes in an environment includes a housing with a cavity between a first retainer portion and a second retainer portion, a first diaphragm held in the cavity of the housing to indicate fault conditions, and a second diaphragm held in the cavity of the housing to indicate alarm conditions.