Systems and apparatus for an oval O-ring groove for aircraft wheels may generally comprise an inboard wheel portion and an inboard O-ring groove. The inboard wheel portion may include an inboard rim located opposite of an inboard tubewell. The inboard tubewell may have an inboard mating surface located on an axially outward edge of the inboard tubewell. The inboard O-ring groove may be formed as a partial oval-shaped recess located on an outer edge of the inboard mating surface.

A powered aircraft wheel is designed to include multiple wheel sections configured to define a cavity within the wheel and to support completely within the wheel cavity an onboard non-engine drive means controllable to move an aircraft autonomously without reliance on aircraft engines during taxi and ground travel. Each part of the powered wheel may be constructed of a material specifically selected to emphasize a functional property of the material that is optimal for the function of the wheel part at a specific location. The selected combination of functionally distinct materials gives the powered aircraft wheel a unique optimal structural and functional capability.

An aircraft landing gear bogie beam including first and second ends and a mounting bearing for connection to an aircraft landing gear main strut between the ends. Each end has a respective axle, and each axle defines a wheel mounting portion on each side of the bogie beam. The bogie beam is arranged to enable the first and second axles to each pivot relative to the bearing about a respective longitudinal axis of the bogie beam by an amount that is sufficient to place a wheel rim of a wheel assembly in contact with the ground in the event of a tyre of the wheel assembly deflating.

Systems and method for an electrical system on an aircraft are provided. In example embodiments, the electrical system can be for an aircraft having a turbine engine. The turbine engine having a high pressure (HP) spool and a low pressure (LP) spool. The HP spool can be configured to drive a first generator to provide a first electrical output. The LP spool can be configured to drive a second generator to provide a second electrical output. The first generator and the second generator can be coupled to an electrical power distribution bus that provides electrical power to a load. A hybrid electric propulsion system and a secondary aircraft systems bus can both be coupled to the electrical power distribution bus. The electrical system can further include a control system configured to allocate power among the first generator, the second generator, and the hybrid electric propulsion system, and the secondary aircraft systems bus.

A system and method of controlling operation of a host device in real-time, the host device operatively connected to an optical device and a radar device. The optical device is configured to obtain visual data of at least one object. The object is located at an incline, relative to the host device, the incline being characterized by an elevation angle () and an azimuth angle (). The radar device is configured to obtain radar data, including a radial distance (r) of the object from the host device, the azimuth angle (), and a range rate (dr/dt). The controller is programmed to determine a time-to-contact for the host device and the object based at least partially on a 3-D position and 3-D velocity vector. The operation of the host device is controlled based at least partially on the time-to-contact.

A fuel vent connector includes a longitudinal axis and a flow path a long the longitudinal axis. The connector further includes a first portion pivotally supporting a plurality of fingers, each finger amongst the plurality of fingers having a latching head biased radially outwardly and configured to latch within a fuel vent opening. The connector further includes a second portion biased longitudinally away from the first portion with respect to the longitudinal axis. The flow path extends through the first and second portions, and longitudinal movement of the second portion towards the first portion moves the fingers radially inward.

A hydraulic torque compensation device comprises a pair of housings, a first housing including a first high pressure liquid chamber and a second low pressure liquid chambers, a second housing having a third high pressure liquid chamber, a fourth accumulator chamber, and a fifth low pressure chamber that is defined by a wall and an end of the second housing. A first main duct links the first chamber of the first housing to the third chamber of the second housing. A second main duct links the second chamber of the first housing to the fifth chamber of the second housing. Each housing also include a piston, the first chamber between a first piston body and an end of the first housing and the third chamber between a second piston body and the wall. The device ensures a counter action to engine loads when a positive torque is applied.

A method can include emitting, from a light source, directional light through fuel contained in a fuel tank, and determining a refraction angle of the directional light after the directional light passes through an interface with the fuel. The method can further include determining, by a processing device, an index of refraction of the fuel based on the determined refraction angle, and determining, by the processing device, a density of the fuel based on the determined index of refraction of the fuel.

A multiply-redundant system that protects fueling of rockets, aircraft and other vehicles using Liquefied Natural Gas (LNG) along with an oxidizer such as Liquefied Oxygen. One or more sensors in combination with one or more optional microswitches combine to detect any leaks, fire or explosion hazards quickly locking out further fueling. For different levels of safety, different combinations of sensors can be used.

A preloading axle clamp for a wheel bearing includes an axle adapted to receive a wheel bearing and a connecting fork. A bushing is positioned about a first end of the axle. A fastener having a first flange is coupled to the first end of the axle, wherein a portion of the fastener is inserted into the first end to retain the connecting fork on the axle. A nut is threadedly coupled to the bushing, wherein rotation of the nut on the bushing causes a preloading force on the wheel bearing.