A system for indicating the pressure in an aircraft landing gear shock absorber is provided, the system comprising a source of collimated light and a target, the source of collimated light being attached to the aircraft, and being operable to emit light onto the target; the position of the point of incidence of the light emitted from the source of collimated light on the target being indicative of the pressure in the aircraft landing gear shock absorber. A kit for making such a system and a method of indicating the pressure in an aircraft landing gear are also provided.

A system for indicating the pressure in an aircraft landing gear shock absorber is provided, the system comprising a source of collimated light and a target, the source of collimated light being attached to the aircraft, and being operable to emit light onto the target; the position of the point of incidence of the light emitted from the source of collimated light on the target being indicative of the pressure in the aircraft landing gear shock absorber. A kit for making such a system and a method of indicating the pressure in an aircraft landing gear are also provided.

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 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 method for producing a hollow part (17; 21; 46) made of a metal material, includes preparing a blank (1; 18; 33) of the metal material of the hollow part (17; 21; 46), and at least one sacrificial mandrel (2; 19; 34, 35) made of a material which has a yield stress in the range from −30% to +20% of the yield stress of the material of the blank (1; 18; 33), preferably in the range from −15% to +10%, ideally in the range from −5% to +3%; applying a punch (10) on at least one of the ends of the blank (1; 18; 33) in order to produce the expansion of at least a portion of said blank (1; 18; 33) and to create at least one internal space (12; 20; 36, 37) inside said blank (1; 18; 33); inserting a sacrificial mandrel (2; 19; 34; 35) in said an internal space (12; 20; 37) of the blank (1; 18; 33);crimping the sacrificial mandrel (2; 19; 34, 35) in said blank (1; 18; 33);producing, by co-forging, a simultaneous deformation of said blank (1; 18; 33) and of said sacrificial mandrel (2; 19; 34, 35), with a homothetic ratio K; and performing a machining in order to remove the sacrificial mandrel (2; 19; 34, 35).

An example method includes receiving pitch angle sensor information indicative of a pitch angle of a vehicle, wherein the vehicle comprises a main landing gear having a strut and a pitch control surface configured to control the pitch angle of the vehicle; determining a trailing-edge-up limit for upward movement of the pitch control surface to control a de-rotation rate of the vehicle as the vehicle lands; receiving load sensor information indicative of a load on the strut of the main landing gear of the vehicle; based on the pitch angle of the vehicle being below a pitch angle threshold, determining an updated trailing-edge-up limit based on the load on the strut; and controlling the pitch control surface based on the updated trailing-edge-up limit.

A multi-propeller assembly for a drone, the multi-propeller includes a housing, a motor coupled having a circular cavity surrounded by a plurality of magnets disposed at the opposing second side of the housing, a first, second, and third three-bladed propeller having drive members rotatably coupled within the circular cavity of the motor and nested within each other, wherein the motor is configured to simultaneously rotate the first and third three-bladed propeller in a first direction and the second three-bladed propeller in an opposite second direction using the plurality of magnets.

A bearing having an electrically conductive sleeve and a self-lubricating liner wherein the electrically conductive sleeve comprises a first portion and a second portion, the first portion and the second portion having respectively an inner surface and an outer surface; the self-lubricating liner extends over the inner surface of the first portion of the electrically conductive sleeve to define a first tubular volume, the first tubular volume having a first diameter and a first longitudinal axis; and the inner surface of the second portion of the electrically conductive sleeve defines a second tubular volume, the second tubular volume having the same diameter and the same longitudinal axis as the first tubular volume.

An aircraft landing gear assembly comprising: a ground contacting part, an aircraft attachment part, and a component comprising: a first base member and a second base member separated along a first longitudinal axis, a plurality of first connecting points on the first base member arranged in a first regular polygon, a plurality of second connecting points on the second base member arranged in a second regular polygon, the second regular polygon having the same number of sides as the first regular polygon, and a plurality of first straight beams fixed to the first and second base members at the first and second connecting points and extending between the first and second base members, each beam aligned skew to the longitudinal axis.

An example method includes receiving pitch angle sensor information indicative of a pitch angle of a vehicle, wherein the vehicle comprises a main landing gear having a strut and a pitch control surface configured to control the pitch angle of the vehicle; determining a trailing-edge-up limit for upward movement of the pitch control surface to control a de-rotation rate of the vehicle as the vehicle lands; receiving load sensor information indicative of a load on the strut of the main landing gear of the vehicle; based on the pitch angle of the vehicle being below a pitch angle threshold, determining an updated trailing-edge-up limit based on the load on the strut; and controlling the pitch control surface based on the updated trailing-edge-up limit.