Landing gear for an aircraft, the landing gear having at least one pair of shock absorbers comprising a first shock absorber and a second shock absorber, each shock absorber comprising a cylinder defining an inside space and a rod carrying a piston, the inside space being subdivided at least into a “primary” chamber and into a “secondary” chamber, the shock absorber including at least one throttling orifice putting the secondary chamber into fluid flow communication with the primary chamber. The primary chamber of the first shock absorber is connected to the secondary chamber of the second shock absorber of the pair by a first pipe, and the secondary chamber of the first shock absorber of the pair is connected to the primary chamber of the second shock absorber of the pair by a second pipe.

Landing gear for an aircraft, the landing gear having at least one pair of shock absorbers comprising a first shock absorber and a second shock absorber, each shock absorber comprising a cylinder defining an inside space and a rod carrying a piston, the inside space being subdivided at least into a “primary” chamber and into a “secondary” chamber, the shock absorber including at least one throttling orifice putting the secondary chamber into fluid flow communication with the primary chamber. The primary chamber of the first shock absorber is connected to the secondary chamber of the second shock absorber of the pair by a first pipe, and the secondary chamber of the first shock absorber of the pair is connected to the primary chamber of the second shock absorber of the pair by a second pipe.

The invention relates to a surfing arrangement (3) for mounting to underneath an aircraft (1), comprising at least a tank of a water collecting system (10), which arrangement (3) is configured for providing a gliding surface (7) on which said aircraft (1) may surf on water when having a moving speed higher than a predetermined value. The arrangement (3) comprises an elongated body (9), underneath which elongated body (9) the gliding surface (7) is situated, wherein the elongated body (9) is connectable to underneath an aircraft (1) by means of a linkage arm arrangement (23) arranged to a coupling element (25) configured to be coupled to the aircraft (1). The linkage arm arrangement (23) is, when the arrangement (3) is coupled to an aircraft (1), operational to vertically move the elongated body (9) between a raised position, in which raised position the gliding surface (7) is positioned above a lowermost contact point of a piece of a landing gear (5), and a lower position, in which lower position the gliding surface (7) is positioned underneath said lowermost contact point of the piece of said landing gear (5). Said movement of the elongated body (9) being selectively operational during flight of the aircraft (1). The invention further relates to an aircraft (1) comprising such a surfing arrangement (3).

The invention relates to a surfing arrangement (3) for mounting to underneath an aircraft (1), comprising at least a tank of a water collecting system (10), which arrangement (3) is configured for providing a gliding surface (7) on which said aircraft (1) may surf on water when having a moving speed higher than a predetermined value. The arrangement (3) comprises an elongated body (9), underneath which elongated body (9) the gliding surface (7) is situated, wherein the elongated body (9) is connectable to underneath an aircraft (1) by means of a linkage arm arrangement (23) arranged to a coupling element (25) configured to be coupled to the aircraft (1). The linkage arm arrangement (23) is, when the arrangement (3) is coupled to an aircraft (1), operational to vertically move the elongated body (9) between a raised position, in which raised position the gliding surface (7) is positioned above a lowermost contact point of a piece of a landing gear (5), and a lower position, in which lower position the gliding surface (7) is positioned underneath said lowermost contact point of the piece of said landing gear (5). Said movement of the elongated body (9) being selectively operational during flight of the aircraft (1). The invention further relates to an aircraft (1) comprising such a surfing arrangement (3).

A rotorcraft and a connecting structure for an arm and an airframe of a rotorcraft are provided. The connecting structure includes: a fixed sleeve pipe configured to extend out from a circumferential edge of the airframe; an insertion head configured to be disposed to the first end of the arm and configured to be inserted into the fixed sleeve pipe; a lock sleeve configured to be fitted over the arm and having an insertion portion configured to be embedded into the insertion groove; and a lock nut configured to be fitted over the arm and configured for being in threaded connection with the fixed sleeve pipe.

A rotorcraft and a connecting structure for an arm and an airframe of a rotorcraft are provided. The connecting structure includes: a fixed sleeve pipe configured to extend out from a circumferential edge of the airframe; an insertion head configured to be disposed to the first end of the arm and configured to be inserted into the fixed sleeve pipe; a lock sleeve configured to be fitted over the arm and having an insertion portion configured to be embedded into the insertion groove; and a lock nut configured to be fitted over the arm and configured for being in threaded connection with the fixed sleeve pipe.

An aircraft landing gear assembly has a longitudinally elongated frame coupled to a lower portion of a fuselage of an aircraft, the frame being capable of supporting at least a portion of the weight of the aircraft. A fairing encloses substantially all of the frame. An optional integrated step can be carried by the frame, and a longitudinally elongated aperture would be formed in the fairing adjacent the step. The step allows a user to place a foot into the aperture and onto the step. An optional door can cover the aperture, and an optional secondary step can be carried by the door.

An aircraft landing gear assembly has a longitudinally elongated frame coupled to a lower portion of a fuselage of an aircraft, the frame being capable of supporting at least a portion of the weight of the aircraft. A fairing encloses substantially all of the frame. An optional integrated step can be carried by the frame, and a longitudinally elongated aperture would be formed in the fairing adjacent the step. The step allows a user to place a foot into the aperture and onto the step. An optional door can cover the aperture, and an optional secondary step can be carried by the door.

An unmanned aerial vehicle (UAV) includes a vehicle body and a multi-ocular imaging assembly. The multi-ocular imaging assembly includes at least two imaging devices disposed in and fixed to the vehicle body.

An unmanned aerial vehicle (UAV) includes a vehicle body and a multi-ocular imaging assembly. The multi-ocular imaging assembly includes at least two imaging devices disposed in and fixed to the vehicle body.