The present invention relates to a hybrid VTOL jet car comprising a light weight floatable chassis adapted for carrying a payload, a retractable tail section attached to a light weight floatable chassis at rear end adapted for stabilizing the hybrid VTOL jet car, a plurality of wheels at the bottom of the hybrid VTOL jet car, a plurality of retractable wings on the sides of light weight floatable chassis, adapted for manoeuvring the hybrid VTOL jet car. Disclosed embodiments further comprising a plurality of thrust-producing engines adapted for generating the thrust required for driving the hybrid VTOL jet car on a surface as well as in the air and a plurality of parachutes attached to the hybrid VTOL jet car to safely land the hybrid VTOL jet car under emergency.

An aircraft is described with both VTOL (vertical takeoff and landing) capabilities and convention airplane capabilities. A preferred embodiment comprises a fuselage and fixed wing, with one boom on either side of the fuselage. Each boom comprises a tilt rotor on a fore end and a fixed rotor on the aft end. Both rotors can be directed vertically for VTOL capability. During cruise the tilt rotors can be directed forward for thrust and the fixed rotors can be stopped and directed along the boom axis, minimizing drag. The described embodiments have advantages in weight savings and maneuverability compared to other VTOL aircraft.

An aircraft is described with both VTOL (vertical takeoff and landing) capabilities and convention airplane capabilities. A preferred embodiment comprises a fuselage and fixed wing, with one boom on either side of the fuselage. Each boom comprises a tilt rotor on a fore end and a fixed rotor on the aft end. Both rotors can be directed vertically for VTOL capability. During cruise the tilt rotors can be directed forward for thrust and the fixed rotors can be stopped and directed along the boom axis, minimizing drag. The described embodiments have advantages in weight savings and maneuverability compared to other VTOL aircraft.

A wing assembly for an aircraft is disclosed including a wing and a wing tip device at the tip of the wing, wherein the wing tip device is moveable between a flight configuration and a ground configuration. The wing has a spar extension which extends spanwise away from a distal end of the wing, the spar extension having a first end portion fixed in the wing and a second end portion which, in the flight configuration, is positioned in the wing tip device such that, in the flight configuration, the spar extension transmits flight loads between the wing tip device and flight-load bearing structure in the wing. The wing assembly may have an actuation assembly to move the wing tip device.

A wing assembly for an aircraft is disclosed including a wing and a wing tip device at the tip of the wing, wherein the wing tip device is moveable between a flight configuration and a ground configuration. The wing has a spar extension which extends spanwise away from a distal end of the wing, the spar extension having a first end portion fixed in the wing and a second end portion which, in the flight configuration, is positioned in the wing tip device such that, in the flight configuration, the spar extension transmits flight loads between the wing tip device and flight-load bearing structure in the wing. The wing assembly may have an actuation assembly to move the wing tip device.

A wing assembly for an aircraft is disclosed having a wing and a wing tip device at the tip of the wing, wherein the wing tip device is moveable between a flight configuration and a ground configuration. The wing has a spar extension which extends spanwise away from a distal end of the wing, the spar extension having a first end portion fixed in the wing and a second end portion which, in the flight configuration, is disposed in the wing tip device such that, in the flight configuration, the spar extension transmits flight loads between the wing tip device and flight-load bearing structure in the wing. The wing assembly may have an actuation assembly to move the wing tip device.

A wing assembly for an aircraft is disclosed having a wing and a wing tip device at the tip of the wing, wherein the wing tip device is moveable between a flight configuration and a ground configuration. The wing has a spar extension which extends spanwise away from a distal end of the wing, the spar extension having a first end portion fixed in the wing and a second end portion which, in the flight configuration, is disposed in the wing tip device such that, in the flight configuration, the spar extension transmits flight loads between the wing tip device and flight-load bearing structure in the wing. The wing assembly may have an actuation assembly to move the wing tip device.

A vertical take-off and landing (VTOL) unmanned aerial vehicle having a foldable fixed wing and a twin-ducted fan power system (7) arranged at a tail portion of a fuselage in a transverse and tail propulsion arrangement provides lift for vertical take-off and landing and propulsion for horizontal flight. By means of deflection of a control servo plane arranged at a duct exit, a vectored thrust is provided to enable a fast attitude change. When the aerial vehicle takes off and lands vertically/flies at a low speed, the wing is folded to reduce the frontal area exposure to crosswind. When the aerial vehicle is flying horizontally, the wing is expanded to obtain larger lift. A Coanda effect is created at a trailing edge of the wing by suction of the duct to improve performance.

An expanding pin system is described that can provide automated and/or power controlled locking and unlocking of an expanding pin assembly in a mechanical joint. For example, the expanding pin system can include an actuation assembly that includes a single actuator (e.g., motor) to control an expanding pin assembly for locking and unlocking a mechanical joint.

Apparatus and methods for limiting trailing edge deflection in aircraft folding wing tips are disclosed herein. An example aircraft wing disclosed herein includes a fixed wing portion. The fixed wing portion includes an outboard rib. The aircraft wing also includes a wing tip moveably coupled to the fixed wing portion. The wing tip is moveable between an extended position and a folded position. The wing tip includes an inboard rib that is disposed in a trailing edge section of the wing tip. The wing tip includes a stop plate coupled to the inboard rib. The stop plate extends inboard from the inboard rib such that when the wing tip is in the extended position, the stop plate is disposed below a portion of the outboard rib of the fixed wing portion to limit upward deflection of the trailing edge section of the wing tip relative to the fixed wing portion.