A wing structure for a vehicle, and a vehicle. The wing structure comprises at least one multi-connecting-rod structure. The multi-connecting-rod structure is arranged in a direction extending from the main body of a vehicle to a wingtip, each multi-connecting-rod mechanism comprises a plurality of connecting rods, and connecting rods which are adjacent to each other are connected by means of a motor. The present technical solution provides a wing structure having the feature of a morphing wing having a large range in both chordwise and spanwise directions. The wing structure has the capability of changing airfoil and changing a pitch angle within a large range, the capability of twisting along a spanwise direction at a distal portion, the capability of swinging perpendicularly within a large range along the plane in which the main body of the vehicle is located, and the capability of swinging longitudinally within a large range along the main body of the vehicle, adjustment can be performed on a complex flow field or environment, the motion speed and the motion efficiency are significantly improved, and high maneuvering actions can be achieved.

A multi-segment oblique flying wing aircraft which has three distinct segments including two outer wing segments and a central wing segment. The central segment may be thicker in the vertical direction and adapted to hold pilots and passengers. The outer wing segments may be substantially thinner and may taper as they progress outboard from the wing center. The multi-segment oblique flying wing aircraft be adapted for rotating into a high speed flight configuration, or may be adapted for take-off and cruise at a constant angle. In an extreme flight case, the central wing segment may rotate to a local sweep of ninety degrees.

A multi-segment oblique flying wing aircraft which has three distinct segments including two outer wing segments and a central wing segment. The central segment may be thicker in the vertical direction and adapted to hold pilots and passengers. The outer wing segments may be substantially thinner and may taper as they progress outboard from the wing center. The multi-segment oblique flying wing aircraft be adapted for rotating into a high speed flight configuration, or may be adapted for take-off and cruise at a constant angle. In an extreme flight case, the central wing segment may rotate to a local sweep of ninety degrees.

A method for realizing a vertical take-off and landing aircraft that does not use a mechanism dedicated for take-off and landing, which cannot be achieved on the basis of an existing concept of aircraft flight control, by introducing a new concept of a shoulder rotational axis and an arm rotational axis into aircraft flight control and controlling vertical take-off and landing and ordinary flight with the same mechanism. This instruction eliminates a necessity of a tail and ailerons from an airframe of the aircraft, enables reduction of manufacturing, maintenance, and running costs thereof, and makes it possible to avoid problems of maneuverability and cruising distance performance of airframes of vertical take-off and landing aircrafts.

A method for realizing a vertical take-off and landing aircraft that does not use a mechanism dedicated for take-off and landing, which cannot be achieved on the basis of an existing concept of aircraft flight control, by introducing a new concept of a shoulder rotational axis and an arm rotational axis into aircraft flight control and controlling vertical take-off and landing and ordinary flight with the same mechanism. This instruction eliminates a necessity of a tail and ailerons from an airframe of the aircraft, enables reduction of manufacturing, maintenance, and running costs thereof, and makes it possible to avoid problems of maneuverability and cruising distance performance of airframes of vertical take-off and landing aircrafts.

A yaw alleviation device for an aircraft containing rotatable wing roots attached to wings. The device includes a spring configured to operatively connect to a wing; and a buckling member to operatively connect to the wing. The spring is configured to extend from an original unstrained position upon the buckling member undergoing buckling from an original unbuckled position to cause rotation of one or both wings in rotationally opposite directions. The buckling member may be positioned parallel and at an offset distance to the spring.

A yaw alleviation device for an aircraft containing rotatable wing roots attached to wings. The device includes a spring configured to operatively connect to a wing; and a buckling member to operatively connect to the wing. The spring is configured to extend from an original unstrained position upon the buckling member undergoing buckling from an original unbuckled position to cause rotation of one or both wings in rotationally opposite directions. The buckling member may be positioned parallel and at an offset distance to the spring.

An unmanned aerial vehicle (UAV) having wings stowed against a fuselage of the UAV in a first arrangement is disclosed. Methods and systems for deploying the wings into a second arrangement are disclosed. For example, after a launch of the UAV, the UAV monitors for at least one pre-set condition. The at least one pre-condition being a pre-condition associated with deploying wings of the UAV into the second arrangement. Upon detecting the at least one pre-set condition, the wings of the UAV are deployed into a second arrangement. Deploying the wings comprises activating, in response to detecting the at least one pre-set condition associated with the UAV, a gearbox configured to transition the wings from the first arrangement to the second arrangement. Roll control may be maintained throughout launch and deployment.

An unmanned aerial vehicle (UAV) having wings stowed against a fuselage of the UAV in a first arrangement is disclosed. Methods and systems for deploying the wings into a second arrangement are disclosed. For example, after a launch of the UAV, the UAV monitors for at least one pre-set condition. The at least one pre-condition being a pre-condition associated with deploying wings of the UAV into the second arrangement. Upon detecting the at least one pre-set condition, the wings of the UAV are deployed into a second arrangement. Deploying the wings comprises activating, in response to detecting the at least one pre-set condition associated with the UAV, a gearbox configured to transition the wings from the first arrangement to the second arrangement. Roll control may be maintained throughout launch and deployment.

A flight control surface with an actuator with an aerodynamic fairing for a swept aircraft wing. The swept aircraft wing includes a movable flight control surface with a hinge line non-perpendicular to the line of flight of the aircraft, and an actuator arm configured to actuate the flight control surface. The actuator arm includes a longitudinal axis substantially aligned with the line of flight, the actuator arm extending at least partially from an outer surface of the aircraft wing, and a fairing arranged on the outer surface of the aircraft wing to at least partially cover the actuator arm. Aligning the actuator arm with the line of flight of the aircraft may allow for an improved fairing to be provided.