Abstract: The pocket structure for a foldable wing of an aircraft, especially a high erformance aircraft, is constructed at least partially of flexible material forming a completely closed volume with an inward fold for receiving a wing portion. The fold divides the closed volume into two portions which are interconnected outside the reach of the fold to form an auxiliary fuel tank for the aircraft. The pocket structure has sealing lips extending along both of its outwardly facing side walls. The sealing lips are constructed as two bellows which are filled with a gas under pressure. Thus, the lips perform two functions. First, the lips seal a zone below the wing from a zone on top of the wing to maintain the pressure difference. Second, the lips strengthen and protect the outwardly facing side walls of the wing pocket structure forming an auxiliary fuel tank. The pocket also performs two functions, namely, the wing receiving function and the tank function.

Abstract: A short takeoff and landing aircraft (10) and vertical/short takeoff and landing aircraft (10), having upper surface blowing engines (12, 14) on gull-shaped wings (24, 26) which may be tilted and translated by a variable incidence translation device (52). The translation means (80, 62, 64) is adapted to provide center of gravity travel trim and critical engine out moment trim. Thrust vectoring of the upper surface blowing engines is accomplished by a combination of the upper surface blowing and wing tilt, and vectoring of lower lift/boost engines (124, 126) is accomplished by swiveling nozzles (138, 140). Critical engine out lateral trim is accomplished by a combination of airplane bank and differential vectoring by the lower lift/boost engines (124, 126).

Abstract: An air gap between a main flap and an adjacent aircraft portion is closed an auxiliary flap. The auxiliary flap (8) has a hinging axis (9) extending substantially in parallel to the aerodynamic flow along aircraft portions adjacent to the auxiliary flap. With the aid of the auxiliary flap an aerodynamically improved transition zone is provided between the aircraft portion and the main flap.

Abstract: A wing structure for an aircraft designed for both STOL and supersonic flight conditions includes a biplanar wing arrangement in which the lower wing section is staggered behind the upper wing section and the lower wing section is designed for both translational and rotational displacements relative to the upper wing section. For short takeoff and landing capabilities, the lower wing section is rotated and translated relative to the upper wing section so that the leading edge of the lower wing section is adjacent to the trailing edge of the upper wing section. For high speed supersonic flight, the lower wing section is adjacent to the trailing edge of the upper wing section. For high speed supersonic flight, the lower wing section is rotated and translated relative to the upper wing section so that the wing sections are substantially parallel.

Abstract: An airplane is disclosed which has a pair of fixed, outwardly extending delta wings extending laterally from a fuselage, a set of initial flaps pivotably attached to the rear of the fixed wings, a set of dependent flaps pivotably attached to the rear of the initial flaps, and a variable positionable concomitant stablizer located at the rear of the dependent flaps forming the rear of the delta wings during the high-speed configuration capable of achieving independence from the fixed wings upon actuation of the flap system; the above components all locked together to form the delta wing during high-speed flight with an actuator which also serves as a stress supporter for the flap system during its actuation.

Abstract: An aircraft sustentation system is disclosed which consists of one pair of fixed swept primary wings attached to the fuselage of the aircraft, and one pair of pivotal swept transverse wings attached to the fuselage of the aircraft in a manner where all leading edges, trailing edges, and lateral angles of both sets of wings are parallel or exceed a parallel relationship to each other, the pivotal transverse wings possessing transverse wing collars capable of accepting accessory and/or landing gear supports or wells; and the pivotal transverse wings utilizing actuation mechanisms capable of canting, laterally tilting, and variable sweeping the transverse wings in a manner where the swept transverse wing leading edges approach or contact the trailing edge of the primary wing or primary wing flap with a parallel relationship during the low-speed high-lift configuration.

Abstract: An improved utility class hydrofoil boat having an integrated hydrofoil suspension and steering system wherein pairs of foils may be inclined at various angles, to the lateral axis of the boat, converting from surface piercing to submerged type foils when operated in concert and, in combination with the production of a yawing force about the vertical axis, may be used to produce coordinated turns by introducing a differential in the angle of inclination between starboard and port foils or by introducing a differential in the sweepback angle between starboard and port foils. In the preferred embodiment, a symmetrical, submerged tail foil having a positive dihedral is rotated to produce a yawing moment in proportion to the bank produced by manipulation of the pairs of foils, resulting in coordinated, banked turns with a single control movement.

Abstract: A deployable wing assembly using an inner wing segment and an outer wing segment. The inner wing segment is hinged longitudinally to the body of a missile, or the like, and with the outer wing segment hinged by a pin perpendicular to the surface of the wing segments at the junction, and including deploying and locking arrangements for both sections.

Abstract: A ball pivot thrust bearing flex joint assembly having an inner race member and an outer race member, the inner surface of the outer race member being a concave spherical self lubricating surface which provides a maximum envelopment of the complementary convex spherical outer surface of the inner pivoting ball race. The inner race ball is provided with a through aperture along the axis of primary motion for acceptance of a through shaft or bolt, and is provided with integral lateral extensions which are necked down to provide clearance for secondary axis motion. The end portions of the through hole aperture are provided with self lubricating bearings which support the radial loads and accommodate main axis rotation. Flat, washer type, self lubricating bearings are provided between the ends of the inner race pivoting ball and the associated clevis.

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: An upper and lower member are joined together near the tip. They are hinged near the front and back on the top member. This allows the wings to be opened for high speed, when cruising, and to be closed for take off and landing at a low speed. The exact size and shape of the moveable sections will be dictated by the size of the wing and the distance between the upper and lower wings where they join the fuselage. When the wing reaches a certain speed the drag forces will become more demanding creating a faster movement through the air passages causing a suction at the front of the wings. The ram affect on the front and the suction affect in the back will accomplish two things. It will dissipate the drag that tries to build up at the trailing edge and eliminate the pile up of air at the leading edges of the wing. The air passageways between the wings, when in the open position, will have to be the same size all of the way through the passageways.

Abstract: A supersonic airplane has a fuselage, a wing, a vertical stabilizer, a canard and a pair of turbine engines mounted in the fuselage. Each engine is of relatively simple design with a fixed inlet, a compressor and a turbine with a single drive shaft interconnecting the turbine and compressor. The engine can employ either fixed or variable exhaust nozzle geometry, depending on whether an afterburner is installed. The engine is point designed to provide maximum design thrust at a given intermediate throttle setting when the airplane is being propelled by the engine at a predetermined supersonic cruise Mach number. Maximum allowable thrust at speeds below the predetermined cruise Mach number is achieved without variable geometry air inlets by maintaining the corrected airflow through the engine at a substantially constant value equivalent to the corrected airflow at the predetermined supersonic cruise Mach number.

Abstract: A wing pivot assembly for variable sweep wing aircraft for movably securing a wing of the aircraft to the fuselage. The wing pivot assembly has a pivot pin supported by a pair of inboard lugs secured to the fuselage of the aircraft. The wing is, in turn, movably secured to the pivot pin by bearings interposed between the pivot pin and a pair of outboard lugs. In addition an outboard shear fitting located between the wing and the pivot pin movably supports the wing and transfers shear loads to the pivot pin. An inboard shear fitting and anti-rotation device secures and transfers shear loads between the pivot pin and the fuselage. As a result of the above arrangement a multi-load path structure provides for a fail-safe pivot assembly.

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: An aircraft having a fuselage provided with wing panels in staggered positions along the fuselage such that control surfaces of the forward wing panel are substantially closer to the center of gravity than are the control surfaces of the rearward wing panel. This arrangement results in reduced drag effects at transonic speeds, and provides a novel way of obtaining precise control of the aircraft position by using the control surfaces for vertical translation with minimum pitching moments.

Abstract: A supersonic airplane having a wing mounted for pivotal movement between a conventional position orthogonal to the fuselage and an oblique position relative to the fuselage has its vertical pivot axis offset from the mean aerodynamic center of lift of the wing when the wing is in the conventional position. The pivot axis can, for example, be offset rearwardly from the mean aerodynamic center of lift and transversely relative to the fuselage in the direction of the trailing tip of the wing when in an oblique position to counteract pitch and roll moments induced by the aeroelastic effect on the wing and by the center of pressure shift occurring at supersonic flight speeds.

Abstract: A wing, for aircraft of cropped, arrow-type planform with thin leading and side edges, having a pivotable tip to alter the crop angle of the wing during flight. Increasing the crop angle causes the wing side edge to become a trailing edge which reduces the strength of the side edge vortex flow. Decreasing the crop angle causes opposite results, in particular the side edge is now a leading edge and can generate a leading edge vortex flow. The wing constitutes a roll control device for aircraft of the stated design particularly effective at higher angles of attack.

Abstract: An aircraft of supersonic transport configuraton featuring thrust vectoring in conjunction with wing apex segments used as canard surfaces during take-off, landing, and low-speed flight. The angle of incidence of the wing apex segments, when the segments are functioning as canard surfaces, is variable with respect to the aircraft angle of attack. The wing apex segments furthermore form a portion of the main wing panel swept leading edge when not functioning as canard surfaces. The combination of thrust vectoring and deployable wing apex segments results in increased aircraft range and improved low-speed longitudinal stability while providing acceptable take-off length capabilities.

Abstract: A staggered channel aircraft having a forward pair of wings and a rearward pair of wings. The forward pair of wings are substantially horizontal and are swept backward from the fuselage to join at their tips the pair of rearward wings. The rearward wings are sloping and are swept backward from their tips to join the fuselage in a substantially triangular-like configuration.

Abstract: For sealing the gap between the fuselage and a swing-wing of a swing-wing aircraft there is provided an elongated, inflated, flexible bag mounted in a recess of the fuselage, all the longitudinal walls of the bag being of flexible material and including a flexible base-wall affixed by a frame along its two longitudinal edges to the aircraft structure, the bag further having a multiplicity of internal, substantially parallel, closely-spaced, flexible, transverse, flanged diaphragms attached by the flanges along their sides to corresponding longitudinal walls of the bag, the flexible diaphragms, at the inflation pressure employed, being rendered substantially inextensible by reinforcing webs in directions such that the transverse cross-sectional dimensions and shape of the inflated bag are constrained by the diaphragms to conform to the dimensions and shape of the diaphragms, and the diaphragms being apertured to permit inflation of the bag from one end.

Abstract: An aircraft that is designed to additionally be able to travel along a railroad track so that it can get into a heart of a city, instead of terminating at an airport located some distance away from the city; the aircraft including wings which can be folded inwardly adjacent the side of the aircraft fuselage so that it requires approximately a same width of clearance as a conventional railroad train, and the railroad tracks being additionally fitted with a system of channel rails welded on top of the oid railroad track so that the airplane can travel thereupon.

Abstract: A device for sealing the fuselage gap in a variable geometry aircraft. The fuselage gap is designed to receive part of the movable wing on the aircraft. The seal is in contact with the upper and lower wing surfaces near the inboard trailing edge section so that the fuselage gap is effectively sealed during flight. The seal is constructed of an air bellows with a triangular-shaped cross section and a plurality of partition walls therein, each partition wall being filled with air passageways in order to allow equilization of air pressure within the bellows. The partition walls are connected to one of the outer sheath walls of the bellows through a hinge-like connection. The hinge consists of numerous loops with a hinge pin protruding through the loops to interlock the concerned outer wall of the bellows with the partition walls. In another embodiment, a one-piece, elastic wire is threaded through the loops of all partition walls consecutively.

Abstract: Two wing semi-spans of unitary construction are mounted on an aircraft fuage. Screwjacks mounted in the fuselage extend and retract each semi-span while maintaining the wing sweep angles constant. Pivoting struts and carriage blocks are employed to support the extensible semi-spans. Rollers connected to the carriage blocks are constrained to follow tracks mounted in the fuselage, providing support at the inboard end of each semi-span.

Abstract: An aircraft including a single fuselage having a main wing and a horizontal stabilizer airfoil pivotally attached at their centers to the fuselage. The pivotal attachments allow the airfoils to be yawed relative to the fuselage for high speed flight, and to be positioned at right angles with respect to the fuselage during take-off, landing, and low speed flight. The main wing and the horizontal stabilizer are upwardly curved from their center pivotal connections towards their ends to form curvilinear dihedrals.