A system and method for transformation of motor transportation vehicle for ground and air transport, motor transportation vehicle are disclosed. The motor transportation vehicle consists of the body with the cabin, the front and rear axles, an actuation system, wings, covers, and tail including the support and the tail surfaces, and for transformation of the motor transportation vehicle for air transport to the motor transportation vehicle for ground transport the following transformation steps are preformed: minimization of the wings footprint area by turning the wings around their horizontal axes, which axes run through the halves or near the halves of the wing widths; opening two body covers; turning the folded wings into the vertical position; turning the folded wings from the vertical position towards rear position around the horizontal axis perpendicular to the length of the motor transportation vehicle, followed by closing the body covers tilting the support cover/covers out; retracting the support/supports of the tail surfaces under the opened support covers; closing the support cover/covers.

An aircraft float includes a float body configured to provide buoyancy to an aircraft, and a lower portion of the float body is configured to contact water. The lower portion of the float body includes a turbulator.

An aircraft float includes a float body configured to provide buoyancy to an aircraft. The float body includes a skin. A longitudinally extending structural member is located internal to the skin, and the longitudinally extending structural member is coupled to an upper portion of the skin.

An amphibious robot includes a housing including a first shell and a second shell and having a first configuration and a second configuration, a rack disposed in an inner cavity of the housing, a telescopic assembly disposed on the rack and connected between the first shell and the second shell, and a rotary wing assembly disposed on the rack and having a folded configuration and a flight configuration. The rotary wing assembly includes: a folding arm with one end rotatably connected to the rack, a rotary wing, and a tilting arm connected between the rotary wing and the folding arm, the tilting arm and the rotary wing are extended to an outside of the housing to be adapted to drive the robot to fly in the flight configuration, and the tilting arm is rotatable relative to the folding arm to adjust a rotation direction of the rotary wing.

An underwater and aerial vehicle includes a fixing frame, a core navigation system and an energy supply system. The fixing frame has a circular ring configuration in a middle part thereof, and the waterproof sealing cabin is fixed in the circular ring configuration, and multiple cantilever arms extend around the circular ring configuration. An underwater navigation control module and a relay are provided on an auxiliary fixing platform. A second brushless motor is provided on each of the cantilever arms. Each second brushless motor is provided with a marine propeller. A flight control module, a remote control receiver and a power management module are provided on a fixing platform. A first brushless motor is provided on each of the cantilever arms. Each first brushless motor is provided with a rotor via a coupling. The energy supply system is arranged in a lower part of the waterproof sealing cabin.

The invention provides a float plane having a fuselage, a wing, and two floats mounted to the fuselage. In one group of embodiments, the float plane is a firefighting float plane that includes a water tank and a water scooping assembly. In another group of embodiments, the float plane includes a spreader bar suspension assembly. In certain embodiments, the float plane is a firefighting float plane that includes a water tank, a water scooping assembly, and a spreader bar suspension assembly.

A manual wing-fold mechanism provides a means by which to reconfigure the wing of an aircraft between a flight configuration and one that can be easily stowed and transported. The folding mechanism includes an extension tube that enables the outboard portion of the wing to be extended away from the inboard section of the wing, rotated about the lateral axis of the aircraft and then pivoted rearward so that the wing is aligned with the longitudinal axis of the aircraft along side the fuselage. The wing-fold mechanism is independent of the structural components of the wing used to convey aerodynamic loads during flight and provides a means for the user to bring the outboard wing section into a near alignment position while the wing-fold mechanism thereafter assists to refine the alignment into its final flight configuration.

An aircraft having a longitudinal axis determining a fore-aft direction, comprising at least two floats configured to support the aircraft on a ground medium located below the floats with a ground-facing side of the floats, wherein each float comprises: a first support wheel and a second support wheel, the first support wheel being located within the float further in the fore direction than the second support wheel, wherein at least the first support wheel is located within the float so that it protrudes partly out of the ground-facing side of the float; wherein the first support wheel protrudes out of the ground-facing side of the float so that an angle between a first line z1 tangential to a float profile line, intersecting the float profile line in front of the first support wheel on the ground-facing side, which has the smallest angle with respect to the horizontal axis of the float, and which intersects the profile line within a circle C concentric with the first support wheel and of a radius 2R being two times larger than a radius R of the first support wheel, the first line z1 intersecting the circumference of the first support wheel in point B, and a second line z2 tangential to the circumference of the first support wheel point B, wherein the first line z1 and the second line z2 are comprised within the same, vertical plane, which is parallel to the fore-aft direction, is comprised in a range 145-175.

An aircraft includes a central wing accommodating passengers and/or freight and two lateral wings that pivot on the central wing about respective axes of rotation. The various wings obey the following geometric characteristics: 0.3?Long<L.sub.arg<L.sub.ong, 0.11?L.sub.ong<H.sub.aut<0.25?L.sub.ong, E.sub.nv>1.4?L.sub.ong, wherein L.sub.arg being the distance between the two axes, L.sub.ong being the length of the central wing, H.sub.aut being the height of the central wing, E.sub.nv being the wingspan of the aircraft. The axes of rotation are inclined by an angle relative to the vertical axis of the aircraft such that the lateral pivot from rear to front and vice versa so as to come closer to, or deploy on either side from, the fuselage.

A robot includes a housing including a first shell and a second shell and having a first configuration and a second configuration, a rack disposed in an inner cavity of the housing, a telescopic assembly disposed on the rack and connected between the first shell and the second shell, and a rotary wing assembly disposed on the rack and having a folded configuration and a flight configuration. The rotary wing assembly includes: a folding arm with one end rotatably connected to the rack, a rotary wing, and a tilting arm connected between the rotary wing and the folding arm, the tilting arm and the rotary wing are extended to an outside of the housing to be adapted to drive the robot to fly in the flight configuration, and the tilting arm is rotatable relative to the folding arm to adjust a rotation direction of the rotary wing.