Technologies for providing blended wing body aircraft control surfaces are described herein. In some examples, one or more of the control surfaces have angular configurations that reduce the formation of air vortexes when in upward or downward configurations, thereby reducing the drag on the aircraft when the control surfaces are being used.

A wingless compact aircraft, with limited footprint and no exposed high-speed moving parts. The aircraft can takeoff and land vertically, can fly at high-speed and even cruise on land and water in one of the preferred embodiments.

A wingless compact aircraft, with limited footprint and no exposed high-speed moving parts. The aircraft can takeoff and land vertically, can fly at high-speed and even cruise on land and water in one of the preferred embodiments.

An aerodynamic surface for an aircraft, comprising a torsion box, a movable control surface, and a central element, the torsion box comprising a rear spar, upper and lower covers, and the movable control surface comprising a leading edge, a front spar, a hinge line, a beam having a first end and a second end, and a counterweight attached to the second end of the beam. The first end of the beam is attached to the front spar, and the second end is projected beyond at least the hinge line so that the counterweight is arranged between the upper and lower covers extending from the rear spar of the torsion box towards the movable control surface.

An aerodynamic surface for an aircraft, comprising a torsion box, a movable control surface, and a central element, the torsion box comprising a rear spar, upper and lower covers, and the movable control surface comprising a leading edge, a front spar, a hinge line, a beam having a first end and a second end, and a counterweight attached to the second end of the beam. The first end of the beam is attached to the front spar, and the second end is projected beyond at least the hinge line so that the counterweight is arranged between the upper and lower covers extending from the rear spar of the torsion box towards the movable control surface.

Linkage assemblies for aircraft wing hinged panels are described herein. An example linkage assembly includes a flap follower arm coupled between a spoiler support beam and a flap, a rocker, a panel link coupled between the hinged panel and the rocker, and a cross-bar link coupled between the flap follower arm and the rocker. The flap follower arm, the rocker, the panel link, and the cross-bar link are configured to coordinate adjustment of positions of the hinged panel and the flap relative to each other.

Linkage assemblies for aircraft wing hinged panels are described herein. An example linkage assembly includes a flap follower arm coupled between a spoiler support beam and a flap, a rocker, a panel link coupled between the hinged panel and the rocker, and a cross-bar link coupled between the flap follower arm and the rocker. The flap follower arm, the rocker, the panel link, and the cross-bar link are configured to coordinate adjustment of positions of the hinged panel and the flap relative to each other.

Systems and methods for controlling a fixed-wing aircraft during flight are disclosed. The aircraft comprises first and second flight control surfaces of different types. The method comprises determining that a pilot command of the first flight control surface will excite a structural flexible mode of the aircraft and then executing the pilot command of the first flight control surface in conjunction with a command of the second flight control surface to mitigate the effect of the excitation of the structural flexible mode of the aircraft.

One embodiment is an apparatus comprising an aircraft wing; a control surface hingedly connected to a trailing edge of the aircraft wing, wherein a slot is provided between the aircraft wing and the control surface; a seal disposed over the slot, the seal hingedly connected to the aircraft wing; a spring mechanism for preloading the seal against a top surface of the control surface such that the gap is sealed with the control surface is in a first position relative to the aircraft wing; and at least one cam blade for lifting the seal from the top surface of the control surface as the control surface moves from the first position to a second position relative to the aircraft wing and returning the seal to the top surface of the control surface as the control surface moves from the second position to the first position.

A free-streamline airfoil includes a front portion, the front portion including a leading edge geometry configured to force a sudden separation of the flow, and a contoured