A bracket for connecting a traverse of a landing gear to a cabin of a helicopter. A landing gear retainer is fixed around the traverse coaxially to the longitudinal direction of the traverse and at least one cabin clamp mount is fixed to the cabin. The landing gear retainer is in between the cabin and upper and lower pendulum bolts and upper and lower pendulum bearings. A pendulum is in longitudinal direction of the traverse hinged to the landing gear retainer. The invention is further related to an application of such brackets.

An unmanned aerial vehicle includes a central body and a plurality of arms extendable from the central body. Each of the plurality of arms is configured to support one or more propulsion units. Each of the plurality of arms is configured to transform between (1) a flight configuration in which the arm is extending away from the central body and (2) a compact configuration in which the arm is folded against the central body. At least one of the plurality of arms is configured to rotate about a first rotational axis and at least a portion of the at least one of the plurality of arms is configured to rotate about a second rotational axis not parallel to the first rotational axis.

An unmanned aerial vehicle includes a central body and a plurality of arms extendable from the central body. Each of the plurality of arms is configured to support one or more propulsion units. Each of the plurality of arms is configured to transform between (1) a flight configuration in which the arm is extending away from the central body and (2) a compact configuration in which the arm is folded against the central body. At least one of the plurality of arms is configured to rotate about a first rotational axis and at least a portion of the at least one of the plurality of arms is configured to rotate about a second rotational axis not parallel to the first rotational axis.

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 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 multi-position landing gear for an aircraft may include a first landing skid disposed on a bottom side of the aircraft, and a second landing skid disposed on one of a top side or the bottom side of the aircraft, wherein the first landing skid and the second landing skid are rotatable relative to the aircraft.

A multi-position landing gear for an aircraft may include a first landing skid disposed on a bottom side of the aircraft, and a second landing skid disposed on one of a top side or the bottom side of the aircraft, wherein the first landing skid and the second landing skid are rotatable relative to the aircraft.

A delivery drone apparatus for automatically delivering packages includes a drone body having a body cavity. A pair of landing skids is coupled to the drone body. A battery, a CPU, and a GPS are coupled within the body cavity. A transceiver is coupled within the body cavity and is in operational communication with the battery, the CPU, and the GPS. The transceiver is configured to communicate with a smartphone. At least one camera is coupled to the drone body. The camera is in operational communication with the battery, the CPU, the GPS, and the transceiver. A plurality of motors are coupled to the drone body. Each motor has a propeller and is in operational communication with the battery and the CPU. An electromagnet is coupled to the drone body. A package magnet is selectively engageable with the electromagnet and is configured to be coupled to a package.

A delivery drone apparatus for automatically delivering packages includes a drone body having a body cavity. A pair of landing skids is coupled to the drone body. A battery, a CPU, and a GPS are coupled within the body cavity. A transceiver is coupled within the body cavity and is in operational communication with the battery, the CPU, and the GPS. The transceiver is configured to communicate with a smartphone. At least one camera is coupled to the drone body. The camera is in operational communication with the battery, the CPU, the GPS, and the transceiver. A plurality of motors are coupled to the drone body. Each motor has a propeller and is in operational communication with the battery and the CPU. An electromagnet is coupled to the drone body. A package magnet is selectively engageable with the electromagnet and is configured to be coupled to a package.

A landing platform for an unmanned aerial vehicle, including a plurality of substantially funnel-shaped centering housings configured to cooperate with a corresponding plurality of projections of the aerial vehicle for reaching a predetermined landing position. The platform can include a mechanism for recharging the battery of the aerial vehicle and/or with an arrangement for serial data transfer.