A modular vehicle system includes at least one body module having at least one body connection interface, and a kit. The kit includes a plurality of utility modules including at least one first utility module (in the form of a fixed-wing utility module) and at least one second utility module (in the form of a rotor-wing utility module). Each first utility module includes at least one utility module connection interface in the form of a first utility module connection interface for coupling with the body connection interface. Each second utility module includes at least one utility module connection interface in the form of a second utility module connection interface, distinct from the first utility module connection interface, for coupling with the body connection interface. Each body connection interface is configured for selective reversible coupling at least with respect to any one of the utility module connection interfaces while concurrently excluding coupling of another utility module connection interface thereto, to provide an air vehicle.

A motor vehicle (100) has four centreless wheels (10) drivable for use on the ground and four propellers (16) rotatable within the open centres of the wheels (10) for use in the air. The wheel-propeller assemblies (10, 16) are carried on mounting units (14) secured to a frame (12). The mounting units (14) are rotatable on the frame (12) and the wheel-propeller assemblies (10, 16) are rotatable on their respective mounting units (14), in each case by means of servomotors, to convert the vehicle (1009) from its ground mode shown in FIG. 1 to its air mode as shown in FIG. 2, and also to turn the wheel-propeller assemblies (10, 16) so as to steer the vehicle (100) when on the ground and to tilt the wheel-propeller assemblies (10, 16) so as to direct the vehicle (100) when in the air.

A motor vehicle (100) has four centreless wheels (10) drivable for use on the ground and four propellers (16) rotatable within the open centres of the wheels (10) for use in the air. The wheel-propeller assemblies (10, 16) are carried on mounting units (14) secured to a frame (12). The mounting units (14) are rotatable on the frame (12) and the wheel-propeller assemblies (10, 16) are rotatable on their respective mounting units (14), in each case by means of servomotors, to convert the vehicle (1009) from its ground mode shown in FIG. 1 to its air mode as shown in FIG. 2, and also to turn the wheel-propeller assemblies (10, 16) so as to steer the vehicle (100) when on the ground and to tilt the wheel-propeller assemblies (10, 16) so as to direct the vehicle (100) when in the air.

An unmanned aircraft (100) according to the present disclosure is equipped with a flight propeller (2) and includes a main body (1), a locomotion unit having an aquatic locomotion mechanism and a terrestrial locomotion mechanism independent of the flight propeller, and a connector that connects the main body and the locomotion mechanisms.

The current technique provides an unmanned vehicle that is capable of travelling in the air, on the ground and/or in the water. The driving force of the unmanned vehicle is provided by at least one propelling module that includes a motor, a shaft and a propeller. The propelling module is coupled to a chassis. The chassis includes one or more support elements that each couples to one or more aileron member. An aileron member is configured to tilt with or about the support element to change fluid flux about the aileron member and thus change a position of the propelling force.

The current technique provides an unmanned vehicle that is capable of travelling in the air, on the ground and/or in the water. The driving force of the unmanned vehicle is provided by at least one propelling module that includes a motor, a shaft and a propeller. The propelling module is coupled to a chassis. The chassis includes one or more support elements that each couples to one or more aileron member. An aileron member is configured to tilt with or about the support element to change fluid flux about the aileron member and thus change a position of the propelling force.

A vertical take-off and landing (VTOL) aircraft has a first drivable configuration in which the pilot seat is positioned between the wings and facing the direction of forward travel. The VTOL may be driven in the first configuration as a normal automobile. In the first configuration the wings are aligned with the direction of forward travel and their surfaces are vertically oriented. In the first configuration, the VTOL may also attain altitude and be maneuvered using thrust from propulsion sources. In a second configuration, the pilot seat is rotated 90 degrees from the direction of forward travel to a direction of forward flight. Forward flight is achieved using thrust to rotate the wings from the vertical orientation to a lift-providing orientation. In concert with the rotation of the wings, the pilot seat is counter-rotated to maintain the seat facing the direction of forward flight.

A vertical take-off and landing (VTOL) aircraft has a first drivable configuration in which the pilot seat is positioned between the wings and facing the direction of forward travel. The VTOL may be driven in the first configuration as a normal automobile. In the first configuration the wings are aligned with the direction of forward travel and their surfaces are vertically oriented. In the first configuration, the VTOL may also attain altitude and be maneuvered using thrust from propulsion sources. In a second configuration, the pilot seat is rotated 90 degrees from the direction of forward travel to a direction of forward flight. Forward flight is achieved using thrust to rotate the wings from the vertical orientation to a lift-providing orientation. In concert with the rotation of the wings, the pilot seat is counter-rotated to maintain the seat facing the direction of forward flight.

A wingless vertical take-off and landing (VTOL) vehicle has a main body including airfoil sections on either side of a central module in which a load may be carried. Articulated forward thrust systems are mounted on a leading edge of the main body and lateral members are located on either side of the main body and form winglets. At least one rear vertical-thrust system may also be provided and, in one embodiment, is mounted in an aperture aft of the central module. The forward thrust systems transition between a vertical flight configuration and a horizontal flight configuration. The lateral members are configured as both vortex-damping members and also to channel backwash from the forward thrust systems over the airfoil formed by the main body.

A wingless vertical take-off and landing (VTOL) vehicle has a main body including airfoil sections on either side of a central module in which a load may be carried. Articulated forward thrust systems are mounted on a leading edge of the main body and lateral members are located on either side of the main body and form winglets. At least one rear vertical-thrust system may also be provided and, in one embodiment, is mounted in an aperture aft of the central module. The forward thrust systems transition between a vertical flight configuration and a horizontal flight configuration. The lateral members are configured as both vortex-damping members and also to channel backwash from the forward thrust systems over the airfoil formed by the main body.