Abstract: Flight controls with automatic balance for use in controlling the movement of an aircraft through a fluid system, the control system includes ailerons divided into two parts, which at lower speed adopt the shape of a conventional aileron and rotate in their entirety with the same degree, and at high speeds a first part of the flap rotates or extends to a determinated angle by an actuator while the second part of the aileron, which is hinged or articulated to the first part of the aileron, rotates with reference to the main part, where the amount of rotation is a function of the air speed pressure, and one or more springs oppose the rotation caused by air speed pressure.

Abstract: A helicopter rotor blade includes a main airfoil body (12) and a movable control flap (3) incorporated in the trailing edge profile of the airfoil body. The flap (3) is movably connected to the main airfoil body (12) by a flexibly bendable junction element (4), and is actuated by a piezoelectric actuator unit (5) via a push/pull rod (6) and a lever arm (7), whereby the control flap is deflected relative to the main airfoil body. The junction element (4) is preferably a continuous integral fiber-reinforced composite component having a flexible bending portion (42) with a reduced thickness in comparison to the adjoining portions, whereby the reinforcing fibers extend continuously through the joint in the direction of the connection between the main airfoil body and the flap.

Abstract: Arrays of microslats operating within the boundary layer of an aircraft wing or other surfaces are provided. The arrays consist of rows of microslats, staggered between rows, and shaped so that the trailing edge of the microslat is normal or perpendicular to the direction of expected reverse flow on the surface. For flow regions having directionally stable flow, the microslats are rectangular. Where the direction of the expected reverse flow is variable, the trailing edge of the microslats is triangular, thereby accepting an angular range of reverse flow. Each microslat operates independently through a hinge on its leading edge and an individual spring which holds the microslat flush to the aerodynamic surface until actuated by reverse flow. Where the boundary layer is expected to thicken, i.e., downstream along a surface, the arrays are formed with two layers of microslats, smaller microslats in a top layer and larger in a bottom layer.

Abstract: A segmented flap having a variable curvature for an airplane wind. The flap includes segments arranged to be angularly adjustable in relation to each other and in relation to the wing and at least an articulating mechanism having a first link arm and a second link arm. The first link arm is arranged at an edge of the wing. The second link arm is rotatably attached to the first link arm by a first shaft. The first link arm is provided with an elongated first channel that extends at the side of and in a determined angle intersects an elongated second channel arranged in the second link arm. A guide rail is arranged in a direction transversal to the two channels and located in an opening defined by the channels where they intersect each other.

Abstract: An aircraft aileron system unique in its construction, method of deployment and the functional results obtained, is comprised of two panels located at the rear portion of the wing, in a spanwise direction and aligned with the wing's trailing edge. The panels are independently hinged at their leading edges and rotate to make angular deflections with respect to the wing. The upper, aileron panel is restricted to upward deflection only from its neutral position and in operation is deployed independently as an aileron. The lower, auxiliary flap panel is capable of both upward and downward deflections from its neutral position, and is deployed independently downward as an auxiliary flap. Both panels are deployed together upwardly only as an aileron. Alternatively, the aileron panel may be capable only of upward deployment while the auxiliary flap panel is capable of downward deployment only, to provide a simpler aileron system.

Abstract: A vane-airfoil combination for shifting forces associated with an airfoil. The vane-airfoil combination includes an airfoil moving through a fluid, such as air. A plurality of vanes is positioned in front of the airfoil to divert the path of the fluid to the airfoil. The change in the path of the fluid rotates the forces associated with the airfoil in relation to the original path of the fluid. Specifically, a lift force is rotated to provide a thrust component force, as well as a lift component force. In addition, a drag force is rotated to provide a lift component force, as well as a reduced drag component force. The airfoil may be any type of airfoil, such as a rotating cylinder. The vane-airfoil combination may also include a fore-body and an after-body for reducing the pressure along an upper portion of the airfoil.

Abstract: A continuous skin and seal airfoil comprises a rigid structural wing box located centrally chordwise and extending spanwise and including a spanwise extending spar, an upper skin surface and a lower skin surface. Upper and lower control surfaces are pivotally mounted on the spar for movement about a spanwise extending axis between an elevated position and a lowered position and includes an upper skin surface. In similar fashion, a lower control surface is pivotally mounted on the wing box for movement about a spanwise extending axis between an elevated position and a lowered position and includes a lower skin surface. An upper seal member extends spanwise and is fixed to both the wing box and to the upper control surface. Similarly, a lower seal member extends spanwise and is fixed to both the wing box and to the lower control surface. Actuators move the control surfaces between an elevated position and a lowered position.

Abstract: An airbrake located on the wing of an aircraft between a rear spar and a wing flap comprises two panels aligned with the upper surface of the wing when the airbrake is closed. In the open state or fully deployed position, the two panels are contiguous and behave as a single panel. However, in the intermediate states, the panel closest to the flap is deflected more than the other panel, so that a slot is formed between them. This slot makes it possible to significantly decrease turbulence on either side of the airbrake when the latter is used in low deflection flight.

Abstract: A split rudder control system for an aircraft which reduces the net opening hinge moments opposing return of the split rudders to the fully closed position from small deflection angles. The split rudder control system provides a smoothly faired aerodynamic protuberance on the upper surfaces of the split rudder control members adjacent to the trailing edge of the wing when the control members are in the closed position and at small deflection angles relative to the closed position. The aerodynamic protuberance smoothly deflects the airstream flow over the upper surface of the wing as it approaches the trailing edge, increasing the local velocity of the airstream at a point forward of the trailing edge. The aerodynamic feature is contoured such that a maximum local airstream velocity occurs generally at the interfacing edges of the control members.

Abstract: Apparatus for detecting and signaling a skewing or misalignment of adjacent aircraft leading edge slats is disclosed. A cable is attached to an actuator having a compression spring system and located in an outboard slat. The cable passes through cable guides in several adjacent slats before being attached to an inboard slat. The compression spring system utilizes a dual concentric pair of compression springs for maintaining a tight cable. When a misaligned condition is detected by a proximity switch, the increased cable load will cause the actuator to lock itself in a position out of the range of the proximity sensor.

Abstract: Segmented spoilers are parallel arrays of individually-extended barrier surfaces, such as rotatable eccentrically-mounted disks. The overlapping surface areas extend through a slot on a aircraft surface. When actuated, a segmented array generates a stiff, extendable, profiled spoiler-barrier. The individual surface areas are power-activated from below the airfoil surface according to motor commands from autopilots, operators, sensors and computers. Disk spoiler systems provide very rapid generation and retreat of controllable height barriers. The management of Bernoulli lift phenomenon with disk spoilers has unique use on an aircraft's nose, along the top of its wings, on the forward surfaces of horizontal and vertical stabilizers and within the intake sections of gas turbine aircraft engines. Disks are rotated by electric rotor-positioning motors and aircraft-powered axial force systems.

Abstract: An improved vertical/short takeoff or landing aircraft (10). The aircraft has a canard wing (14), attached to the forward section of the aircraft body, that has an engine (26) on each side. Each engine drives a pusher propeller (42). Located aft of the canard wing (14) is a primary wing (16) that includes a number of control surfaces and that is rotatably attached to the fuselage (12). The primary wing (16) is rotated downwardly about its chordwise axis when the aircraft takes off or lands vertically. When short takeoffs and landings are required the wing is partially rotated and during conventional flight, the wing is rotated to a position that is approximately parallel to the longitudinal axis of the aircraft (12). The aircraft also has a tail control group that consists of a horizontal stabilizer (22) and elevator (34) to where on each side is attached a vertical stabilizer (22) and rudder (36).

Abstract: An airfoil system for use on water vessels is described. A plurality of fore and aft symmetrical sails are arranged to form an asymmetrical two surface airfoil. The individual sails may be rotated to allow tacking. The parameters of sail configurations described form a high lift low drag airfoil. Two and three sail configurations are described.

Abstract: Aileron-supported split flaps and ground speed spoilers (collectively referred to as "aerodynamic lifting or braking devices") for reducing aircraft approach speeds and reducing the length of the runway needed to land the aircraft. The actuating mechanism for the aerodynamic lifting or braking device allows the latter to rotate with the supporting aileron as the latter is moved up and down when the lifting or braking device is in its stowed position. When the lifting or braking device is in its extended position, up and down aileron movements will cause the aerodynamic lifting or braking device to translate to and fro, but the lifting or braking device will remain in the extended position, irrespective of aileron movement. Hydraulic and torque tube systems can be used to deflect the aerodynamic lifting or braking device which completes the aerodynamic profile of the supporting aileron when that device is in its stowed position.

Abstract: A seal assembly for sealing a variable gap between the surface of a first element and a second element movable relative thereto. A seal may comprise a seal housing attached to the second element for movement therewith and having a sealing surface thereon and at least one elongated seal member carried by the housing having first and second conjugate sealing surfaces thereon, the first sealing surface for rubbing and sealing engagement with the first element surface and the second sealing surface for sliding and sealing engagement with the housing sealing surface. A biasing assembly may be carried by the housing for biasing the first and second conjugate sealing surfaces of the sealing member toward sealing engagement with the first element surface and housing sealing surface, respectively.

Abstract: A double segmented airplane flap with the main flap movable by a four-bar linkage and the aft flap programmed with a linkage pivotally mounted to wing support structure. The two flap segments are pivotally joined. Linkage programming the aft flap segment is located and sized so that the two flap segments remain in the same relative position as to each other throughout main flap translation, but the aft flap segment may be rotated in either direction at any position by an actuating device.