Abstract: An anti-icing pressurized air distribution duct system for deployable wing slats wherein mutually telescoping transfer ducts interconnecting a longitudinal wing slat spray duct and a longitudinal wing supply duct, with bearing and seal means fixed on the inner transfer duct to bear slidably against the outer duct interior and remaining protected within the outer duct throughout slat extension and retraction.

Abstract: A leading edge arrangement includes a fixed wing portion 10, a slat member 18 slidably mounted with respect thereto by an arm 14. The arm 14 is provided with an internal trackway 15 and external cam surfaces 16' and 16", the trackway co-operating with roller bearings 12 on the fixed wing portion and the cam surfaces co-operating with respective roller bearings 13' and 13" on the fixed wing portion. The profiles of the trackway and cam surface are selected so that from a stowed cruise condition the slat member initially moves to a take-off setting along a path in which the ratio of downward deflection to extension movement is low, and subsequently moves to a landing setting along a path in which the said ratio is high. A modification is also described in which the rearward heel of the slat member which is exposed when the slat is extended is formed of a flexible panel portion, so that it may blend smoothly with the remainder of the rearward surface of the slat member.

Abstract: A laminar flow control aircraft wing combines suction surfaces and slots in its leading and trailing edge regions, with natural laminar flow over its main box region to achieve laminar boundary layer flow over a majority of the wing surface area. The wing includes a leading edge flap that is used to protect the leading edge region of the wing from insect accumulation and surface erosion caused by the impact of dirt, rain, or other airborne materials when the leading edge flap is deployed in a low-speed position. At high aircraft speeds, the leading edge flap is stored in the surface of the leading edge region of the wing and forms part of the suction system for that area of the wing. The wing also includes a flexible trailing edge suction surface spoiler system that allows the spoilers to bend downwardly when the trailing edge flap is deployed into a low-speed position.

Abstract: A variable-camber airfoil includes a four-bar linkage camber altering mechanism and a flexible panel in the lower skin of the airfoil. A flexible upper skin extends from the upper end of a front spar assembly to the upper end of a nose structure of the airfoil. A rotary actuator is mounted forward of the front spar assembly within the cavity of the airfoil, and is used to actuate the camber altering mechanism. A main drive arm, which acts as a link in the camber altering mechanism, extends forwardly from the rotary actuator. To actuate the camber altering mechanism, the main drive arm is rotated downwardly and rearwardly through an arcuate path in a vertical chordwise plane. The main drive arm pulls downwardly on first and second links, which, due to the kinematics of the four-bar linkage, causes the nose structure to rotate and move downwardly and rearwardly in a manner that will produce the desired aerodynamic curvature in the flexible upper skin.

Abstract: The invention is a spoiler device for an aircraft having a leading edge slat (50) mounted on at least a portion of the leading edge of the wing of the aircraft. A rear portion (52) of the leading edge slat (50) is rotatably mounted thereto and movable from a retracted position to an extended position (52') so as to act as a spoiler. A latch mechanism comprising links 56, 60, 68 and spring member (76) which yieldably hold the rear portion (52) of the slat (50) in the retracted position. An actuator (80) is provided which is mounted to the wing and which is in detachable contact with the latch mechanism of the slat (50). Upon actuation the rear portion (52) is extended and is returned to the retracted portion by the spring member (76). The actuator (80) can be either mechanical, pneumatic, hydraulic or electrical.

Abstract: The invention is a leading edge flap and boundary layer control system for an aircraft wing having a substantially sharp leading edge. The system comprises the wing 10 incorporating a spanwise slot 26 having front and rear guide walls 28, 30. A guide member 44 is rotatably mounted in the wind movable from a retracted position to an extended position. A flap segment 54 is rotatably mounted to the guide member 44 and is movable from a retracted position to an extended position in conjunction with the guide member 44. The flap segment incorporates an aerodynamic surface adapted to form an aerodynamic extension of the leading edge 16 of the wing 10 and, furthermore, cooperating with the guide member 44 to form a smooth transition inlet to the front guide wall 28 of the slot 26. Actuators 66, 72 are provided to actuate the guide member 44 and flap segment 54 from their retracted positions to their extended positions.

Abstract: Traditional roll control systems such as ailerons, elevons or spoilers are least effective at high angles of attack due to boundary layer separation over the wing. This invention uses independently deployed leading edge flaps 16 and 18 on the upper surfaces of vortex stabilized wings 12 and 14, respectively, to shift the center of lift outboard. A rolling moment is created that is used to control roll in flight at high angles of attack. The effectiveness of the rolling moment increases linearly with angle of attack. No adverse yaw effects are induced. In an alternate mode of operation, both leading edge flaps 16 and 18 are deployed together at cruise speeds to create a very effective airbrake without appreciable modification in pitching moment. Little trim change is required.

Abstract: A variable camber leading edge device having a movable nose section and an upper flexible panel extending rearwardly from the nose section. To move the nose section between its upper cruise position and a high lift downwardly deflected position, there is attached to the nose section a generally arcuate cam track, having its forward and rear portions curving upwardly. The cam track is constrained to move in a generally arcuate path by means of two spaced pair of rollers, and it is driven by a pinion gear engaging an upwardly facing middle portion of the track.

Abstract: A slat system in which the slats are supported on tracks and the slats are actuated by a simple bell crank linkage oriented so that its plane of motion is parallel to the wing chord reference plane. The mechanism retracts to a collapsed over-center position and extends to an over-center position so as to lock the slat into the retract or extend positions. Each slat segment is driven by two identical mechanisms tied together by a synchronization link which provides redundancy. Either actuator can drive the surface alone, as the second actuator is driven through the synchronization lever, in case of power loss to the second actuator.

Abstract: A Kreuger flap is hinge-mounted to the leading edge of an aircraft wing by a plurality of hinges hinged at one end internally of the wing, near its leading edge, and at the other end to the rear surface of the Kreuger flap. A torsion tube extending longitudinally through the wing over the length occupied by the Kreuger flap and to the rear of the hinge connection to the wing, is forcibly rotated by a single hydraulic cylinder connected to a crank arm fixed to and projecting radially from the torsion tube. A coil spring fixed at one end to the wing and at its opposite end to a second arm projecting radially from one end of the torsion tube, is moved overcenter during arm movement between first and second position during Kreuger flap extension and retraction and biases the Kreuger flap towards retraction.

Abstract: A leading edge slat of an aircraft wing is connected to the ends of two rods each of them being linked to a crank arm which, in turn, is swung over a particular angular range by means of a planetary gear being driven by a common shaft. Arcuate guide rails on the slat run in rolls which are journalled on the wing case.

Abstract: An actuating mechanism for variable camber leading edges of aerodynamic airfoils characterized by its rigidity and structural stability and which permits varying the camber of a flexible continuous airfoil skin through leading edge deflection angles ranging from on the order of 14.degree. to on the order of 22.degree. with reference to the wing box chord line without deployment of a Krueger flap and up to on the order of 32.degree.

Abstract: A slat assembly is mounted upon the leading edge of an aircraft wing, and responds automatically to changes in air speed or in the angle of attack of the wing, to increase lift at lower air speeds, and to reduce the stalling speed of the wing. A capability is induced in the aircraft for landing and taking off in short distances. For an aircraft of given size and power, also, there is offered an added safety factor in that the aircraft is permitted to land at slower landing speeds than have heretofore been possible. For the purpose of accomplishing these results, the automatic leading edge slat utilizes a base plate projecting from the leading edge of the aircraft wing, and supporting a slat having airfoil characteristics forwardly of the leading edge of the wing.

Abstract: An aerofoil sail has a rigid main panel (10) pivotally mounted to a hull (17) about a vertical axis (15) with trailing a flap (12A) hinged (14) to one side of the main panel. The trailing flap comprises a series of separate flaps (12A' ,12A" ,12A'") individually settable so that the angle of incidence can differ (.alpha.,.beta.) at different levels on the sail. Alternatively, a single trailing flap can be torsionally flexible so that the angle of incidence can differ along its length. In a preferred form flaps (12A,12B) are provided at opposite edges of main panel (10) and can be alternatively folded in to give a reversible aerofoil section.

Abstract: A wing leading edge slat actuation and positioning system, wherein a slat panel is connected to one end of an extensible track member which is supported and guided at its other end, by rollers mounted to fixed structure in the leading edge section of the wing. The actuation and positioning system comprises a unified drive and a programming mechanism which is connected to the slat panel and functions to combine an aerodynamic slot opening or closure operation with a slat extension drive mechanism. The unified drive and programming mechanism comprises a contoured camtrack somewhat in the shape of an S-camtrack and having a roller follower which is connected to a link and drive arm; and this combination allows synchronization of slat actuation with programming control of slat angle-of-deflection and aerodynamic slot opening or closure.

Abstract: The invention is a leading edge flap for an airfoil. The leading edge (24) is rotatably mounted to the airfoil (14). A first flap segment is (48) attached to the leading edge (24) and has an external aerodynamic surface (50a) adapted to form a portion of the bottom aerodynamic surface of the airfoil (14), when the flap (20) is in the retracted position. A second flap segment (60) is pivotally attached to the first flap segment (48) and is adapted to be retracted within a recess (80) within the airfoil (14). A link (70) is pivotally connected to both the second flap segment (60) and the airfoil rib structure (22) such that rotation of the leading edge (24) extends the first and second flap segments (48 and 60) from their retracted positions downwardly and forwardly of the leading edge (24), forming an aerodynamic extension of the airfoil (14).

Abstract: The invention relates to aircraft wings, wherein the fairing element between the leading edge of a wing and the fuselage comprises a streamlining flap movable between a folded position in which it is housed in a recess in the fairing element and forms a part of the leading edge and the part adjacent the lower surface of said fairing element, and an extended position in which it ensures continuity of the leading edge between the fuselage and the high-lift spoiler likewise in extended position. Moreover, there is a communication between the housing of the streamlining flap and the housing of the high-lift spoiler so that, when these two flap elements are in their extended positions, the air penetrating in the housing of the streamlining flap disposed on the lower surface side emerges through the housing of the high-lift spoiler disposed on the upper surface side, with the result that there is an increased upper surface blowing.

Abstract: A chordwise extensible wing leading edge system incorporating a rigid contoured panel member which is exposed during forward extension movement of the leading edge slat for closing in the proximity area between said slat and the relatively stationary leading edge portion of the wing, as a function of the forward movement of the slat. A further embodiment utilizes a second panel member so that both the upper and the lower surface contour of the wing airfoil envelope are aerodynamically continuous to complete the contour of the intervening space between the extended position of the slat and the stationary portion of the wing; whereby, this combination results in approaching the merits of wing cambering devices capable of operation at relatively high airspeeds as opposed to landing or take-off airspeeds.

Abstract: To prevent deposition of ice on the frontal surface of for instance, the horizontal tail of aircraft anti-icing member is installed in front of the edge along its entire length. The member has an airfoil profile with a chord equal to 3-8% of that of the tail to be protected and is located in a zone not exceeding the tail is thickness, a duct being formed between the member and the surface to be protected for the passage of an accelerated air stream.

Abstract: An actuating mechanism for variable camber edges of aerodynamic airfoils--viz.

Abstract: A series of flaps along the leading edge of a highly swept-back wing for a supersonic airplane; wherein, the spanwise series of flaps comprise a double-flap chordwise having fore and aft flap segments. When the leading edge double-flap is positioned at a forward and downward angle-of-deflection relative to the wing, the foreflap segment is further positioned at an angle-of-deflection relative to the aft-flap segment. This difference in the deflection angles, between the fore-flap segment and the aft-flap segment, creates a vortex flow region ahead of the wing leading edge; and this vortex functions to control separation of an upper surface boundary layer airflow, over the remainder of the upper surface of the wing. Also, the vortex flow will move in a spanwise direction outboard toward the tip of a swept-back wing, while remaining forward or ahead of the upper surface of the aft-flap segment.

Abstract: A wing leading edge high-lift generating device in the form of a spanwise slat segment having both an upper and a lower surface, faired into an airfoil configured leading edge of a relatively stationary portion of the wing therebehind and movable with respect thereto by a downwardly extending hinge arm pivotally related to a downwardly extending hinge bracket from the wing within a fairing structure which also includes an actuator between the hinge arm and bracket for biasing the hinge arm connected to the leading edge device away from and downwardly with respect to the hinge bracket of the wing about the pivotal connection therewith.

Abstract: The present aircraft steering method makes use of additional lift gained by ontrolling the separating of vortical flows from the leading edges of the wings for the purpose of controlling the aircraft about its pitch axis, its roll axis, and its yaw axis. The vortical flows are selectively or differentially separated from the leading edge of the wings by raising or lowering leading edge flaps and/or blowing a flowing medium over the wing surfaces substantially in parallel to the leading edge.

Abstract: A wing leading edge variable camber flap for an airplane, the flap having a pivoted bullnose and flap extension and retraction linkage mechanism for sequencing the flap into three positions of operation: a stowed position for high speed cruise operation of the airplane; a first forwardly and downwardly extended flap position whereat an aerodynamic slot is formed between the trailing edge of the flap and the relatively fixed leading edge of the wing, coupled with a steep flap angle-of-deflection of the flap relative to the wing chord plane, for low speed landing operation of the airplane; and a further forwardly extended second position whereat the trailing edge of the flap is moved to an abutment relation with the leading edge of the wing to seal off the aerodynamic slot, to form a substantially aerodynamically continuous upper surface and the flap angle-of-deflection being less than the landing position, for creating less drag during take-off operation of the airplane.

Abstract: This invention relates to an improvement in a transverse, force-connected body with variable profiling, particularly an airplane wing, containing flexible upper, lower, and nose skin parts and supporting elements hingedly engaging thereat in conjunction with a control gear, the improvement comprising clamps securing the upper and lower flexible skin parts at a rigid part of the wing, rigid carriers in the upper and lower areas of the wing, and shaped profile elements on the upper and lower carriers, the shaped profile elements having outwardly-pointing shaped profile surfaces for the selective support of the flexible skin parts.

Abstract: Airfoil device and method providing smooth, continuous, variation in airfoil camber and surface curvature over substantially the entire length of the device by use of a trusslike bendable beam as an airfoil rib having the airfoil skin surfaces flexibly slidable relative thereto. The beam is divided chordwise into upper and lower beam members each formed of a plurality of articulated sections. The beam members are connected by a bendable jackscrew which upon rotation causes one member to move chordwise, and its curvature to be changed, relative to the other thereby effecting deflection of the airfoil with concomitant variation in its camber and the curvatures of its outer skin surfaces.

Abstract: A leading edge slat apparatus especially adapted to be deployed from the undersurface of an airfoil without encountering excessive resistance from the airstream. The apparatus comprises a slat member which is stowed in an airfoil with the forward end positioned forward of the rear end and which is moved downwardly and forwardly to its deployed position. Concurrently therewith, the rear end is moved upwardly relative to the forward end, with the forward end still being positioned forwardly of the rear end. In a first embodiment, a main actuating member has a forward end pivotally connected to the slat member and a rear end slideably connected to the airfoil. A tilting arm is pivotally connected to the airfoil at one end and pivotally connected to the actuating member and a tilting link at a second end.

Abstract: A drooping leading edge device is provided in which the leading edge structure that droops is pivotally mounted, by a single pivot inside the wing, upon the front spar structure of the wing and is of substantially constant shape. A gap which would otherwise open up between the upper skin of the main part of the wing and the upper skin of the leading edge structure, when the leading edge droops, is filled by an upper flexible skin section secured to the main part of the wing and extending forward first into contiguity with the rear edge of the upper skin of the leading edge structure and then inside said leading edge structure. At the underneath of the wing, a rear flexible portion of the lower skin of the leading edge device extends back to meet the forward edge of the lower skin of the main part of the wing.

Abstract: Tailoring the contour and chord length of a variable camber leading edge flap for the tapered wing of an aircraft is aimed at improving the aircraft's low speed performance particularly for takeoff and landing. Each segment of a spanwise series of leading edge flap segments has a constant chord flexible panel and a spanwise tapered leading edge or bullnose member. By using different chord flexible panels in adjacent flap segments, together with a tapered bullnose, the effective chord length and contour of the variable camber leading edge flap can be varied smoothly in the spanwise direction without resorting to different flap linkage mechanisms at each spanwise station. Further, through the change in cross-sectional shape of the bullnose member along the semi-span of the wing, a change in the effective flap angle (angle-of-incidence of the flap-chord relative to the wing-chord plane) is also produced.

Abstract: A leading edge flap system for the tapered wing of an aircraft and more particularly, the spanwise flap segments and their linkage mechanism allow a relatively large leading edge bullnose member to be extended and unfolded out from a wing cavity. Each of the spanwise flap segments is supported from the leading edge of the wing by a pair of linkage mechanisms which are spaced apart spanwise and attached towards each spanwise end portion of the flap segment. The spanwise spaced apart linkage mechanisms are interconnected by a torque tube which is rotated through a fixed number of degrees by an actuator. By altering the geometry of the linkage mechanism, a differential motion is applied between the spanwise ends of the flap segment to torsionally twist the panel in a spanwise direction thereby varying the flap deflection angle spanwise.

Abstract: An airfoil having a support frame, a rigid nose section, and upper and lower variable camber skin sections extending from the nose section rearwardly to the support frame. The frame has a rigid mounting arm which extends forwardly into the variable camber section, and a pivot link is connected from that mounting arm to a lower portion of the nose section so that is is able to swing downwardly and rearwardly to its cambered position. A toggle linkage connects an upper portion of the nose section to the frame just beneath the upper variable camber skin section. Flexure of the toggle linkage during downward movement of the nose section reduces the chord length of the arc of the variable camber upper skin section so that a proper continuous curve is formed by the upper variable camber skin section from the nose section back to the frame.

Abstract: The present canard type of aircraft comprises steering rudder elements which are tiltable substantially about the leading edge of each wing of the aircraft, whereby the respective edge of the rudder element extends alongside said leading edge of the respective wing. Another edge of the rudder element extends alongside a surface portion of the fuselage or body of the aircraft in close conformity with said surface portion, but movable relative thereto. A sealing may be inserted between the rudder element and the fuselage in such a manner that said movement is permitted.

Abstract: A variable camber leading edge flap and linkage mechanism for allowing two different extended operating positions of the flap, i.e. a landing position whereat an aerodynamic slot is formed between the aft edge of the flap and the fixed leading edge of the wing, coupled with a relatively steep flap angle relative to the wing chord plane; and a take-off position whereat the aerodynamic slot is closed and the flap angle is less than at the landing position. Also, a pair of cam mechanisms are interposed between linkages and sequenced in their operating functions to alternately restrain and release certain of the linkage members in order to open or close the aerodynamic slot and change the flap angle in a manner that insures that air loads acting on the variable camber flap do not cause linkage oscillation and flap instability.

Abstract: An improved boundary layer control system is particularly useful in applications where controlled air is to be injected into a boundary layer region adjacent to a surface of an aircraft wing. The controlled air is obtained from an air source having a temperature and a pressure which are substantially greater than ambient temperature and pressure, such as that obtained from a jet engine bleed air source. A number of manifolds are located in spanwise arrangement along the wing and serve to conduct the air from the source to a plurality of nozzle penums, each of which includes a plurality of spanwise-spaced apertures for injecting air into a portion of the boundary layer region. The manifolds are interconnected by compressible bellows and are mounted so that respective inboard ends are fixed and respective outboard ends are free to move longitudinally.

Abstract: A seal assembly for sealing the slot formed between the aft end of an extended leading edge flap and the leading edge of a wing includes a flexible, blade-type seal extending spanwise between the leading edge flap and the wing. The upper end of the seal is attached to the underside of the leading edge flap adjacent its aft end and extends downwardly therefrom. The bottom portion of the seal is normally spaced from the leading edge of the wing. The seal is flexible so that when air is flowing over the leading edge flap and the wing, airflow from the underside of the flap causes the lower end of the seal to move toward the leading edge of the wing and intimately engage the leading edge of the wing in sealing contact. After the bottom edge of the seal engages the leading edge of the wing, the differential pressure between the upper surface of the flap and the wing and the region below the leading edge flap maintains the seal in contact with the leading edge.

Abstract: A variable camber leading edge airfoil system that is attached to the front f the fixed wing section of an aircraft. When the system is in the retracted position it provides an airfoil having a slight curvature suitable for supersonic flight and when in the extended position it provides an airfoil having a large curvature suitable for high lift subsonic flight. The system is capable of operating at any intermediate position depending upon the requirements of any particular flight conditions. The system includes a rigid lower panel, a leading edge beam, a flexible upper panel and an actuating mechanism. Actuation of the actuating mechanism to the extended position simultaneously causes the rigid lower panel to move downward and rotate counterclockwise, the leading edge beam to move downward and rotate counterclockwise, and causes the flexible upper panel to flex to a proper curvature and have the rearward edge move forward and slide along the upper forward edge of the fixed wing section.

Abstract: An aircraft spoiler system consisting of semi-circular rods disposed within the leading edge of an aircraft wing and rotatably carried thereby so that in the inactive position the substantially flat surfaces are flush with the wing surface and in its most active position the flat surfaces are at right angles to the wing surface with approximately half of the rods extending above the wing surface, acting in a manner to eliminate the lift of the wing, i.e., as spoilers. The rods are controlled by a pair of magnetic clutches which connect the spoiler rods to a rotary solenoid when a toggle switch is thrown by the pilot. The spoilers have mechanical spring returns which automatically retract them when the switch is in its "off" position or in the event of a power failure. A retro-fit mounting is provided for fitting the spoilers on existing wing section.