Fuel system for Canard aircraft

• US 4,913,380 A
• Filed: 10/13/1988
• Issued: 04/03/1990
• Est. Priority Date: 10/13/1988
• Status: Expired due to Fees

• Current Assignee: OMAC Incorporated
• Original Assignee: OMAC Incorporated
• Inventors: Vardaman, Billy G., Meyer, Corwin W.
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US07/256,952
• Time in Patent Office: 537 Days
• Field of Search: 244/135 R, 244/135 C, 244/13, 244/45 R, 244/45 A, 244/91, 137/263, 137/571, 60/734, 60/39.094
• US Class Current: 244/135.00R
• CPC Class Codes: B64D 37/04 Arrangement thereof in or on aircraft
• CPC Class Codes: Y10T 137/4807 Tank type manifold [i.e., one tank supplies or receives from at least two others]
• CPC Class Codes: Y10T 137/86187 Plural tanks or compartments connected for serial flow

Abstract

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.

Claims

1. 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.

2. The gravity feed fuel system as claimed in claim 1, further comprising a fuel filler system:

said fuel filler system comprising at least one filler manifold for supplying fuel to each of said strake tanks and to said wing tanks, means for metering fuel to each fuel tank at a rate proportional to its size such that each tank is approximately at the same level during and upon completion of fueling, and wherein said filler manifold includes an antisiphoning filler cap assembly.

3. The gravity feed fuel system as claimed in claim 2, wherein said strake tanks comprise individual right and left side strake tank sections mounted within said fuselage to the right and left sides of the aircraft fuselage, wherein each strake tank section includes an individual filler manifold, and wherein the left and right main wing fuel tanks are interconnected respectively to the left and right strake tank sections such that left and right fuel tank section systems are formed thereby, and wherein said left and right aircraft fuel tank system sections are disconnected from each other and filled separately.

4. The gravity feed fuel system as claimed in claim 1, further comprising a fuel vent system:

said fuel vent system comprising. a vent line, a manifold within the top of each fuel tank having at least one opening therein, a ball float check valve selectively closing off each said at least one opening within each fuel vent system manifold and including a ball float gravity positioned such that the openings under normal flight conditions are open with said ball floats closing off the manifold openings upon the fuel level rising to the opening level for any reason to prevent fuel from entering the vent line, and said vent line interconnecting the manifolds and connecting the openings within respective manifolds, and wherein said vent line terminates in a fuel vent discharge opening located on a lower surface of the high main wing of the aircraft.

5. The gravity feed fuel system as claimed in claim 1, further comprising a fuel tank outlet strainer within an outlet of the main fuel supply line opening to the sump tank for removing large contaminants from the fuel flowing to the engine, wherein said at least one boost pump comprises a pair of electric, in line fuel pumps constituting respectively, main and emergency boost pumps, said main fuel supply line opening to inlets for each of said boost pumps, each of said boost pumps further comprising an outlet containing check valves to prevent back-flow through the boost pumps from the engine, said main fuel supply line including a tee downstream of the main and emergency fuel boost pump outlets, a fuel filter within said main fuel supply line downstream of the tee, and a fuel shut-off valve downstream of said outlet check valve and upstream of said engine.

6. The gravity feed fuel system as claimed in claim 1, further comprising a fuel drain system,

said fuel drain system comprising a drain valve assembly installed in the bottom of the collector tank in the sump tank, said drain valve assembly including a cylindrical valve casing, an axial bore within said casing, an axially shiftable plunger in said casing, a drain inlet line opening from said sump tank to the side of said valve casing, an overboard drain line opening axially to said valve casing and being normally closed by said plunger, a coil spring mounted within said casing on the side of said plunger remote from said overboard drain line outlet connection, to bias said plunger to a position closing off communications to said drain line, a spring-loaded remote actuating pull control wire coupled to said plunger and terminating in a drain pull knob such that pulling of said control knob causes retraction of the plunger from the end of said overboard drain line opening to the interior of said valve casing to communicate the line between said sump tank and said valve casing to said overboard drain line.

7. The gravity feed fuel system as claimed in claim 6, wherein said primary boost pump and said secondary boost pump include seal drain lines commonly connected to said overboard drain line downstream of said drain valve assembly such that the electric fuel pump seal drains function only when a seal failure occurs permitting fuel leakage at the primary or secondary boost pump to escape through the overboard drain line.