Abstract: A fire suppression system for a use in a fire zone is provided. The fire suppression system includes a case, a fire extinguishing container, a battery assembly, a control assembly and a sensor device. The sensor device is configured to detect a potential fire hazard within the fire zone and signal the discharge of a fire extinguishing material outside the case and into the fire zone upon the detection of a potential fire hazard. The fire suppression system can further include a smoke generating container configured to release a smoke generating agent outside of the fire zone upon the detection of a potential fire hazard in order notify operators and systems of a potential fire hazard occurring within the fire zone.

Abstract: A fire suppression system for a use in a fire zone is provided. The fire suppression system includes a case, a fire extinguishing container, a battery assembly, a control assembly and a sensor device. The sensor device is configured to detect a potential fire hazard within the fire zone and signal the discharge of a fire extinguishing material outside the case and into the fire zone upon the detection of a potential fire hazard. The fire suppression system can further include a smoke generating container configured to release a smoke generating agent outside of the fire zone upon the detection of a potential fire hazard in order notify operators and systems of a potential fire hazard occurring within the fire zone.

Abstract: A control head for controlling the discharge of pressurized extinguishing agent from a container in an aircraft fire extinguishing system. The control head is hexagonal and is provided with an outlet fitting, a fill valve, an actuator body, a pressure switch and a pressure gauge. Each component can be threaded into any of the side faces or the end face of the control head so that the limited space available within the aircraft can be accommodated. An electrical detonator within the actuator body can be exploded to rupture a pair of frangible discs in succession. This opens a flow path for the extinguishant which is then discharged from the bottle to a delivery line which distributes it to the area of the fire. The detonator and its electrical heads are hermetically sealed in the actuator body to prevent contamination.

Abstract: An aircraft fire protection system includes a plurality of extinguishant bottles which can be detonated to deliver extinguishant into a manifold and then to selected fire zones through valves associated with the respective fire zones. Solid state control circuitry opens the appropriate valve when a corresponding push button switch is initially depressed and detonates one or more bottles in sequence when the same switch is subsequently depressed one or more times. A manual crash switch opens all valves when depressed once and discharges all bottles when depressed again. An automatic crash switch opens all valves and detonates all bottles if the aircraft should crash. A test circuit operates in a test mode to open all valves in sequence and to simulate sequential detonation of all bottles by applying low level current to the bottle detonator circuits.

Abstract: An aircraft fire protection system includes a plurality of extinguishant bottles which can be detonated to deliver extinguishant into a manifold and then to selected fire zones through valves associated with the respective fire zones. Solid state control circuitry opens the appropriate valve when a corresponding push button switch is initially depressed and detonates one or more bottles in sequence when the same switch is subsequently depressed one or more times. A manual crash switch opens all valves when depressed once and discharges all bottles when depressed again. An automatic crash switch opens all valves and detonates all bottles if the aircraft should crash. A test circuit operates in a test mode to open all valves in sequence and to simulate sequential detonation of all bottles by applying low level current to the bottle detonator circuits.

Abstract: A fire protection system is disclosed herein for use in aircraft equipped with engine and fuselage compartments. In the preferred and illustrated embodiment, the fire protection system utilizes a plurality of containers of extinguishant, the containers being connected to a common manifold. The manifold connects to a number of solenoid operated, feedback connected zone valves, each of which is connected through a distribution line to a specified fire zone of the aircraft. A control system is included which closes certain fire zone valves, opens the one where opening is required to direct the extinguishant to that particular zone of the aircraft, and then opens an individual container. The control system additionally includes sensors at selected locations around the aircraft to provide a warning to an operator who manually operates the system.