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.

An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

An aircraft includes a wing and a rotor pod mounted to the wing. The rotor pod includes a body having a forward end and an aft end. A propeller is mounted to the body of the rotor pod at the forward end. A control surface is mounted to the body of the rotor pod between the forward and aft ends and extends outwardly from the body. The control surface is displaceable relative to the body between a first control configuration and a second control configuration to control an attitude of the aircraft. The control surface in the first control configuration is closer to the propeller than the control surface in the second control configuration.

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.

A hybrid aerial vehicle (HAV) comprising: a fuselage of the HAV; a first mechanism within the fuselage for accepting a plurality of wings of the HAV, the first mechanism allowing coordinated contraction of the plurality of wings essentially into the fuselage such that tips of the wings are position in proximity of the fuselage and coordinated extension of the wings such that tips of each wing are positioned away from the fuselage; a first wing extending from the port side of the fuselage and connected to the first mechanism; a second wing extending from the starboard side of the fuselage and connected to the first mechanism; a second mechanism placed within the fuselage in proximity to its front end, the second mechanism allowing motion of propellers of the HAV affixed there to between a first plain and a second plain; a first set of propellers affixed at the port side of the fuselage to the second mechanism; a second set of propellers affixed at the starboard side of the fuselage to the second mechanism; a third mechanism placed within the fuselage in proximity to its rear end, the third mechanism allowing motion of propellers of the HAV affixed there to between a first plain and a second plain, and further placing the propellers affixed thereto to be at a vertical displacement with respect to the propellers affixed to the second mechanism; a third set of propellers affixed at the port side of the fuselage to the third mechanism; and a fourth set of propellers affixed at the starboard side of the fuselage to the third mechanism.

A land-and-air vehicle configured to switch between a first form to be taken during ground traveling and a second form to be taken during flight includes a main body, a main wing unit, an operation unit, and a controller. The controller is configured to control, on the basis of an operation performed on the operation unit by an operator, a behavior of the land-and-air vehicle during the ground traveling and during the flight. The operation unit includes a handle and a step. The handle of the operation unit includes a throttle unit. The controller is configured to control, both during the ground traveling and during the flight, yawing of the land-and-air vehicle in response to an operation performed on the handle, and to control thrust for the land-and-air vehicle during the flight in response to an operation performed on the throttle unit.

A land-and-air vehicle configured to switch between a first form to be taken during ground traveling and a second form to be taken during flight includes a main body, a main wing unit, an operation unit, and a controller. The controller is configured to control, on the basis of an operation performed on the operation unit by an operator, a behavior of the land-and-air vehicle during the ground traveling and during the flight. The operation unit includes a handle and a step. The handle of the operation unit includes a throttle unit. The controller is configured to control, both during the ground traveling and during the flight, yawing of the land-and-air vehicle in response to an operation performed on the handle, and to control thrust for the land-and-air vehicle during the flight in response to an operation performed on the throttle unit.

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.