초록 ▼

A high wing Canard aircraft mounts three strake fuel tanks within the top of the aircraft fuselage on the right and left sides thereof in a fore and aft array interconnected by horizontal interconnect lines at the bottoms of the strake tanks to provide an alternate fuel path in the event of tank-lin

A high wing Canard aircraft mounts three strake fuel tanks within the top of the aircraft fuselage on the right and left sides thereof in a fore and aft array interconnected by horizontal interconnect lines at the bottoms of the strake tanks to provide an alternate fuel path in the event of tank-line contamination blockage and forming a secondary gravity feed system. A pair of wing tanks integrated to the high wing of the Canard aircraft, to the rear of the strake tanks, feed along with individual horizontal fuel lines from the strake tanks to a central fuel collector tank interposed between the main high wing sections with low pressure drop flapper check valves at the ends of the individual horizontal lines internally of the collector tank for preventing fuel from leaving the collector tank. The primary gravity feed system defined thereby isolates each tank from the other, thereby preventing large fuel excursions during extreme flight maneuvers. A sump tank integrated to and underlying the common collector tank supplies fuel through the main fuel supply line to the engine via primary and secondary boost pumps. The excess fuel returning from the engine at boost pump pressure functions as the motive fluid for jet pumps, one in the front of each forward strake tank and one in the outboard portion of each wing tank for supplying fuel to the collector tank at a rate one half of the engine take-off fuel demand. Overflow return lines are routed from the top of the collector tank back to each tank containing a jet pump. These lines also terminate with low pressure drop flapper check valves to prevent cross flow between tanks. Filler manifolds overlying one of the strake tanks to each side of the aircraft meter fuel to the tanks along one side, at a rate proportional to the tank size.

대표청구항 ▼

A gravity feed fuel system for a high wing Canard aircraft including: an elongated fuselage, a high, main wing mounted to the top of said fuselage and having right and left wing sections projecting outwardly thereof to opposite sides of said fuselage, said fuel system comprising: a plurality of fore

A gravity feed fuel system for a high wing Canard aircraft including: an elongated fuselage, a high, main wing mounted to the top of said fuselage and having right and left wing sections projecting outwardly thereof to opposite sides of said fuselage, said fuel system comprising: a plurality of fore and aft, spaced strake fuel tanks mounted within the top of said fuselage forward of said main wing at a common level, a wing tank within each main wing section at said common level, a common, central collector tank mounted between said wing tanks, in alignment with said fuselage tanks and at said common level, a fuel sump tank below said collector tank, means communicating said sump tank with the bottom of said collector tank to receive fuel directly from the collector tank, main fuel supply line opening to the sump tank for feeding fuel to at least one aircraft engine mounted to said aircraft, a primary gravity feed system comprising individual horizontal fuel lines leading from the bottom of each strake and wing tank to the central common fuel collector tank, each individual fuel line terminating at said fuel collector tank in a low pressure drop, normally open flapper check valve for preventing reverse flow from the collector tank back to the strake and wing tanks, a secondary gravity feed system comprising horizontal interconnect fuel lines connected to and opening freely at opposite ends into the bottoms of adjacent strake tanks, said individual fuel lines and said interconnect fuel lines being oversized to meet maximum fuel demands of the engine with some margin of safety, and a fuel transfer system comprising: at least one boost pump in the main fuel supply line between said sump tank and said engine, at least one jet pump in the strake tank most remote from said collector tank and a jet pump in an outboard portion of each wing tank, a fuel return line from said engine for returning excess fuel at boost pump pressure, means for connecting said fuel return line to said jet pump for causing the excess fuel at boost pump pressure to act as the motive flow for the jet pumps, inlets to the jet pumps for allowing fuel within said most remote strake tank and each wing tank to enter the jet pumps for aspiration thereby, discharge lines from each jet pump to the collector tank, and wherein the jet pumps have a capacity such that each jet pump supplies fuel to the collector tank at a high proportion of the engine take-off fuel demand, whereby the collector is supplied with fuel by the fuel transfer system which is considerably in excess of the maximum engine demand, and wherein said fuel transfer system further comprises overflow return lines routed from the top of the common, central collector tank back to each fuel tank containing a jet pump, and wherein said overflow return lines terminate at each tank containing a jet pump in low pressure drop, normally open flapper check valve for preventing fuel cross flow between tanks.