A landing gear includes a pair of skids, a cross tube and a stiffening portion. The pair of skids is arranged in parallel with a front-rear axis of an airframe of a rotary wing aircraft. The cross tube is attached to the airframe and coupling the pair of skids to each other. The cross tube includes curved portions located closer to end portions of the cross tube than to portions of the cross tube attached to the airframe. The stiffening portion suppresses flattening of the cross tube and is arranged in at least one of internal spaces of the curved portions or a stiffened portion located between a pair of curved portions. The stiffening portion includes an enlarged diameter portion which increases in diameter by an axial fastening power acting in an axial direction of the cross tube, and a fastening portion configured to generate the axial fastening power.

A landing gear includes structural parts arranged to connect a wheel to a structure of an aircraft, each structural part including two or more interfaces for connection to one or more other of the structural parts or to the structure of the aircraft and two or more webs which extend so as to face one another while delimiting between them a free space and which connect the two interfaces in order to transmit the forces from one to the other.

A landing gear includes structural parts arranged to connect a wheel to a structure of an aircraft, each structural part including two or more interfaces for connection to one or more other of the structural parts or to the structure of the aircraft and two or more webs which extend so as to face one another while delimiting between them a free space and which connect the two interfaces in order to transmit the forces from one to the other.

A rotorcraft together with a heat dissipation structure for a motor are provided. The motor includes a body and a revolving shaft driven by the body, and the heat dissipation structure for the motor includes: a casing being a hollow structure having a top opening and an air inlet in a bottom portion, in which the body is disposed inside of the casing, and an air channel is formed between a circumferential edge of the body and an inner wall of the casing; a head cover connected to the revolving shaft of the motor synchronously and provided with a plurality of air flow picks on the lower surface thereof; and a mounting stand fixed to an upper surface of the head cover.

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 method for weight off wheel shock strut servicing includes deflating the shock strut, compressing the shock strut via a jack until the shock strut is in a compressed position, charging the shock strut with an oil until a pressure of the oil reduces a volume of a residual air located inside of the shock strut, lowering the jack until a shock strut piston reaches a pre-determined extension, and charging the shock strut with a gas until the gas comprises a pre-determined pressure.

A method for weight off wheel shock strut servicing includes deflating the shock strut, compressing the shock strut via a jack until the shock strut is in a compressed position, charging the shock strut with an oil until a pressure of the oil reduces a volume of a residual air located inside of the shock strut, lowering the jack until a shock strut piston reaches a pre-determined extension, and charging the shock strut with a gas until the gas comprises a pre-determined pressure.

Disclosed is a package delivery mechanism (PDM) of an unmanned aerial vehicle (UAV). The PDM includes a gravity activated locking mechanism to lock and unlock a package attached to the UAV based on the weight of the package. When the package is attached to suspension means of the UAV that lowers the package to the ground from the UAV, the locking mechanism automatically engages with the package and keeps the package locked to the suspension means, due to the weight of the package. When the package is lowered and reaches on the ground, the weight of the package is offloaded from the suspension means, which enables the locking mechanism to be disengaged, thereby releasing the package. The PDM includes a severing module to sever the suspension means from the UAV.

Certain aspects of the technology disclosed involve a container for delivery by drone (e.g., an unmanned aerial vehicle). The container can include a coupling mechanism to lock and unlock a package attached to the drone based on a tension applied to the coupling mechanism. The package can include sidewalls affixed to a top wall. The sidewalls can include securing mechanisms to be secured to a bottom wall of the container. A rigid extremity can be a contiguous extension of any of the sidewalls and extend below a lower surface of the sidewalls. The rigid extremity can include a malleable contour proximate to a corner of the container. The malleable contour can extend from a base of the rigid extremity through the sidewall. An aperture in the top wall can be configured for a inserting member of a coupling mechanism.