A taxiing system for an aircraft including an undercarriage having a wheel, includes an electric motor associated with the wheel, an electric controller of the electric motor, connected to an output of an electrical power supply, and a taxiing control computer configured to determine control instructions for the electric motor and to transmit these instructions to the electric controller. The taxiing control computer is configured to receive braking of the aircraft commands during the taxiing of the aircraft and to determine control instructions for the electric motor corresponding to operation of the motor in generator mode when it receives a braking command. The electric controller is connected to an energy absorber making it possible to absorb the electric energy produced by the electric motor when the latter is operating in generator mode.

A system for weight measurement for an aircraft having a weight on wheels threshold between a flight mode and a ground mode includes a weight on wheels sensor arrangeable on a landing gear assembly of the aircraft, and a computing device receiving first detected data from the sensor related to strain on the landing gear assembly. The computing device calculates a rate of change of the strain over time to determine when the landing gear assembly reaches the weight on wheels threshold. The system also measures aircraft gross weight in a static condition.

A corrosion inhibition composition is disclosed comprising a cerium, a tungstate, a molybdate and silicate compounds. A corrosion inhibition composition is provided comprising a zinc oxide, a zinc hydroxide benzoate, a sodium benzoate, a molybdate and a silicate compound. A corrosion inhibition composition is provided comprising a zinc oxide, a zinc phosphate, a calcium silicate, an aluminum phosphate, a zinc calcium strontium aluminum orthophosphate silicate hydrate, a molybdate, and silicate compounds.

A system and method for refurbishing an internal surface of an article of manufacture includes a sputtering unit. The internal surface of the article of manufacture defines an internal cavity. The sputtering unit includes an electrode assembly coupled to a sealing portion. The refurbishing method begins with preparing the internal surface to remove physical damage and contamination. Next, the sputtering unit is interfaced with the article by extending the electrode assembly into the cavity and sealing the sputtering unit to the article with the sealing portion. The internal surface of the article then defines a boundary of a sputtering chamber. A dimensional value is provided that is related to an internal dimension of the cavity. Finally the sputtering unit is operated to deposit material onto the internal surface based upon the provided dimensional value.

A system and method for refurbishing an internal surface of an article of manufacture includes a sputtering unit. The internal surface of the article of manufacture defines an internal cavity. The sputtering unit includes an electrode assembly coupled to a sealing portion. The refurbishing method begins with preparing the internal surface to remove physical damage and contamination. Next, the sputtering unit is interfaced with the article by extending the electrode assembly into the cavity and sealing the sputtering unit to the article with the sealing portion. The internal surface of the article then defines a boundary of a sputtering chamber. A dimensional value is provided that is related to an internal dimension of the cavity. Finally the sputtering unit is operated to deposit material onto the internal surface based upon the provided dimensional value.

Systems and methods for mechanically rotating an aircraft about its center-of-gravity (C.sub.G) are disclosed. The system can enable the rear, or main, landing gear to squat, while the nose landing gear raises to generate a positive angle of attack for the aircraft for takeoff or landing. The system can also enable the nose gear and main gear to return to a relatively level fuselage attitude for ground operations. The system can include one or more hydraulically linked hydraulic cylinders to control the overall height of the nose gear and the main gear. Because the hydraulic cylinders are linked, a change on the length of the nose cylinder generates a proportional, and opposite, change in the length of the main cylinder, and vice-versa. A method and control system for monitoring and controlling the relative positions of the nose gear and main gear is also disclosed.

A landing gear includes a fixing mechanism, a driving mechanism disposed on the fixing mechanism, a translating member connected to the driving mechanism and configured to move relative to the fix mechanism whey being driven by the driving mechanism, and two supporting feet disposed opposite to each other. The two supporting feet are pivotally connected to the fixing mechanism and movably connected at two ends of the translating member. The driving mechanism is configured to drive the two supporting feet through the translating member to rotate relative to the fixing mechanism.

An aircraft includes an aircraft body including one or more exterior surfaces and a projector secured to a component of the aircraft. The projector is configured to selectably project one or more images on the one or more exterior surfaces. A method of displaying a projected image on an aircraft surface includes moving a landing gear assembly of the aircraft from a retracted position to an extending position, activating a projector disposed at the landing gear assembly, and displaying a projected image at the aircraft surface via activation of the projector.

Disclosed herein are a vehicle system and method for VTOL. The vehicle system includes: a carrier vehicle and a cruise vehicle. The carrier vehicle includes one or more fuselages, one or more wings, one or more attach units coupled to the one or more fuselages or to the one or more wings, and propulsion systems operable to provide, at least, substantially vertical thrust and substantially horizontal thrust. The cruise vehicle includes one or more fuselages for carrying passengers or cargo and one or more wings. The one or more attach units of the carrier vehicle are adapted to couple to the cruise vehicle to detachably engage.

Disclosed herein are a vehicle system and method for VTOL. The vehicle system includes: a carrier vehicle and a cruise vehicle. The carrier vehicle includes one or more fuselages, one or more wings, one or more attach units coupled to the one or more fuselages or to the one or more wings, and propulsion systems operable to provide, at least, substantially vertical thrust and substantially horizontal thrust. The cruise vehicle includes one or more fuselages for carrying passengers or cargo and one or more wings. The one or more attach units of the carrier vehicle are adapted to couple to the cruise vehicle to detachably engage.