An aircraft wing includes: a supporting wing portion; and an auxiliary thrust generation wing portion provided behind the supporting wing portion based on a progress direction of an aircraft, and generating force in the direction of thrust by using a pressure change formed at a posterior side of the supporting wing portion while the thrust is applied.

An aircraft wing includes: a supporting wing portion; and an auxiliary thrust generation wing portion provided behind the supporting wing portion based on a progress direction of an aircraft, and generating force in the direction of thrust by using a pressure change formed at a posterior side of the supporting wing portion while the thrust is applied.

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 wing having a main wing and a trailing edge flight control surface movable between a retracted position, a first extended position in which the control surface is positioned rearwardly in the chord wise direction relative to its retracted position, and a second extended position in which the control surface is rotated relative to its retracted position. A closure panel, mounted to the main wing, extends from the main wing to the control surface, to provide an air flow surface between the main wing and control surface, both when the control surface is in its retracted position and its first extended position. The closure panel is movable, relative to the control surface, to an open configuration in which it opens an airflow passage provided between the control surface and an opposed surface of the aircraft wing when the control surface is in its second extended position.

An aircraft wing having a main wing and a trailing edge flight control surface movable between a retracted position, a first extended position in which the control surface is positioned rearwardly in the chord wise direction relative to its retracted position, and a second extended position in which the control surface is rotated relative to its retracted position. A closure panel, mounted to the main wing, extends from the main wing to the control surface, to provide an air flow surface between the main wing and control surface, both when the control surface is in its retracted position and its first extended position. The closure panel is movable, relative to the control surface, to an open configuration in which it opens an airflow passage provided between the control surface and an opposed surface of the aircraft wing when the control surface is in its second extended position.

A parasite aircraft for airborne deployment and retrieve includes a wing; a fuselage rotatably mounted to the wing; a dock disposed on top of the fuselage and configured to receive a maneuverable capture device of a carrier aircraft; a pair of tail members extending from the fuselage; and a plurality of landing gear mounted to the wing. A method of preparing a parasite aircraft for flight includes unfolding an end portion of a wing; unfolding an end portion of a tail member of the parasite aircraft; and rotating a fuselage of the parasite aircraft so that the fuselage is perpendicular to the wing. A method of preparing a parasite aircraft for storage includes rotating a fuselage of the parasite aircraft to be parallel with a wing of the parasite aircraft; folding an end portion of the wing; and folding an end portion of a tail member of the parasite aircraft.

An aircraft safety lifesaving system, which includes an aircraft body, wherein an openable safety cabin is provided at the top of the aircraft body, a deceleration device is provided in the safety cabin, and the deceleration device is capable of being ejected from the safety cabin to enable the aircraft body to decelerate and land; a damping and buffering mechanism is provided at the bottom of the aircraft body, the damping and buffering mechanism is telescopically provided in the vertical direction, and the damping and buffering mechanism is capable of extending to the position below the aircraft wheel body.

An aircraft includes a first battery, provisions for transport that are powered by a second battery, and a management system for transferring energy between the first battery and the second battery.

A simple, safe, and inexpensive flight control system in an aircraft. An anti-torque system for a rotary-wing aircraft has an airfoil with a first surface extending from a first trailing edge and a leading edge, and a second surface extending from a second trailing edge to join the first surface at the leading edge. The airfoil has a first moveable deflector panel pivotally coupled to the first trailing edge, and a second moveable deflector panel pivotally coupled to the second trailing edge. Means are provided to pivot the deflector panels in unison about their respective pivot axes to alter the direction of travel of the airflow downstream of the pivot axes over the surfaces of the deflector panels, thereby producing a lift in a direction perpendicular to the airflow to counteract the torque applied on the aircraft. The flight control system may be arranged within a fixed-wing aircraft.