The present disclosure provides a flying water-ski device which enables a person to float in the air and fly in addition to gliding on the water in waterskiing. The flying water-ski device may be equipped with an airfoil having an outer form of a simplified triangle whose top faces toward the front. A flap section which has right and left flap axes may be placed at the back-end of said airfoil and right and left flaps, each of which can rotate around said right and left flap axes. A suspension support section may be suspended from said airfoil, and a harness section fixed to the suspension support section. A first tow rope may be coupled to the airfoil, and a second tow rope coupled to the harness section.

An aircraft includes a fuselage having a nose end and a tail end and a center of gravity. A primary wing is coupled to the fuselage aft of the center of gravity. A secondary wing is coupled to the fuselage forward of the center of gravity. A v-tail is coupled to the fuselage between the primary wing and the tail end of the fuselage, the v-tail comprising first and second angled stabilizers, each of the first and second stabilizers including a first end fixed to the fuselage and a second free end, distal to the fuselage.

An aircraft capable of vertical take-off and landing comprises a fuselage, at least one processor carried by the fuselage and a pair of aerodynamic, lift-generating wings extending from the fuselage. A plurality of vectoring rotors are rotatably carried by the fuselage so as to be rotatable between a substantially vertical configuration relative to the fuselage for vertical take-off and landing and a substantially horizontal configuration relative to the fuselage for horizontal flight. The vectoring rotors are unsupported by the first pair of wings. The wings may be modular and removably connected to the fuselage and configured to be interchangeable with an alternate pair of wings. A cargo container may be secured to the underside of the fuselage, and the cargo container may be modular and interchangeable with an alternate cargo container.

A leg mechanism includes an articulated leg system (100), a passive device (130) and a cable (134). The articulated leg system (100) has a leg portion (128). The passive device (130) is coupled to the articulated leg system and is configured to apply a first force to a portion thereof. The cable (134) is coupled to the articulated leg system (100) and is configured to apply a second force, in opposition to the first force, to a portion thereof. When the cable (134) is drawn away from the articulated leg system (100), the second force moves the leg portion (128) in a first direction. When tension is released from the cable (134), the passive device (130) exerts the first force so as to move the leg portion (128) a second direction that is opposite the first direction.

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.

Disclosed is an unmanned aerial vehicle adapted to be positioned against a substantially vertical wall while hovering in the air, including a body and rotors, an arm end, a first leg end and a second leg end intersected by a front plane and adapted for together contacting the wall at three spaced apart positions, the front plane intersecting a vertical axis of the UAV at an upper side of a first plane spanned by a lateral and longitudinal axis of the UAV, the front plane extending at a first angle of between 45 to 85 degrees to the first plane; wherein the UAV is adapted for tilting upon contact of the first and second leg ends with the wall while the arm end approaches the wall, about the first and second leg ends and towards the wall, until the arm end contacts the wall.

An aerial vehicle and methods of use. The aerial vehicle including a central rotor assembly configured to provide vertical thrust. A fuselage having a longitudinal axis mounted to the central rotor assembly. A plurality of rotors smaller than said central rotor mounted to said fuselage by a frame, includes a propeller, an electrical motor, an electronic speed controller, a flight controller (means for controlling the rotation speed of the central rotor and the smaller rotors). A propulsion system for powering said central rotor, said smaller rotors and said flight controller. Together with control and monitoring systems, the aerial vehicle system enables a new agricultural ecosystem for providing small farmer access to global markets.

A coupling mechanism for coupling a light vehicle to a surface, the coupling mechanism comprising: a magnetic coupling device arranged such that it may be switched between a first mode and a second mode, wherein in the first mode the device generates an external magnetic field less than a first strength, and in the second mode the device generates an external magnetic field of at least a second strength, the second strength being greater than the first strength; and a surface detection unit, coupled to the magnetic coupling device, and arranged to determine when the light vehicle is within a predetermined distance of a surface, wherein in response to the surface detection unit determining that the light vehicle is within the predetermined distance, switching the magnetic coupling device from the first mode to the second mode, to secure the light vehicle to the surface.

A vertical takeoff and landing aircraft (101) for transporting persons or loads, including a plurality of preferably equivalent and redundant electric motors (3) and propellers (2), substantially arranged in one surface, wherein each propeller is assigned an individual electric motor to drive the propeller, the aircraft being characterized in that at least one attitude sensor is provided for attitude control of the aircraft (101) in an active signal connection to at least one signal processing unit which is designed or set up to automatically perform the attitude control based on measurement data from the attitude sensor by regulating the speed of at least some of the electric motors (3), preferably with signal actions of the speed controller assigned to each electric motor such that the aircraft (101) is positioned in space with the surface defined by the propeller (2) substantially horizontal at all times, without control input by a pilot or a remote control.