A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500° F. The system additionally includes a fuel system having a deoxygenation unit for deoxygenating fuel in the fuel system, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system.

A conformable tank includes a body with a plurality of walls defining a cavity in the body, and an internal support connected to an internal surface of one of the plurality of wall of the body and protruding into the cavity of the body. The body and the internal support are an additively manufactured integral structure formed by a fiber filament reinforced composite material.

A conformable tank includes a body with a plurality of walls defining a cavity in the body, and an internal support connected to an internal surface of one of the plurality of wall of the body and protruding into the cavity of the body. The body and the internal support are an additively manufactured integral structure formed by a fiber filament reinforced composite material.

This present patent application discloses an unmanned aerial vehicle (UAV) that features a stable and easy way of steering and controlling the unmanned aerial vehicle. The unmanned aerial vehicle comprises of four vanes attached to extension arms, a single engine coupled to a special gearbox and sliding weights. The unmanned aerial vehicle features sliding weights below the extension arms and are used for steering the UAV in a desired direction in air. The sliding weights and the engine are used to control the UAV. The single engine leads to less power consumption, longer battery life, longer flight time and higher flight attitude.

This present patent application discloses an unmanned aerial vehicle (UAV) that features a stable and easy way of steering and controlling the unmanned aerial vehicle. The unmanned aerial vehicle comprises of four vanes attached to extension arms, a single engine coupled to a special gearbox and sliding weights. The unmanned aerial vehicle features sliding weights below the extension arms and are used for steering the UAV in a desired direction in air. The sliding weights and the engine are used to control the UAV. The single engine leads to less power consumption, longer battery life, longer flight time and higher flight attitude.

A method, system and apparatus are provided for generating and dispersing plumes of reflective aerosols. Methods include: supplying fuel to an engine of an aircraft for combustion; supplying an additive to the fuel, where the additive includes at least one of a reflective aerosol or a precursor thereof; combusting the fuel and the additive to the fuel in the engine; and generating, in the exhaust from the engine, a plume of reflective aerosol, where the reflective aerosol reflects sunlight.

A method, system and apparatus are provided for generating and dispersing plumes of reflective aerosols. Methods include: supplying fuel to an engine of an aircraft for combustion; supplying an additive to the fuel, where the additive includes at least one of a reflective aerosol or a precursor thereof; combusting the fuel and the additive to the fuel in the engine; and generating, in the exhaust from the engine, a plume of reflective aerosol, where the reflective aerosol reflects sunlight.

An aircraft wing box is disclosed having a first cover, a second cover, a partition extending between the first and second cover and configured to provide a fuel tight boundary between the first and second covers, a first joint coupling the partition to the first cover, and a second joint coupling the partition to the second cover. The first joint is a slip joint configured to inhibit fuel leakage across the slip joint whilst permitting relative movement between the partition and the first cover.

An aircraft wing box is disclosed having a fuel tank with a fuel-tight boundary, upper and lower covers, forward and aft spars, and a partition including an inboard portion, an outboard portion, and a third portion between the inboard and outboard portions. Each cover is attached to each spar, the inboard portion of the partition is joined to each cover and joined to one of the spars, the outboard portion of the partition is joined to each cover and joined to one of the spars, each cover is joined to the partition. The inboard part, outboard part and third part of the partition are integrally formed as a single-piece; and the single-piece provides part of the fuel-tight boundary of the fuel tank.

An aircraft fuel system monitoring apparatus is disclosed having a processor configured to receive first information indicative of one or more parameters relating to fuel present in an aircraft; receive second information relating to the configuration of a fuel system of the aircraft; receive third information indicative of an orientation of the aircraft; receive fourth information indicative of a state of one or more non-fuel-related systems of the aircraft; and generate a prediction of a quantity of fuel present in the aircraft based on the received first information, the received second information, and one or both of the received third information and the received fourth information.