A landing gear lifting/lowering EHA system includes: a hydraulic actuator configured to lift and lower the leg of an aircraft; at least one electrically operated hydraulic pump; a hydraulic path; a pressure sensor attached to the hydraulic actuator or the hydraulic path and configured to output a measurement signal corresponding to hydraulic pressure; and a controller configured to output a control signal to the electrically operated hydraulic pump, wherein, when a state in which the hydraulic pressure exceeds a set pressure continues for a set time, the control unit stops the electrically operated hydraulic pump in operation and resumes the operation of the electrically operated hydraulic pump after the hydraulic pressure drops to or below a second set pressure after the electrically operated hydraulic pump is stopped.

A landing gear lifting/lowering EHA system includes: a hydraulic actuator configured to lift and lower the leg of an aircraft; at least one electrically operated hydraulic pump; a hydraulic path; a pressure sensor attached to the hydraulic actuator or the hydraulic path and configured to output a measurement signal corresponding to hydraulic pressure; and a controller configured to output a control signal to the electrically operated hydraulic pump, wherein, when a state in which the hydraulic pressure exceeds a set pressure continues for a set time, the control unit stops the electrically operated hydraulic pump in operation and resumes the operation of the electrically operated hydraulic pump after the hydraulic pressure drops to or below a second set pressure after the electrically operated hydraulic pump is stopped.

A retractable landing gear on an aircraft is operated by a landing gear control system 20 having a manually operable lever 26 movable from a first, e.g. gear-down, position to a second, e.g. gear-up position, in response to which a signal (e.g. a gear-up command) is outputted causing the landing gear to move to an up position. The landing gear control system 20 also includes a motor 40 configured to move the lever 26 in dependence on a signal, for example a signal received by a landing gear lever control unit 42 from a take-off detection system 46 which indicates that the aircraft has taken-off. Thus, the lever 26 may be considered as being configured both to be operated by a pilot of the aircraft manually and to be operated by the motor automatically.

Aspects relate to systems and methods for controlling landing gear of an aircraft. An exemplary system includes a nose gear located at a nose of the aircraft, where the nose gear includes a nose piston configured to allow for displacement of a nose wheel relative the aircraft, a main gear located aft of the nose gear, where the main gear includes a main piston configured to allow for displacement of a main wheel relative the aircraft, a hydraulic circuit in fluidic communication with each of the nose piston and the main piston, and a compliant element in fluidic communication with the hydraulic circuit and configured to provide a compliant response at one or both of the nose piston and the main piston.

A structural component, or parts thereof, for a machine system or vehicle, such as an aircraft, is provided. In some examples, the structural component includes at least one embedded passageway or line. In other examples, the passageway or line is formed integrally on the exterior surface of the structural component. In some of these examples, the structural component can benefit from additive manufacturing techniques or methodologies.

A multi-mode unmanned aerial vehicle includes an elongated fuselage, a right and left fixed wing extending from a respective right and left side of the elongated fuselage, a right and left tilt wing attached at a first side to a free end of the respective right and left fixed wing, a right and left duct attached to a second side of the respective right and left tilt wing, a right and left winglet attached to the respective right and left duct opposite to the right and left tilt wing, a tilt tail located within a curved guide slot at a rear end of the elongated fuselage, a rear duct attached to the tilt tail, a tilting mechanism, and an integrated autonomous flight control system.

A multi-mode unmanned aerial vehicle includes an elongated fuselage, a right and left fixed wing extending from a respective right and left side of the elongated fuselage, a right and left tilt wing attached at a first side to a free end of the respective right and left fixed wing, a right and left duct attached to a second side of the respective right and left tilt wing, a right and left winglet attached to the respective right and left duct opposite to the right and left tilt wing, a tilt tail located within a curved guide slot at a rear end of the elongated fuselage, a rear duct attached to the tilt tail, a tilting mechanism, and an integrated autonomous flight control system.

Systems and methods for communicating a signal over a hydraulic line in a vehicle are provided. In one embodiment, a system can include a hydraulic line. The hydraulic line can include at least one communication medium for propagating a communication signal. The system can also include at least one signal communication device configured to receive the communication signal communicated over the hydraulic line. The system can also include at least one vehicle component in communication with the at least one signal communication device.

An aircraft undercarriage includes a leg for mounting on a structure of the aircraft so as to be movable between a deployed position and a retracted position, the undercarriage being fitted with a breaker strut including two hinged elements that are hinged together at a knee, with a first element for coupling to the structure of the aircraft and a second element for coupling to the undercarriage, a return member being arranged between the two elements to urge them towards a substantially aligned position that is defined by respective abutments. According to the invention, one of the strut elements incorporates a linear actuator having a slidable rod that is coupled to the other strut element by means of a link, the assembly being arranged in such a manner that moving the slidable rod of the actuator in a single direction causes, in succession, the elements of the strut to move out of alignment and the undercarriage to move from the deployed position to the retracted position.

An aircraft undercarriage includes a leg for mounting on a structure of the aircraft so as to be movable between a deployed position and a retracted position, the undercarriage being fitted with a breaker strut including two hinged elements that are hinged together at a knee, with a first element for coupling to the structure of the aircraft and a second element for coupling to the undercarriage, a return member being arranged between the two elements to urge them towards a substantially aligned position that is defined by respective abutments. According to the invention, one of the strut elements incorporates a linear actuator having a slidable rod that is coupled to the other strut element by means of a link, the assembly being arranged in such a manner that moving the slidable rod of the actuator in a single direction causes, in succession, the elements of the strut to move out of alignment and the undercarriage to move from the deployed position to the retracted position.