Abstract: A fire detection device is designed to make hydrogen fires detectable in aviation operations and similar applications, whether it is for the purpose of detecting a fire around an aircraft prior to passenger and crew emergency evacuation, or to identify fires in proximity to airport ground vehicles that utilise hydrogen as a fuel or vehicles that are used for transporting or transforming hydrogen in any transport context. The device can be designed to be non-toxic and safe for use in proximity to humans.

Abstract: The invention defines a combined system of sensor(s), control logic, air intake and contaminant deflector for a fuel cell system mounted on an aircraft, which will detect contamination in the free air flow surrounding the aircraft and if excessive contamination is detected will activate the contaminant deflector to protect the fuel cell system from contamination, damage and power loss. The system ensures constant speed of the aircraft by adjusting the power of the fuel cells to compensate any change in aircraft drag and adjusts the speed of any connected compressors to maintain and achieve necessary changes in power and compensation for any air pressure losses the system creates.

Abstract: A cryogenic liquid fuel for a vehicle is safely converted into a gas at a desired pressure. The gas is then warmed up from cryogenic temperatures so that it is in a usable range for consuming devices powering the vehicle. Waste heat from any type of consuming device is used in the most efficient way for the vehicle system. If waste heat is not readily available, then an electric heater can be optionally used. The invention can be used in conjunction with an electric motor to cool it to cryogenic temperatures to improve its performance, or to enhance the performance of the consuming device by cooling it. The system can operate passively to perform the vaporisation function, or can alternatively be actively controlled with sensors and a controller if tight margins of pressure and temperature of the fuel in its gaseous state is desired.

Abstract: Creation of a protected space in the interior of a vehicle surrounding elements of the vehicle’s fuel system stops subsequent unsafe leakage of fuel and flammable gas into other interior spaces of the vehicle. It limits both the potential for the build-up of flammable gas in the interior of the vehicle and the potential of detonation. The protected space, if used to protect a cryogenic fuel system, also protects against liquefaction occurring. In the event that the protected fuel system has a failure the design will cause forced ventilation to occur to safely vent the protected space and protect the vehicle from the failure.

Abstract: A second layer of physical protection against failure for a fuel line of a vehicle for use with high pressure and cryogenic fuels increases safety. The primary fuel line can be assembled from one or more components. The secondary protection is a single outer sleeve that includes a selectively permeable or impermeable membrane and may be reinforced. The sleeve and enclosed volume can also be used to protect against oxygen liquification in cryogenic applications. A means to detect failure of the primary fuel line and optional means to vent leaking fuel depend on the application. Clamp designs may be used to mount and clamp such assemblies in a vehicle structure.

Abstract: A cryogenic tank for storing cryogenic fluids is disclosed. The cryogenic tank is typically configured to be mounted on a vehicle for supplying cryogenic fuel to a propulsion system of the vehicle. The cryogenic tank comprises an inner vessel for containing cryogenic fluids and an outer vessel surrounding the inner vessel to define a vacuum insulating volume therebetween. The outer vessel is configured to transmit static and/or dynamic loads, while the inner vessel is partially or completely isolated from such loads.

Abstract: A tooling to enable variation in radius of molded continuous fiber reinforced polymer curved components which includes a first tooling surface formed on a first tooling member which may be formed of sprung material, a second tooling surface formed on a second tooling member which may be formed of sprung material. The first tooling surface and the second tooling surface are positioned to lie one over the other to form a gap therebetween for receiving a supply of continuous fiber reinforced polymer. The first tooling surface and the second tooling surface are movable towards and away from each other to modify the size of the gap therebetween and thereby modify the amount of compression applied by the first and second tooling surfaces on the continuous fiber reinforced polymer positioned therebetween. A mechanism is engaged with the first tooling member to modify a curvature of the first tooling surface.

Abstract: A method and apparatus for forming a continuously molded carbon fiber reinforced polymer slender curved frame. A continuous supply of uncured carbon fiber reinforced polymer material is directed into a forming tool. The uncured carbon fiber reinforced polymer material is continuously molded into a desired shape in the forming tool. The carbon fiber reinforced polymer material is cured into a frame of the desired shape in the forming tool. The frame is removed from the forming tool. An out-of-plane curvature is put in the frame while the frame is in at least a portion of the forming tool.

Abstract: A method and apparatus for forming a continuously molded carbon fiber reinforced polymer slender curved frame. A continuous supply of uncured carbon fiber reinforced polymer material is directed into a forming tool. The uncured carbon fiber reinforced polymer material is continuously molded into a desired shape in the forming tool. The carbon fiber reinforced polymer material is cured into a frame of the desired shape in the forming tool. The frame is removed from the forming tool. An out-of-plane curvature is put in the frame while the frame is in at least a portion of the forming tool.

Abstract: A tooling to enable variation in radius of molded continuous fiber reinforced polymer curved components which includes a first tooling surface formed on a first tooling member which may be formed of sprung material, a second tooling surface formed on a second tooling member which may be formed of sprung material. The first tooling surface and the second tooling surface are positioned to lie one over the other to form a gap therebetween for receiving a supply of continuous fiber reinforced polymer. The first tooling surface and the second tooling surface are movable towards and away from each other to modify the size of the gap therebetween and thereby modify the amount of compression applied by the first and second tooling surfaces on the continuous fiber reinforced polymer positioned therebetween. A mechanism is engaged with the first tooling member to modify a curvature of the first tooling surface.

Abstract: An aircraft is disclosed having a wing, the wing having a connection interface at the tip of the wing, and the wing being interchangeable between a first configuration in which a first wing tip is connected to the connection interface, and a second configuration in which a second wing tip is connected to the connection interface to replace the first wing tip. The second wing tip comprises a fuel pod for carrying additional fuel, and a wing tip device for improving aerodynamic efficiency. The wing may be designed for performance in both configurations.

Abstract: An aircraft is disclosed having a wing, the wing having a connection interface at the tip of the wing, and the wing being interchangeable between a first configuration in which a first wing tip is connected to the connection interface, and a second configuration in which a second wing tip is connected to the connection interface to replace the first wing tip. The second wing tip comprises a fuel pod for carrying additional fuel, and a wing tip device for improving aerodynamic efficiency. The wing may be designed for performance in both configurations.

Abstract: An aircraft comprising a wing, the wing having a connection interface at the tip of the wing, and the wing being interchangeable between a first configuration in which a first wing tip is connected to the connection interface, and a second configuration in which a second wing tip is connected to the connection interface to replace the first wing tip. The second wing tip comprises a fuel pod for carrying additional fuel, and a wing tip device for improving aerodynamic efficiency. The wing may be designed for performance in both configurations.

Abstract: The invention relates to a method and apparatus for inspecting an aircraft fuel tank. The invention also relates to an aircraft fuel tank including an inspection apparatus. The invention provides an aircraft fuel tank, the aircraft fuel tank containing a robotic device. The robotic device is arranged to be movable within the aircraft fuel tank. The robotic device further comprises a sensor for inspecting the aircraft fuel tank.

Abstract: The invention relates to a method and apparatus for inspecting an aircraft fuel tank. The invention also relates to an aircraft fuel tank including an inspection apparatus. The invention provides an aircraft fuel tank, the aircraft fuel tank containing a robotic device. The robotic device is arranged to be movable within the aircraft fuel tank. The robotic device further comprises a sensor for inspecting the aircraft fuel tank.

Abstract: An aircraft comprising a wing, the wing having a connection interface at the tip of the wing, and the wing being interchangeable between a first configuration in which a first wing tip is connected to the connection interface, and a second configuration in which a second wing tip is connected to the connection interface to replace the first wing tip. The second wing tip comprises a fuel pod for carrying additional fuel, and a wing tip device for improving aerodynamic efficiency. The wing may be designed for performance in both configurations.

Abstract: An aircraft wing, the wing having a connection interface at the tip of the wing, and the wing being configurable between a first configuration in which a first wing tip device is connected to the connection interface, and a second configuration in which a second wing tip device is connected to the connection interface to replace the first wing tip device. The design of the wing is such that it is designed for performance in both the first and the second configurations.