In an aspect, an aircraft fueling apparatus is disclosed. The apparatus includes at least a container comprising a fuel tank configured to store liquified gas fuel. The apparatus may also include a translocation device configured to carry the at least a container. An orientation guidance track may also be included in the apparatus. The orientation guidance track may be configured to direct a movement of the translocation device to a first position.

The present disclosure provides modular hydrogen-fuel storage assemblies with an external form factor corresponding to Unit Load Device (ULD) cargo containers, allowing the assemblies to be easily loaded into and stored in a cargo bay area of an aircraft. Each assembly can house one or more hydrogen fuel tanks containing liquid and gaseous hydrogen, which can be used to power an APU or other power system of the aircraft. Each assembly can include an internal cradle system for securing the tanks within the assembly, a ground servicing panel for refueling, a quick connection assembly for quickly coupling the assembly to the APU or other power system, a cold box for managing various fluid flow, and an avionics bay for controlling the various components of the assembly.

A power supply device that supplies power to a power load of a flying body, comprises: a power generation unit; a hollow housing including a reserving portion configured to reserve a fuel of the power generation unit, and a storage portion configured to store the power generation unit; and a connecting portion configured to connect the housing to an airframe of the flying body. The housing has a shape long in a front-and-rear direction of the flying body, and is arranged outside the airframe, and the reserving portion and the storage portion are arranged in a longitudinal direction of the housing.

A power supply device that supplies power to a power load of a flying body, comprises: a power generation unit; a hollow housing including a reserving portion configured to reserve a fuel of the power generation unit, and a storage portion configured to store the power generation unit; and a connecting portion configured to connect the housing to an airframe of the flying body. The housing has a shape long in a front-and-rear direction of the flying body, and is arranged outside the airframe, and the reserving portion and the storage portion are arranged in a longitudinal direction of the housing.

A fuel tank dam comprises a first section, a second section, a third section, and a flange section. The first section can be fixed to a first structural component, and the second section can be fixed to a second structural component. The third section has a bellows comprising a plurality of folded sections and is disposed between the first section and the second section. The flange section extends along an outer plate at least from an edge section of the third section and can be fixed to the outer plate.

A seal for sealing an aircraft fuel tank, an aircraft wing rib and stringer sealing assembly, an aircraft wing fuel tank, an aircraft structural wing box, an aircraft wing, and a method of sealing an aperture are disclosed. The seal is for sealing a wing rib to a stringer passing through an aperture in the rib at a variable position in the aperture. The seal includes self-adjustment means to absorb any tolerance when forming the seal, upon the stringer being assembled into the aperture in the rib.

An autonomous propeller propulsion system for an aircraft. The autonomous system comprises a chassis with first attachment systems which engage with second attachment systems of the wing to ensure detachable attachment of the autonomous system, a fuel cell attached to the chassis, an electric motor attached to the chassis and having an output shaft, a propshaft rotated by the output shaft, a propeller attached to the propshaft, a controller converting an electric current delivered by the fuel cells into an electric current delivered to the electric motor, a hydrogen feed duct and an air feed duct, a set of auxiliary equipment, and a first connection arrangement, which connects with a second connection arrangement of the aircraft.

An autonomous propeller propulsion system for an aircraft. The autonomous system comprises a chassis with first attachment systems which engage with second attachment systems of the wing to ensure detachable attachment of the autonomous system, a fuel cell attached to the chassis, an electric motor attached to the chassis and having an output shaft, a propshaft rotated by the output shaft, a propeller attached to the propshaft, a controller converting an electric current delivered by the fuel cells into an electric current delivered to the electric motor, a hydrogen feed duct and an air feed duct, a set of auxiliary equipment, and a first connection arrangement, which connects with a second connection arrangement of the aircraft.

A fuel tank comprises an interior wall, a sump, and a baffle that comprises a center fitting, a full-length containment petal, a partial-length containment petal, a dump tube. The full-length containment petal comprises a full-length side edge, extending radially outward from the center fitting. The partial-length containment petal comprises a partial-length side edge, extending radially outward from the center fitting. The dump tube is connected to the sump. The full-length side edge of the full-length containment petal is longer than the partial-length side edge of the partial-length containment petal. All of the partial-length side edge of the partial-length containment petal is attached to a linear portion of the full-length side edge of the full-length containment petal.

A fuel tank comprises an interior wall, a sump, and a baffle that comprises a center fitting, a full-length containment petal, a partial-length containment petal, a dump tube. The full-length containment petal comprises a full-length side edge, extending radially outward from the center fitting. The partial-length containment petal comprises a partial-length side edge, extending radially outward from the center fitting. The dump tube is connected to the sump. The full-length side edge of the full-length containment petal is longer than the partial-length side edge of the partial-length containment petal. All of the partial-length side edge of the partial-length containment petal is attached to a linear portion of the full-length side edge of the full-length containment petal.