An aircraft comprising a plurality of fuel tanks in each wing is arranged such that each fuel tank is provided with a venting pipe connected to a single venting chamber. The venting chamber is itself located in a central fuel tank located in the wing centre-box and is thus located inwardly of at lea
An aircraft comprising a plurality of fuel tanks in each wing is arranged such that each fuel tank is provided with a venting pipe connected to a single venting chamber. The venting chamber is itself located in a central fuel tank located in the wing centre-box and is thus located inwardly of at least two of the fuel tanks. The venting chamber has two venting pipes each being connected via a respective surge tank in each wing to the exterior of the aircraft.
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The invention claimed is: 1. An aircraft comprising a plurality of fuel storage chambers located within said aircraft, at least one of said fuel storage chambers being located within a wing of said aircraft, said wing having an outward portion associated with the wingtip and an inward portion, each
The invention claimed is: 1. An aircraft comprising a plurality of fuel storage chambers located within said aircraft, at least one of said fuel storage chambers being located within a wing of said aircraft, said wing having an outward portion associated with the wingtip and an inward portion, each of at least two of the fuel storage chambers being provided with a venting conduit for permitting fluid communication with a venting chamber of a venting chamber system, wherein the venting chamber is located inwardly of said at least one fuel storage chamber and has a venting outlet for permitting fluid communication between the venting chamber and the exterior of the aircraft, the aircraft comprising a venting chamber conduit provided between the venting outlet of the venting chamber and an overflow chamber, the overflow chamber being provided with an overflow venting outlet for permitting fluid communication between the overflow chamber and the exterior of the aircraft, the overflow chamber being located in the outward portion of the wing. 2. An aircraft according to claim 1, wherein the venting chamber is located inward of said at least two fuel storage chambers. 3. An aircraft according to claim 1, wherein the venting chamber is disposed within a fuel storage chamber located centrally relative to the wings of the aircraft. 4. An aircraft according to claim 1, wherein each of said at least two fuel storage chambers is associated with a mutually different wing of the aircraft. 5. An aircraft according to claim 1, wherein the venting chamber system comprises a plurality of venting regions in fluid communication with each other, but arranged such that during level flight of the aircraft the flow of fuel, if any is present, from one of the venting regions to another of the venting regions is restricted. 6. An aircraft according to claim 5, wherein at least two of the venting regions are defined within the venting chamber by one or more substantially liquid-impermeable partitions that allow venting gases to flow from one venting region to another. 7. An aircraft according to claim 5, wherein the venting chamber system comprises only one venting chamber, with the venting regions being defined within the venting chamber. 8. An aircraft according to claim 5, wherein the venting chamber system comprises a plurality of venting chambers wherein each of at least two of the venting regions is located within a separate venting chamber. 9. An aircraft according to claim 5, wherein each of the venting regions is associated with one or more fuel storage chambers, the fuel storage chambers associated with one of the venting regions all being located in one wing and the fuel storage chambers associated with another of the venting regions all being located in a different wing. 10. An aircraft according to claim 9, wherein each venting region may be provided with a separate venting chamber outlet for permitting fluid communication between the venting region and the exterior of the aircraft. 11. An aircraft according to claim 1, wherein one of said venting conduits includes a valve arrangement that is arranged to restrict the overflow of fuel into the venting conduit. 12. An aircraft according to claim 1, wherein one of said venting conduits includes a fuel storage chamber venting outlet located towards the trailing edge of said wing, said venting conduit connecting said venting outlet via a forwardly extending portion and via an inwardly extending portion to the venting chamber system, the portions being arranged in series and within the fuel storage chamber. 13. A fixed-wing aircraft with two anhedral wings, said aircraft comprising a plurality of fuel tanks located within said aircraft, each of said wings having an outward portion associated with the wingtip and an inward portion, each of at least two of the fuel tanks being located within mutually different wings of the aircraft and being provided with a venting conduit for permitting fluid communication with a venting chamber of a venting chamber system, wherein the venting chamber is disposed within a fuel tank located centrally relative to the wings of the aircraft and is located inwardly of said at least two fuel storage tanks and has a venting outlet for permitting fluid communication between the venting chamber and the exterior of the aircraft, wherein the aircraft further comprises two surge tanks, the surge tanks being located in the outward portion of mutually different wings of the aircraft, a venting chamber conduit being provided between the venting outlet of the venting chamber and each surge tank, each surge tank being provided with an overflow venting outlet for permitting fluid communication between the surge tank and the exterior of the aircraft.
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이 특허에 인용된 특허 (1)
Vardaman Billy G. (Albany GA) Meyer Corwin W. (Ocala FL), Fuel system for Canard aircraft.
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