Abstract: A helicopter 10 with a system for controlling mainrotor torque which reduces the power and size requirements of conventional anti-torque means. The torque countering forces are generated by disrupting the main rotor downwash flowing around the fuselage. The downward flow is separated from the fuselage surface 11 by strakes 16 and 17 positioned at specified locations on the fuselage 11. These locations are determined by the particular helicopter wash pattern and fuselage configuration, generally being located 30.degree. before top dead center 21 and 30.degree. from bottom dead center 22 on the fuselage side to which the main rotor blade 12 approaches during rotation. The strakes 16 and 17 extend along the fuselage 11 from the cabin section 18 to the aft end and can be continuous or separated for aerodynamic surfaces such as a horizontal stabilizer 15.

Abstract: A high strength, lightweight, heat resistant control surface for a high speed aircraft such as a missile or the like, comprises a heat resistant lightweight composite such as a graphite reinforced polyimide having a leading edge portion comprising a heat resistant metal such as Inconel. The leading edge portion includes a web fixing the leading edge portion to the composite by bonded attachment thereto at a location remote from the leading edge and adjacent surfaces thereby providing delayed exposure of the bond to leading edge heat buildup during flight.

Abstract: A control force generator for an aircraft using circulation control to a selectively produce lift on an otherwise non-lift surface. The generator employs a novel, double-slot single Coanda surface arrangement for selectively generating the aerodynamic lift.

Abstract: A glider comprising a pair of wings having overlapped forward, inner root portions that are freely pivotally connected and tailfins on rearward, outer portions of the wings. The tailfins are angularly offset from the general longitudinal axes of the wings so as to have an airfoil liftout angle of attack to the relative wind during flight which causes the wings to swing out to an extended configuration.

Abstract: An airplane airframe having wings connected to the fuselage by spars of smaller cross section than the wings. Movable winglets may be provided at the outboard ends of the wings. The fuselage may be an airfoil shaped lifting body structure with longitudinal splines at its edges. The splines may be movable in flight, and may be provided with flaps which are also movable in flight so that the splines can be readjusted to alter the aerodynamic characteristics of the airframe during flight. The undersurface of the fuselage may include cambers symmetrical about the center plane of the fuselage.

Abstract: The subject invention relates to a new and improved airfoil design. More particularly, an airfoil design is disclosed which improves efficiency by taking advantage of the vortex created at the wing tips.

Abstract: This invention relates to aircraft designs with substantial trim drag reduction while maintaining commercially feasible low parasitic and induced drag. The stable or control configured aircraft utilizes controllable winglets to generate pitching, yawing, and rolling moments in flying wing or tailless airframe configurations which are preferably of a swept forward style.

Abstract: A pair of canards (18, 20) are mounted to the fuselage (22) of an aircraft (10). Each canard is mounted to the fuselage by a hinge (44) for vertical swinging movement. Connected to the hinge (44) is a trunnion (72) about which the canard rotates for incidence adjustment. The hinge (44) for each canard is independently powered by a drive motor (58) enabling the canards (18, 20) to be vertically moved either symmetrically or asymmetrically. Incidence is changed by a rotary actuator housed within the trunnion (72) for each canard. The rotary actuator for each canard is independently operable enabling the canards (18, 20) to be symmetrically or asymmetrically rotated.

Abstract: The invention relates to an aircraft provided on either side of its fuselage with at least one lift structure constituted by at least two wings whose distal ends are connected either to each other or to at least one wing element, each structure forming in front elevation of said fuselage a closed polygon, and comprising an upper wing and a lower wing, the zone of attachment of the latter on the fuselage possibly being offset in the direction of the streamline flow with respect to the zone of attachment of the upper wing. According to the invention, each of the wings is made so that the values of the moment of inertia and of the lift, both varying as a function of the longitudinal distance, each take a maximum value at a zone of the wing other than the root. The invention is more particularly applicable to aircraft with multiple wing elements.

Abstract: An empennage assembly for supersonic aircraft includes longitudinally and rearwardly extending booms (12) mounted upon the wings (16) or fuselage of the aircraft. The booms (12) include aft rotatable sections (22) upon which are mounted larger (18) and smaller (20) tail surfaces. The boom sections (22) are angularly rotated through angular displacements .theta. such that the dispositions of the tail surfaces (18, 20) are interchanged between their dispositions during low subsonic and high supersonic flight conditions. In this manner, the directional and longitudinal aerodynamic static stability components of the aircraft are rendered substantially constant at an optimum low or near-neutral level of stability in order to enhance the flight maneuverability capabilities of the aircraft throughout the subsonic, transonic, and high supersonic speed ranges.

Abstract: An ejection seat is provided with fins on opposite sides which are normally stored along the seat side rails and are deployed immediately after ejection to yaw-stabilize the seat as it is slowed by a drogue. The fins are mounted for rotation and are deployed such that they extend rearwardly and out to the sides.

Abstract: A wing tip vortices suppressor utilizing a scoop having an inlet at the lower, leading surface of the wing and an outlet at the upper, trailing surface to reduce turbulence causing pressure differential across the wing. A turbulence fence is used at the tip to account for the frictional losses of the air flowing through the scoop and other phenomena that prevent exact pressure equilization.

Abstract: A jet propelled aircraft of the kind in which propulsion jets are directed over the top surface of the wing so as to cause additional lift as a result of the supercirculation induced on the wing and the deflection of the jets downwards, due to the Coanda effect, immediately downstream of the wing is provided with two longitudinal surfaces projecting from said top surface so as to form a single surface ejector system. The wing of the aircraft has a fixed front part which occupies a minor portion of the wing chord, and a movable rear portion which is articulated to the fixed portion about a substantially transverse axis and can be inclined downwards relative to the fixed part. The portion of the wing between the two longitudinal surfaces may be provided on its trailing edge with a movable attitude control surface of the aircraft.

Abstract: A wing tip is contoured and shaped to bring about a controlled mergence of fluid flows across the upper and lower wing surfaces and alleviation of the resulting vortex when the wing is producing lift or thrust. Control through geometry of the wing tip can be augmented by discharging fluid into the merging flows which weakens the strength of the vortex and results in more rapid dissipation in the wake of an aircraft. Additionally, the origin of the vortex is prevented from migrating inboard of the wing tip which improves overall wing efficiency.

Abstract: A wing assembly in an aircraft includes a pair of wings and a winglet situated at each of the wing tips, the winglets or portions thereof being movably mounted. In order to avoid the need for providing structural reinforcement for the wings to accommodate the additional bending moments acting on the wings due to the presence of the winglets, a system is provided for automatically moving the winglets between a first position wherein each winglet has a first aerodynamically optimal angle of attack and a second position wherein each winglet has a second minimal angle of attack wherein the winglets add substantially no bending moment to the wings, the winglets being so automatically moved in response to the stress acting on the wing.

Abstract: A swivel-mounted trim element of a predetermined configuration for use with aircraft for the purpose of providing additional control in flight. The trim element is mounted immediately to the rear of a channel-shaped stabilizer mounted externally or molded into the fuselage of an aircraft and is especially suited for small aircraft, particularly those having V-surface tail assemblies. The trim element configuration is generally right-angled with the base portion being additionally formed to have a downwardly-canted portion at the leading edge and an inwardly-canted portion at the trailing edge. In operation, the trim element provides two-axis rudder trim about both the pitch and yaw axis.

Abstract: A cruciform wing structure for a solar powered aircraft is disclosed. Solar cells 28 are mounted on horizontal wing surfaces 20, 22. Wing surfaces 24, 26 with spanwise axis perpendicular to surfaces 20, 22 maintain these surfaces normal to the sun's rays by allowing aircraft to be flown in a controlled pattern at a large bank angle.The solar airplane may be of conventional design with respect to fuselage, propeller and tail, or may be constructed around a core 70 and driven by propeller mechanisms 75, 76, 77, and 78 attached near the tips of the airfoils.

Abstract: A swivel-mounted trim element of a predetermined configuration for use with aircraft for the purpose of providing additional control in flight. The trim element is mounted immediately to the rear of a channel-shaped stabilizer mounted externally or molded into the fuselage of an aircraft and is especially suited for small aircraft, particularly those having V-surface tail assemblies. The trim element configuration is generally right-angled with the base portion being additionally formed to have a downwardly-canted portion at the leading edge and an inwardly-canted portion at the trailing edge. In operation, the trim element provides two-axis rudder trim about both the pitch and yaw axis.

Abstract: A boat having an airfoil, providing aerodynamic lift, attached to the aft portion of the boat stabilized with canted vertical stabilization fins, an airfoil, providing and having aerodynamic lift, attached to the forward portion of the boat. Specifically, a boat is disclosed having an elongated air foil, pivotally attached to the forward portion of the boat and a stacked pair of elongated airfoils pivotally attached to the aft portion of the boat. The angle of attack of each of the airfoils can be independently adjusted. In addition, the aft pair of stacked airfoils as an assembly can be raised, lowered, and adjusted with respect to its angle of attack. Vertical stabilization fins are provided for the ends of the aft airfoils and the ends of the forward airfoils. The aft stabilization fins are canted to provide lateral stability and to concentrate forces acting on the boat to the middle of the boat.

Abstract: Devices to reduce the drag experienced by aircraft and other travelling bodies, comprising sail-like members mounted on the body surface. These members project into the local stream that forms close to the surface during motion, and tend to divert that local stream back into the free stream direction and in so doing to experience useful thrust. The members are cambered and the camber varies from root to tip to allow for change in the local stream direction as distance from the surface increases. Special sails for use on surfaces subject to some complex flows, adjustable sails and arrays of several sails for use especially at aircraft wing tips, are also proposed.

Abstract: An elongated channel-shaped stabilizer for use with aircraft and other aerospace vehicles for the purpose of providing additional stability and control in flight. The stabilizer can be fastened externally or molded into the fuselage of an aircraft and is specially suited for small aircraft, particularly those having V-wing tail assemblies. Single and multiple stabilizers can be provided and located at various points around the fuselage or hull of the vehicle, including top, bottom and sides. The channel configuration is generally U-shaped with straight or inwardly canted or bent sides.

Abstract: Retractable wing-tip mounted vanes are actuated from the normal cockpit controls of an airplane to provide both roll control and direct lift control. When not required, these devices retract into wing fairings. Simple to manufacture and operate, these controls permit reduced manufacturing costs through much simpler wing construction. The vanes consist of suitably constructed plates that slide over one another and which form an end plate to the wing when fully deployed. Asymmetric deployment produces an out-of-balance moment in roll; symmetric deployment induces direct lift by increasing wing lift on both wing panels.

Abstract: A high efficiency vertical tail unit is combined with a variable wing geory for large angles of attack, primarily for all-wing aircraft such as delta-type craft. The vertical tail unit is hinged for adjustment about an axis substantially parallel to the longitudinal axis of the fuselage. The outer wing portions are connected, at an angle, with a vertical tail unit which is directed vertically downward in its normal position. The assembly comprising an outer wing portion and a vertical tail unit is rotatable about the parallel axis whereby three different wing types may be realized in the same craft.

Abstract: A wing extension or tip fin is disclosed wherein the tip fin is joined to an aircraft wing to form a nonplanar wing configuration which minimizes induced drag during both low speed and high speed operation of an aircraft. The tip fin which is of generally trapezoidal geometry, extends streamwise along the end of the aircraft wing and is canted to project upwardly and outwardly therefrom. Additionally, the tip fin is twisted to toe-out relative to the freestream direction with the angle of twist varying along the lower portion of the tip fin length. Viewed from the side, the tip fin has a sweep angle at least equal to the sweep angle of the aircraft wings with the leading edge of the tip fin intersecting the wing tip chord at a position aft of the wing leading edge. A strake which extends along the upper surface of the wing from the wing leading edge to the tip fin leading edge, forms a smooth transition between the wing and tip fin.

Abstract: Precompression fins extending perpendicular from the wings of a high speed missile are judiciously located relative to an axisymmetric inlet of an airbreathing power plant such that the outwash angle induced by the body and wing of the missile enhances the performance of the inlet.

Abstract: An improved fluid fence which reduces drag on solid objects moving through a fluid environment and an airfoil or aircraft wing structure having an improved open fence on its surface improving the lift-to-drag characteristics of the airfoil.

Abstract: A water ski boat having separate air foils attached to the forward and aft portions of the boat arranged to exert more lift on the aft portion than on the forward portion of the boat. Specifically, a water ski boat is disclosed having an elongated air foil, pivotally attached to the forward portion of the boat and a stacked pair of elongated airfoils pivotally attached to the aft portion of the boat. The angle of attack of each of the three airfoils can be independently adjusted. In addition, the aft pair of stacked airfoils as an assembly can be raised, lowered, and adjusted with respect to its angle of attack. In a further embodiment, vertical stabilization fins are provided for the ends of the aft airfoils and the ends of the forward airfoils. All of the airfoils are removably attached to the water ski boat so that the boat can be readily configured with or without airfoils.

Abstract: A tip fin or wing extension is disclosed wherein the tip fin is mountable to a conventional aircraft wing to form a nonplanar wing configuration which minimizes induced drag during both low speed and high speed operation of the aircraft. The tip fin is of generally trapezoidal geometry extending streamwise along the end of the aircraft wing and projecting vertically upward therefrom. The height of the tip fin and its cross sectional geometry are established to provide a substantial reduction in induced drag relative to that exhibited by the aircraft wing alone. Further, the tip fin is joined to the wing by a smoothly contoured upwardly extending arcuate region and the maximum thickness ratio of the tip fin airfoil section is established to minimize interference drag caused by the interaction of the tip fin within the wing flow field.

Abstract: The vortex system behind an aircraft is responsible for more than half of the aircraft drag in cruise flight and sometimes more in other flight conditions. The purpose of the vortex diffuser is to intercept the wing tip vortex just aft of the wing trailing edge, diffuse the trailing vorticity and thereby achieve a reduction in drag. To do this, an airfoil-shaped device is mounted on a trailing boom situated at or near to the wing tip. The airfoil is mounted above the boom at an angle inboard of the vertical. Its height is a percentage of wing semispan as is also the mean airfoil chord.The aft-mounting feature permits greater drag reduction at high subsonic Mach number and the inboard vane cant provides significant structural relief. In addition to drag reduction by diffusing the wing tip vortex, some reduction in trailing vortex hazard is also obtained.

Abstract: Devices to reduce the drag experienced by aircraft and other travelling bodies, comprising sail-like members mounted on the body surface. These members project into the local stream that forms close to the surface during motion, and tend to divert that local stream back into the free stream direction and in so doing to experience useful thrust. The members are cambered and the camber varies from root to tip to allow for change in the local stream direction as distance from the surface increases. Special sails for use on surfaces subject to some complex flows, adjustable sails and arrays of several sails for use especially at aircraft wing tips, are also proposed.

Abstract: Vane members are movably mounted on the hulls of watercraft to serve steering and stabilization functions. Several embodiments are provided, some of which rotate between extended and shielded positions, others of which fold to vary the angle at which they extend from their associated hull, and still others of which both rotate and fold to facilitate storage alongside planar hull portions. Both shaft and surface bearing vane mounting systems are described. In preferred practice, the vanes are used on hydrofoil-carrying semi-displacement ships, and the provision of stowably mounted hydrofoils, planing surfaces, and wave form generators on such ships is also provided. Such vane members are also provided on vehicles operable in a fluid medium, such as torpedos operable completely submerged in water, and aerial vehicles such as missiles and aircraft of both the rotary wing and fixed wing types, to similarly serve steering and stabilization functions.

Abstract: A lightweight, segmented, easily assembled aircraft having a hollow fuselage tube, upon which the cockpit, wing, empennage, landing gear, engine, and shell segments are supported and secured, is presented. The wing construction aerodynamically extends the effective wingspan of the aircraft and stabilizes flight by including an aileron slot, which rams positive pressured air from the lower surface of the wing over the upper surface of the wing to laminarize the turbulent air near the ailerons, and including an end plate, which is toed-in and canted towards the upper surface. A fore shell segment separates from and moves fowardly of a fixed, aft shell segment along a track apparatus, secured to the hollow fuselage tube, to permit access to the cockpit of the aircraft.

Abstract: A predetermined-sized and shaped foil-fence structure which is substantially perpendicularly mounted at the foil-tip of a hydrofoil craft and projects downward, upward or partly downward and upward from the foil-tip. The fence surfaces are generally disposed parallel to the longitudinal axis of the craft.

Abstract: Device for diminishing tip vortices in an aircraft. For the purpose of diminishing the tip vortices generated by aircraft there are provided retractable foils at or near the airfoil, as wing, tips in question and projecting upwardly and/or downwardly therefrom. The operation of the retractable foils is satisfactory if such foils are parallel to the centerline of the aircraft but it is preferable if such foils are angled slightly with respect thereto, such as if the leading edge of the upper foil is angled approximately 10.degree. inwardly toward the fuselage of the aircraft and the bottom foil is oppositely angled also approximately 10.degree.. The retractable foils, in addition to diminishing wing tip vortices, also when used on wing tips improve the rate of climb of an aircraft at a given engine setting and appear to diminish the area over which the major amounts of noise generated by the aircraft will be dispersed.

Abstract: An aerodynamic housing is disclosed for stabilizing the free-fall descent an article, particularly a sonobuoy, launched from an aircraft. The housing is cylindrically-configured and includes a tail section wherein a plurality of symmetrical channels are formed obliquely to the cylindrical surface of the housing about the circumference thereof, each channel having a leading edge in the shape of a truncated ellipse. A tailring mounted at the rear of the tail section partially covers the channels thereby forming contoured air ducts through which air flows during the free-fall to orient the housing vertically and stabilize the descent.