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An automated fire protection system for a freighter such as an aircraft may include a single fire retardant source for a first deck and a second deck. The system may further include a plurality of sensors for detecting fire and a plurality of nozzles for dispersing the retardant, wherein each nozzle

An automated fire protection system for a freighter such as an aircraft may include a single fire retardant source for a first deck and a second deck. The system may further include a plurality of sensors for detecting fire and a plurality of nozzles for dispersing the retardant, wherein each nozzle is paired with one of the plurality of sensors. Once a fire is detected by one of the sensors, the fire protection system may eject fire retardant through only one or more nozzles paired with the sensor that detected the fire. Because retardant may be accurately dispersed close to the detected fire location through less than the plurality of nozzles, an amount of on-board retardant may be decreased, thereby decreasing weight of the fire suppression system. In an embodiment, the fire retardant may only be discharged during the descent, further decreasing the weight of the fire system.

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1. An aircraft fire suppression system for an aircraft comprising at least a first deck and a second deck, the fire suppression system, comprising: a fire retardant source; a primary valve configured to selectively control a supply of fire retardant from the fire retardant source;a first fire suppre

1. An aircraft fire suppression system for an aircraft comprising at least a first deck and a second deck, the fire suppression system, comprising: a fire retardant source; a primary valve configured to selectively control a supply of fire retardant from the fire retardant source;a first fire suppression system component for the first deck in selective fluid communication with the fire retardant source via the primary valve,comprising: a plurality of first sensors on the first deck for detecting a fire; anda plurality of first retardant nozzles on the first deck, wherein each first retardant nozzle is in fluid communication with the fire retardant source and each at least one first retardant nozzle is uniquely paired. one-to-one, with one of the first sensors; anda second fire suppression system component for the second deck in selective fluid communication with the fire retardant source via the primary valve,comprising: a plurality of second sensors on the second deck for detecting a fire; anda plurality of second retardant nozzles on the second deck, wherein each second retardant nozzle is in fluid communication with the fire retardant source and each at least one second retardant nozzle is uniquely paired, one-to-one, with one of the second sensors,wherein the first retardant nozzles and the second retardant nozzles are selectively operable to dispense fire retardant based on detection of a fire by the paired sensors,wherein the primary valve is configured to supply fire retardant to one of the first fire suppression system and the second fire suppression system based on a detection of a fire by one of the sensors of the first fire suppression system and the second fire suppression system;wherein each of the plurality of first sensors and the plurality of second sensors comprises a heat sensor, comprising:a hollow container having a first end and a second end;a solid material within the hollow container, wherein the solid material has a melting point higher than ambient and lower than a temperature encountered during a fire;a first electrode at the first end of the hollow container; anda second electrode at the second end of the hollow container, wherein the solid material is configured to melt and short the first electrode with the second electrode during a fire. 2. The aircraft fire suppression system of claim 1 wherein, upon detection of a fire by one of the plurality of sensors, the aircraft fire suppression system is configured to eject retardant from only the nozzle paired with the one of the plurality of sensors detecting the fire. 3. The aircraft fire suppression system of claim 1, further comprising: a first plurality of shipping containers on the first deck, wherein one first sensor from the plurality of first sensors directly overlies one of the plurality of first shipping containers; anda second plurality of shipping containers on the second deck, wherein one second sensor from the plurality of second sensors directly overlies one of the plurality of second shipping containers. 4. The aircraft fire suppression system of claim 1, wherein each heat sensor further comprises a wireless transmitter configured to output a wireless signal when the first electrode and the second electrode are shorted together. 5. The aircraft fire suppression system of claim 1, further comprising: a first plurality of shipping containers on the first deck and a second plurality of shipping containers on the second deck,wherein each of the first plurality of shipping containers and each of the second plurality of shipping containers comprises at least one aperture therein, wherein the at least one aperture in each container is configured to deliver a fire indicator to one of the plurality of sensors during a fire event within the container. 6. The aircraft fire suppression system of claim 1 wherein, upon detection of a fire by one of the plurality of first sensors on the first deck, the aircraft fire suppression system is configured to eject retardant from less than the plurality of first nozzles for a time period beginning with the detection of the fire and ending after the aircraft lands on the ground. 7. The aircraft fire suppression system of claim 1 wherein, upon detection of a fire by one of the plurality of first sensors on the first deck, the aircraft fire suppression system is configured to eject retardant from less than the plurality of first nozzles only during a period of time when the aircraft is descending and ending after the aircraft lands on the ground. 8. The aircraft fire suppression system of claim 1, further comprising: a conduit in fluid communication with the fluid source and a plurality of the first nozzles, the primary valve located within the conduit;a plurality of secondary valves positioned along the conduit, wherein one secondary valve is paired with each of the plurality of first nozzles, and each secondary valve may be selectively configured in a first position to block passage of retardant through the first nozzle paired with the secondary valve and block retardant passage downstream through the conduit, in a second position to block passage of retardant through the first nozzle paired with the secondary valve and permit passthrough of retardant downstream through the conduit, and in a third position to allow passage of retardant through the first nozzle paired with the secondary valve and allow retardant passage downstream through the conduit. 9. The aircraft fire suppression system of claim 8, wherein the conduit is a primary conduit, the primary conduit fluid connected to a first secondary conduit on the first deck and the plurality of secondary valves is a first plurality of secondary valves, and the aircraft fire suppression system further comprises: a second secondary conduit on the second deck in fluid communication with the fluid source and a plurality of the second nozzles;a plurality of second secondary valves positioned along the second conduit, wherein one second secondary valve is paired with each of the plurality of second nozzles, and each second secondary valve may be selectively configured in the first position to block passage of retardant through the second nozzle paired with the second secondary valve and block retardant passage downstream through the second conduit, in the second position to block passage of retardant through the second nozzle paired with the secondary valve and permit passthrough of retardant downstream through the second conduit, and in the third position to allow passage of retardant through the second nozzle paired with the secondary valve and allow retardant passage downstream through the second conduit. 10. The aircraft fire suppression system of claim 9, further comprising a controller in electrical communication with the plurality of first secondary valves and the plurality of second secondary valves, wherein the controller is configured to separately position each of the plurality of valves in one of the first, second, and third positions based on a location of a detected fire to direct retardant to the location of the detected fire and to selectively ejected retardant from less than the plurality of nozzles on one of the first deck and the second deck. 11. A fire suppression system of an aircraft, comprising: a fire retardant source; a primary release valve in fluid communication with the fire retardant source; a first conduit and a second conduit each in fluid communication with the primary release valve, the primary release valve configured to selectively supply fire retardant from the fire retardant source to one of the first conduit and the second conduit;a first fire suppression system component for a first deck of the aircraft in fluid communication with the first conduit, the first fire suppression system component comprising:a plurality of first deck sensors for detecting a fire;a plurality of first deck secondary release valves, wherein each first deck secondary release valve is uniquely paired, one-to-one, with one of the plurality of first deck sensors; anda plurality of first deck fire retardant delivery nozzles, wherein each first deck fire retardant delivery nozzle is uniquely paired, one-to-one, with one of the plurality of first deck sensors; and a second fire suppression system component for a second deck of the aircraft in fluid communication with the second conduit, the second fire suppression system component comprising:a plurality of second deck sensors for detecting a fire;a plurality of second deck secondary release valves, wherein each second deck secondary release valve is uniquely paired, one-to-one, with one of the plurality of second deck sensors; and a plurality of second deck fire retardant delivery nozzles, wherein each second deck fire retardant delivery nozzle is uniquely paired, one-to-one, with one of the plurality of second deck sensors, wherein the first deck fire retardant delivery nozzles and the second deck fire retardant delivery nozzles are selectively operable to dispense fire retardant based on detection of a fire by the paired sensors; andwherein each of the plurality of first deck sensors and the plurality of second deck sensors comprises a heat sensor, comprising:a hollow container having a first end and a second end;a solid material within the hollow container, wherein the solid material has a melting point higher than ambient and lower than a temperature encountered during a fire;a first electrode at the first end of the hollow container; and a second electrode at the second end of the hollow container, wherein the solid material is configured to melt and short the first electrode with the second electrode during a fire. 12. The fire suppression system of claim 11, further comprising: a primary conduit for transporting fire retardant from the fire retardant source to the primary release valve;wherein, the first conduit is a first deck secondary conduit for transporting fire retardant from the primary valve to the plurality of first deck secondary valves;wherein, the second conduit is a second deck secondary conduit for transporting fire retardant from the primary valve to the plurality of second deck secondary valves;the system further comprising a first deck tertiary conduit for transporting fire retardant between the plurality of first deck secondary valves; anda second deck tertiary conduit for transporting fire retardant between the plurality of second deck secondary valves. 13. The fire suppression system of claim 11, wherein each of the plurality of secondary release valves is an electromechanical ball valves configurable to each of: a first position that blocks retardant from passing through the nozzle paired with the secondary release valve and blocks retardant from passing through the secondary release valve to one or more downstream secondary release valves;a second position that blocks retardant from passing through the nozzle paired with the secondary release valve and permits retardant to pass through the secondary release valve to one or more downstream secondary release valves; anda third position that permits retardant to pass through the nozzle paired with the secondary release valve and permits retardant to pass through the secondary release valve to one or more downstream secondary release valves. 14. The fire suppression system of claim 11, further comprising one or more cargo containers for storing cargo during transport in proximity to at least one of the sensors, wherein each of the one or more cargo containers comprises at least one aperture configured to deliver a fire indicator to one of the plurality of sensors during a fire event within the container. 15. The fire suppression system of claim 11 configured to, upon detection of a fire by one of the sensors, to eject retardant from only the fire retardant delivery nozzle that is uniquely paired with the sensor detecting the fire. 16. The fire suppression system of claim 11, wherein each heat sensor further comprises a wireless transmitter configured to output a wireless signal when the first electrode and the second electrode are shorted together. 17. The fire suppression system of claim 11 wherein, upon detection of a fire by one of the plurality of first deck sensors when the aircraft is in flight, the fire suppression system is configured to eject retardant from less than the plurality of first nozzles for a time period beginning with the detection of the fire and ending after the aircraft lands on the ground. 18. The fire suppression system of claim 11 wherein, upon detection of a fire by one of the plurality of first sensors on the first deck when the aircraft is in flight, the fire suppression system is configured to eject retardant from less than the plurality of first nozzles only during a period of time when the aircraft is descending and ending after the aircraft lands on the ground.