An aircraft fuel tank system comprising a liquid fuel tank compartment and a float-activated valve 60, comprising a positively buoyant float (64, figure 4) immersed in liquid fuel, moving up to a raised position, causing the valve to close and thus preventing fuel flow out of the tank compartment (figure 6). The float moves down to a lowered position when the fuel level drops, causing the valve to open and permit liquid fuel to flow out of the fuel tank compartment (figure 7). An alternative disclosed aircraft fuel tank system comprises a pressure-activated valve (100, figure 8), wherein a weight of liquid fuel in the fuel tank compartment applies a pressure to a valve actuator (e.g. a diaphragm, 105) which causes the valve actuator to move to a first position, causing the valve to close and preventing liquid fuel from flowing out (figure 9). The valve actuator moves to a second position responding to the applied pressure reduction due to dropping fuel level, causing the valve to open and allowing fuel to flow out (114, figure 8). The system may be installed in an aircraft wing or fuselage.
Aircraft fuel system
2017-05-31
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |