Abstract: An under floor housing system for a passenger seat electronic units within an aircraft, where the aircraft includes a passenger cabin with a floor supporting the passenger seats and an air circulation system. Conventionally such electronic units are shoe box sized metal boxes hung under the passenger seats exposing them to damage, occupying valuable cabin space, and impeding access for servicing. The individual passenger seat electronic units are connected to a master control and communicate via conduits to a passenger interface accessible from an associated passenger sea. The units and interface are capable of providing passenger services such as: audio entertainment; video entertainment; telephone; intercom; television; video games; Internet; email; and electrical power supply for laptop computers. The under floor housing system has several individual housings recessed beneath the floor surface adjacent the passenger seats.

Abstract: Disclosed is an apparatus and method for supporting the center stowage bins, center monuments, aircraft systems, and overhead modules, such as attendant rests, for commercial aircraft. Use of an overhead lattice support structure provides an efficient structural support system for the passenger luggage center stowage bins, and also provides the necessary overhead space to accommodate modules, such as crew rests, as well as essential aircraft systems, including ducts, tubes, electrical wiring, and electrical equipment. The overhead lattice support structure also simplifies aircraft assembly operations by allowing more systems (ducting and electrical) to be pre-installed in a back shop rather than in a final assembly line.

Abstract: The invention concerns a launch vehicle comprising a shroud (1a, 5a) supporting auxiliary propellers (2, 3) applying in operation excess flow of stresses to the shroud (1a, 5a), said device comprising means for coupling the payload (4) with the launch vehicle shroud. The invention is characterized in that the coupling means are designed to ensure a mechanical coupling between the payload (4) and the shroud along the direction of the launch vehicle longitudinal axis (X), and to cause them to be disengaged along radial and tangential directions. The invention is useful for neutralizing the effects on the payload of excess stresses applied on the launch vehicle shroud by the auxiliary propellers (2, 3).

Abstract: An airship for lifting and transporting loads, particularly heavy loads. The lifting ability of the airship is given by lighter than air gas contained in bags located between two parallel horizontal platforms constructed in lightweight geodesic fashion, the platform and bag assembly being raised and lowered by means of respectively injecting and exhausting the gas into and from the bags, the whole, together with the lifted object, being moved and steered through the atmosphere by the combined means of conventional powered propeller units and a curtain circumferential to and rotated about the platforms thus using the Magnus Effect.

Abstract: A passenger airplane container system comprises a pod. The pod has a hollow generally cylindrical configuration. The pod further has a horizontal divider. The horizontal divider separates the pod into a passenger area and a baggage area. An airplane is provided. The airplane has a central pod receiving region with a closure device. The closure device is movable between an open orientation and a closed orientation. The open orientation so allows for the movement of a pod into the receiving region. The closed orientation securely encompasses the pod. In this manner the pod is securely contained for takeoff and flight and landing.

Abstract: When stiffening members, such as stringers and frame members, are welded onto a skin sheet to form an aircraft fuselage shell, a crack originating in the skin sheet tends to propagate through the weld joints into the stiffening members. In order to prevent crack propagation into a stiffening member, the stiffening member is reinforced with a web doubler plate or a tension band made of high strength steel or titanium alloys or fiber-reinforced composites. The doubler plate is riveted or adhesively bonded onto a stiffening member web, or the tension band is crimped into the stiffening member web. The resulting fuselage shell structure has crack stopping properties and thus an increased residual strength, so it can be used with welded joints at all areas of the fuselage shell, including the top and sides as well as the bottom of the fuselage.

Abstract: A propulsion system for a non-rigid and at least semi-buoyant vehicle, the vehicle including a pressure stabilized gasbag having a gondola mounted on the bottom thereof. The gasbag further includes catenary curtains extending from the top of gasbag to the bottom of the gasbag and attached thereto. In detail, the propulsion system includes a first pair of tubular members attached, preferably pivotally attached, by one of their ends to the gondola and which extend through the air bag and exit out the top thereof and having propulsion units, preferably turbo-prop engines, attached to their opposite ends. A second pair of tubular members is attached by one of their ends to the gondola, preferably pivotally attached, and extends into the gasbag and having their opposite ends terminating therewithin. A horizontal tubular member extends through the gasbag and has its ends extending out of the sides thereof and is attached to the opposite ends of the second pair of tubular members in the middle thereof.

Abstract: A lighter than air airship is disclosed that has an internal weight supporting structure. The weight supporting structure allows the airship to enjoy the advantages of both static and dynamic lift. The airship disclosed herein is lifted by both lighter than air gasses as well as wings attached to the internal weight supporting structure. A cargo container for use with the airship is also disclosed.

Abstract: This invention relates to a pressure stabilized inflated air transport vehicle having means for limiting crack propagation in the hull envelope whereby leakage of the gas in the haul due to the crack will not exceed the gas pressure maintaining means.

Abstract: A monolithic structure for use as a pressure bulkhead for an aircraft includes a first web, a redundant second web spaced from the first web, stiffeners disposed between and connecting the webs to each other, and first and second outer attachment rings respectively provided on the outer peripheries of the first and second webs for attaching the bulkhead to fuselage structure. One of the webs comprises a pressure web for supporting pressure loading, and the other web defines at least one aperture therethrough. The stiffeners are integrally fabricated along with at least one of the webs and associated attachment ring as a one-piece monolithic part.

Abstract: A non-ridged semi-buoyant vehicle includes a pressure stabilized gasbag having a longitudinal, vertical and horizontal axis, top, bottom and side surfaces and front and rear ends and an aerodynamic shape capable of producing lift. Within the gasbag are first and second vertical catenary curtains attached to the top and bottom surfaces between the sides of the gasbag. These first and second catenary curtains are positioned on either side of the longitudinal axis extending from the front end along a first portion of the gasbag. A pair of first and second Y shaped catenary curtains are coupled to the first and second vertical catenary curtains and extend along a second portion of the gasbag. The arms of each of the Y shaped curtains are attached to the top surface and the legs are attached to the bottom surface of the gasbag. First and second pairs of vertical catenary curtains are coupled to the first and second pairs of Y shaped catenary curtains, respectively, and extend to the rear end of said gasbag.

Abstract: The present invention describes a dual suspension catenary system which includes aspects of both an internal catenary system and an external catenary system. The dual suspension catenary system of the present invention retains and expands upon the advantages of the internal and external catenary systems, such as larger payload suspension and envelope integrity while decreasing the disadvantages (e.g., envelope breach and aesthetics).

Abstract: A structural panel component, such as an aircraft fuselage shell component, includes a single integral part having longitudinal and crosswise stiffening elements integrally arranged on a skin sheet. This integral component has been formed by a high speed milling chip removal process applied to a solid plate-shaped semi-finished starting material. The skin sheet has areas of differing thicknesses, and the height, thickness, and spacing of the stiffening elements varies as needed, depending on the local loading conditions that will prevail on the finished structural component. The configuration of the component can be optimized to minimize the weight while satisfying all load strength requirements. The manufacturing method is very simple and economical.

Abstract: The invention relates to the manufacturing of structural members which are extremely light but can be highly stressed and are designed as a framework, mainly in the field of aviation but also in other technical fields where the framework supports, as large-volume components, are to have a weight that is as light as possible. Sleeve connectors are provided which are designed so that the tubes to be connected to a framework node are covered in a form-locking manner by means of sleeve parts of a sleeve connector which can be glued adjacent to one another on the nodal point, the whole nodal point with all tubes entering at this point being enclosed by the parts of the sleeve connector.

Abstract: A digital longitudinal Aircraft Propulsion Control (APC) system of a multiengine aircraft is provided by engine thrust modulation in response to comparing an input flightpath angle signal .gamma.c from a pilot thumbwheel or an ILS system with a sensed flightpath angle .gamma. to produce an error signal .gamma.e that is then integrated (with reasonable limits) to generate a drift correction signal to be added to the error signal .gamma.e after first subtracting a lowpass filtered velocity signal Vel.sub.f for phugoid damping. The output error signal is multiplied by a constant to produce an aircraft thrust control signal ATC of suitable amplitude to drive a throttle servo for all engines, each of which includes its own full-authority digital engine control (FADEC) computer. An alternative APC system omits sensed flightpath angle feedback and instead controls the flightpath angle by feedback of the lowpass filtered velocity signal Vel.sub.f which also inherently provides phugoid damping.

Abstract: An improved jet thruster system for use in a helicopter without a tail rotor. A non-rotating outer thruster assembly is attached to the rear of the tail boom which, within it, has a source of low pressure air. The outer thruster assembly has a window on each side. Nested within the outer thruster assembly is an inner thruster assembly with a single window which rotates within the outer thruster assembly in response to commands from the helicopter control system. As the single window in the inner assembly is rotated around to where it overlaps with one or the other of the side windows in the outer assembly, an exit opening is created for the low pressure air which in turn creates a desired side force on the tail boom to counteract the torque created by the main rotor and also to provide yaw control for the helicopter. The interior of the inner thruster assembly contains vanes and an air ramp to efficiently redirect the air flow from axial flow to lateral flow within the inner thruster assembly.

Abstract: A thruster for a helicopter is mounted in a rear portion of a tail boom. Two sets of vanes deflect an airflow stream flowing along the tail boom respectively to opposed sides of the tail boom. Two shutters are pivotally arranged partly around the sets of vanes to leave two openings in respective sides of the tailboom. The shutters are pivoted in sympathy toward each other or away from each other to open/close the respective openings symmetrically and simultaneously such that a geometrical center line of each opening remains static irrespective of the status of the opening.

Abstract: A system for enabling an aircraft to accomplish extremely short takeoffs and landings, which includes an integrated flight control system; a takeoff system; a landing system and a high thrust-to-weight propulsion system. The integrated flight propulsion control system includes a multi-axis thrust vectoring system. The takeoff system is operably engageable with the multi-axis thrust vectoring system. The takeoff system includes means for rotating the aircraft nose upwardly below stall speed without substantial use of thrust vectoring from the multi-axis thrust vectoring system. The landing system is operably engageable with the multi-axis thrust vectoring system. It includes means for de-rotating the aircraft from a high angle of attack to a main gear touchdown angle of attack sufficiently low to avoid scraping the tail of the aircraft.

Abstract: A pivot system is disclosed for pivotally connecting a movable component to a fixed component, the pivot system having a swivel device mounted on one of the movable and fixed components, a headed shaft passing through a portion of the other of the movable and fixed components and engaging the swivel device, the headed shaft having a longitudinal axis forming the pivot axis between the components, an anti-rotation device engaging the shaft so as to prevent relative rotation between the shaft and the component to which it is mounted, and an anti-axial movement device engaging the shaft as to prevent relative movement between the shaft and the component to which it is mounted along the longitudinal axis of the shaft. This structure enables the shaft to be installed having access to only one end of the pivot shaft, improving over the known systems in which it is necessary to have access to both ends of the pivot shaft.

Abstract: The invention relates to a mass transit method including a docking terminal where passengers are loaded onto a craft with integral passenger pod. The craft lifts vertically from the docking terminal until it reaches an appropriate commuting altitude within 1,000 feet of the ground at which time the craft will fly to a second docking terminal and vertically descend to the second terminal for unloading of passengers. The commuting routes are networked to create an urban-suburban-rural mass transit system. The utility area of the craft can be detached and replaced. For instance, a passenger pod can be interchanged with a cargo, an emergency medical service (rescue) or a military unit pod for an innovative and versatile means of transportation.

Abstract: A hybrid aircraft is taught having VTOL, R-VTOL and S-STOL capabilities. The aircraft has a lifting body hull and four wing sections arranged in tandem which are pivotally moveable about their neutral axis. Each wing section has mounted thereon a pivotal propeller-rotor assembly for providing thrust substantially in a range between horizontal and vertical. The wings and propellers are integrated to the hull by an outrigger designed to be very stiff and to distribute forces from the wings and propellers to the hull. The hull is shaped to provide aerodynamic lift in an airstream and to facilitate construction by minimizing the number of panels of differing curvature required. The hull is formed of a pressure tensioned frame covered with semi-rigid panels, a lower cladding frame and bow and stem cladding nose cones. The semi-rigid panels covering the frame are formed of gas-tight and abrasion resistant laminate material and are connected to the frame by means of an interface rib and latch system.

Abstract: An aircraft for vertical or short take off and landing operations having two main lift nozzles, both positioned at or near the aircraft center of gravity utilizes one or more jet screen nozzles, arranged in a variety of shapes and combinations, discharging bypass air from a position forward of the center of gravity, and a variable pitch nozzle discharging engine exhaust gas mixed with bypass air from a position aft of the center of gravity, to achieve pitch control while airborne in vertical take off or landing mode. The jet screen nozzle also prevents or reduces ingestion of mixed hot exhaust gas and bypass air discharged through the main lift nozzles. The jet screen nozzle further prevents or reduces ingestion of foreign object debris disturbed by the vertical lift discharge flowing from the main lift nozzles.

Abstract: A flight vehicle which can be joined and firmly strapped to a load, the load being either a human pilot (P) or a remote-controlled pilot. The flight vehicle comprises a supporting frame for attaching to the load, a driving arrangement (100) incorporating a piston engine, and which is connected directly to the shrouded propeller (200) by means of a rotating drive shaft (108) for the purpose of setting up an air stream, also at least two jet pipes (300) which open into outlet nozzles (304, 305) mounted laterally alongside the load or the human pilot (P), whereby the said outlet nozzles can be adjusted to change the direction of the discharged air stream. It is by means of the outlet nozzles (304, 305) that the lift force is set up; this latter force enables the human pilot to lift off the ground to make hover or translatory flights.

Abstract: An aircraft which is capable of safely landing during an emergency landing is disclosed. The aircraft has a safety device which includes a plurality of auxiliary engines. Each auxiliary engine is movable so as to vary the thrust axis in a range between a substantially horizontal direction and a substantially vertical direction. The safety device also includes a plurality of gas bags contracted and disposed at a lower portion of the aircraft body so as to be instantly expandable at a necessary time, such as during an emergency landing.

Abstract: A ducted fan 20 provides lift to a flying vehicle 10. The ducted fan includes direction control vanes (1, 2, 3, 4) for controlling torques applied to the vehicle, and also includes lift negation vanes (305, 306, 307, 308), which control the available lift. The lift negation vanes are oriented with their longitudinal axes parallel to the forward-aft axis (9) of the vehicle in order to reduce drag at high forward velocities. The thrust negation vanes include fixed (305) and movable (305M) portions, with the movable portions rotatable so as to extend into the duct airflow to cause turbulence. The direction control vanes are airfoils arranged for rotation about their quarter-chord axes (410), which reduces the amount of torque required for rotation of the direction-control vanes. This, in turn, allows stepper motors (924a) to be used to drive the vanes. The effects of forward velocity on the ducted fan also creates effects which tend to pitch the vehicle nose-down.

Abstract: A VSTOL aircraft powerplant comprises a gas turbine engine (1), a chamber (2) for receiving exhaust from the turbine section of the engine (1), and a jet propulsion nozzle (3) and vertical lift nozzles (4, 5) connected to the chamber (2). Blocker doors (6, 7) are provided for blocking flow of exhaust from the chamber (2) and thus diverting the flow to the vertical lift nozzles (4, 5). A high pressure air curtain is provided by ducts (9) to control th area of the ports to the vertical lift nozzles (4, 5). Control means coordinate and control the operation of the blocker doors (6, 7) and the air curtain to vary the total efflux between three configurations, namely all efflux occurrng through the jet propulsion nozzle (3) for wing-borne flight; all efflux occurring through the vertical lift nozzle (4, 5) for hovering; and some efflux, which is steplessly variable, occurring through both the vertical lift nozzles and the jet propulsion nozzle for transition between wing-borne and jet-borne flight.

Abstract: A lighter than air apparatus is provided with a gas impermeable sheeting material having a pathway either extending through the apparatus itself or adjacent to the apparatus. One or more control surfaces are provided proximately to an aperture in the pathway for deflecting air passing through the pathway. A propulsion unit with the pathway propels air through pathway. The pathway, the control surfaces, and the control unit allow the lighter than air apparatus to control its bearing and efficiently maintain its position over the Earth.

Abstract: The invention is a ballonet system for a lighter-than-air-vehicle, the vehicle having a lift producing gas bag and a longitudinal, vertical and lateral axis. In detail, the ballonet system includes a plurality of ballonets located within the gas bag positioned along the longitudinal axis and on each side of the vertical axis of the vehicle. Each of the ballonets include a flexible sheet joined at its periphery thereof to a portion of the wall of the gas bag. A ballonet pressurization system is coupled to each ballonet for pressurizing them with air that includes the portion of the wall of the gas bag forming the ballonet having a plurality of holes therethrough. A manifold having an inlet port is joined to the wall covering the holes therein and is adapted to diffuse the pressurized air entering therein.

Abstract: A method and apparatus for producing a thrust force from an annular axial stream of gaseous products fed to a nozzle with a supercritical pressure drop and acceleration to subsonic speed. In the nozzle, the direction of the subsonic annular stream is changed from axial to radial and the radial stream is divided into a plurality of opposing jets which collide in a braking zone and change direction back to axial for discharge into the ambient atmosphere. A change in thrust intensity (modulus) is effected by changing the flow rate of the radial jets and/or the flow rate of the axial stream discharged into the ambient atmosphere. Adjustment of the angle of the thrust vector is effected by changing the angle of discharge of the axial stream into the ambient atmosphere.

Abstract: The thrust director assembly may include a thrust director cone with its apex oriented into the fan airstream and a larger thrust vectoring ring concentric with the director cone. The thrust director assembly axis is angularly displaceable relative to the fan axis for modifying the geometry of the duct outlet such that the aperture of the outlet annulus is reduced on one side and simultaneously enlarged at a diametrically opposite side. The effect of the modified geometry is to increase fan thrust on the enlarged side while diminishing thrust on the narrowed side, thereby to develop a lateral thrust component acting on the airframe for providing long moment pitch and roll control.

Abstract: A flying vehicle has wheels for highways, and a body and an engine. The body, engine and load define a center of mass (CG). Shrouded fans are located about the CG so as to produce, in conjunction with air jet redirection apparatus, the torques required to assume various attitudes. In one embodiment, an upper shrouded fan, with a diameter no greater than eight feet, produces an air jet, centered above the CG, for lifting the body. A second shrouded fan, smaller than the first, produces an air jet for lift, centered below the center of mass, on the longitudinal axis of the vehicle, forward of the CG. Third and fourth paired shrouded fans produce air jets for lift, centered below the CG, on either side of the longitudinal axis of the vehicle, toward the rear of the body. The paired second and third fans have equal diameters, no greater than half of the diameter of the upper fan, to keep the total width eight feet.

Abstract: In a V/STOL aircraft having a vectorable exhaust device in the form of a cascade of variable pitch nozzle vanes, an operating mechanism for effecting coordinated pivotal movement of the vanes is provided to vector engine thrust. The operating mechanism includes a plurality of elongate pushrods arranged in end to end abutment with a corresponding plurality of vane operating levers interspaced between the pushrods. The vanes are rotated about spanwise axes by translation of the pushrods in a direction normal to the vane axes. For a given actuating input the vanes rotate by progressively different amounts so that the combined nozzle throat area remains substantially unchanged throughout the nozzle vectoring range.

Abstract: A vectorable nozzle for directing the thrust produced by an aircraft mounted lift fan includes three relatively rotatable nozzle sections. A first of the nozzle sections is part toroidal in form, and is mounted for rotation at the downstream end of the fan casing about an axis tangential to the casing periphery. The second and third sections define corresponding scarf nozzle sections which are mounted for rotation about respective axes perpendicular to the exit flow plane of the respective upstream nozzle section.

Abstract: A combination converging-diverging exhaust nozzle and thrust reverser for an aircraft turbojet engine is disclosed having a generally annular array of cold flaps extending from a downstream end of a cowling support structure and a generally annular, inner array of hot flaps, located radially inwardly of the cold flap array and extending downstream from an end of the hot gas exhaust duct. The annular array of hot gas flaps comprises two sets of hot flap arrays, an array of first hot flaps being pivotally attached to the downstream edge of the hot gas exhaust duct with the array of second hot flaps having upstream edges that are in contact with downstream edges of the array of first hot flaps. The positions of the arrays of the first and second hot flaps may be adjusted relative to a central longitudinal axis to form a converging-diverging nozzle with a variable cross-sectional area.

Abstract: A variable camber vane comprises a plurality of articulated spanwise segments which can be operated by a mechanism of pivoted links at one end. A plurality of such vanes may be arranged in a supporting frame to act a variable thrust deflector for the exhaust of a lift engine. In a VTOL or STOVL aircraft installation the vane array is mounted on the underside of the aircraft below a downwardly exhausting lift fan and the range of movement of the variable vane array is used to vector lift thrust between a mainly downward direction and a direction having a substantially rearward component.

Abstract: An aircraft comprises a hollow elongated body having a plurality of short wings projecting outwardly form the body in a vertically stacked array. The wings transverse substantially the entire length of the body. Engines with diameters substantially equal to the maximum width of the wings are mounted behind the wings, with at least one engine mounted on either side of the aircraft. Honeycomb structures mounted behind each engine cause the air thrust rearward by the engines to be directed as a smooth laminar flow of air. Air deflectors mounted behind the honeycomb structures deflect the air thrust rearward by the engines. A steering mechanism can orient the deflectors: (i) in a downward direction to provide an upward lifting force on the aircraft, or (ii) in an upward direction to provide a downward force on the aircraft, or (iii) in a port or starboard direction to steer the aircraft. Landing gear is attached to the bottom of the aircraft. Resilient structures are used to absorb shock in case of a crash.

Abstract: A vertical takeoff and landing heavier-than-air aircraft that includes a gyroscopic airfoil in the airstream of a ducted fan to cause vertical lift to the aircraft. The gyroscopic foil is both rotatably and pivotally attached to the aircraft such that it can be titled to provide directional control of the aircraft and, in at least one embodiment, has an adjustable airfoil forming part of the gyroscopic device such that the lift can be varied.

Abstract: In a VTOL or STOL aircraft in which a lift device is housed internally within the aircraft fuselage or wing an outlet nozzle is stowable within the lift device exit aperture. A pair of doors, which when closed conceal the aperture from the sides of the nozzle, and a third folding member form the forward side of the nozzle and support a frame carrying variable vanes which vector the lift thrust.

Abstract: A vertical lift and short takeoff airplane achieving a powered lift which is generated by deflecting downward on the order of nearly 90.degree. the slipstream from the driven propellors by means of the wing flap system of the airplane.

Abstract: An unmanned aerial vehicle incorporates a single engine with bifurcated exhausts which are coupled to side mounted rotating nozzles through a swivel joint. Jet deflection means are mounted to the end of the rotating nozzles to achieve additional degrees of freedom for the aircraft.

Abstract: An unmanned air vehicle capable of vertical take-off and landing, hovering and high-speed horizontal cruise flight. A forward centerbody houses an engine and carries a single rotor assembly having a plurality of propellers lying in a plane substantially perpendicular to the centerline of the forward centerbody. A coaxial aft centerbody is secured to the aft end of the forward centerbody and typically houses the vehicle avionics. A plurality of stators extend outwardly of the aft centerbody, in a plane substantially parallel to the propellers. A single toroidal duct surrounds the rotor assembly and the stators and is secured to the stators. A plurality of movable control vanes are secured between the duct and aft centerbody aft of the stators. A flight control system, typically housed in the aft centerbody, controls the engine and the vanes to cause the vehicle to selectively move upwardly, downwardly, hover or translate to forward, horizontal, motion with the rotor in a plane within 80.degree. of vertical.

Abstract: An airship has a carrier frame with triangular cross-ribs arranged so that an apex faces upwardly and a base faces downwardly, whereby longitudinal beams at the corners of the triangles interconnect the cross-ribs. The carrier frame is enclosed by an envelope including at least three skin segments joined to each other along seams coinciding with the longitudinal frame beams. Each skin segment extends entirely from the bow to the stern and may include several strips. At least two steering air chambers are provided, one near the bow, the other near the stern for trimming purposes. The seams or at least one of the seams, is so constructed that it is readily openable and closable for providing access to the interior of the airship.

Abstract: A high strength panel-like structure having a high strength to weight ratio. The structure comprises two integrally formed panel sections, each panel section comprising an outer sheet portion and inwardly extending ribs that are formed integrally with the related sheet portions, and having inner bonding surfaces spaced from their respective sheet portions. The two panel sections are formed into a unitary structure by bonding the two sections at the bonding surfaces of the ribs. Thus, the bonding area of the panel structure is at the neutral axis of the structure. Desirably inner bonding surfaces of the ribs have a width dimension greater than a width dimension of the ribs.

Abstract: This invention tests a vehicle, such as an aircraft, using nondestructive interferometry. An interferometer detects movements in the vehicle surface due to stress. One applies such stress by pressurizing the vehicle. In one embodiment, a hood housing the interferometer attaches to the vehicle surface with the aid of a vacuum. One can vary the pressure in the vehicle in various ways, while monitoring the interferometer for signs of defects in the structure behind the surface. The invention also includes an arrangement for substantially automating the analysis. For example, one can automatically position the interferometer according to position information received from appropriate sensors, in combination with stored information about the structure of the vehicle. One preferably uses a real-time interferometer, such as an electronic shearography camera, in the present invention. One can quickly determine the location of defects by observing fringes on a video monitor.

Abstract: The invention disclosed here is a method for forming and curing an intricate structure of criss-crossing composite stringers and frames that are bonded to a skin panel. A structure constructed in accordance with the invention would be well-suited for use as a portion of an aircraft fuselage, a boat hull, or the like. The method is preferably practiced by applying uncured composite stringers to an uncured composite sheet panel. This is followed by placing cured frames crosswise over the stringers. The frames have openings at the locations where they intersect with the stringers which enables the frames to come into direct contact with the skin along most of their length. During the forming and curing process, the stringers are covered with a plurality of cauls, and the entire assembly of skin panel, stringers, frames and cauls is subjected to a vacuum bagging and curing process. The cauls serve to maintain both part shape and to control the flow of resin within the stringers as they are cured.

Abstract: An aircraft fuselage structure is fabricated by the following steps. A plurality of ring-shaped members are first prepared, each member being provided around the outer peripheral surface thereof at positions spaced apart in the circumferential direction thereof with a plurality of recesses. Elongated plate members are provided which have respective convex parts corresponding to the recesses, to form stringers. The ring-shaped members are then arranged at a coaxially spaced-apart paralleled disposition, and thereafter a laminating jig is inserted into the coaxially arranged ring-shaped members with a silicone bag interposed therebetween, the silicone bag having an open opposite end. The ring-shaped members are placed in annular recesses provided in the laminating jig and in correspondingly formed annular recesses provided in the bag.

Abstract: The invention is a propulsion system for a V/STOL type aircraft. In detail, the invention comprises a turbofan engine including a fan section, compressor section, combustion section, turbine section and nozzle section. The turbine section comprises a low-pressure turbine portion coupled to and driving the fan section and a high-pressure turbine portion coupled to and driving the compressor section. A lift fan is coupled to the fan section by means of a drive shaft. A clutch is incorporated for decoupling the lift fan from the fan section. A mechanism is incorporated for extracting additional power from the low-pressure turbine portion of the turbine section to drive the lift fan that augments the basic engine thrust for V/STOL operation.

Abstract: Doors sealing radial flow ports are opened by rotation which slides the doors away from the ports. All doors rotate about a longitudinal centerline of the aircraft. Each flow port has its inlet seal surface with a center of curvature offset from the longitudinal axis. Rotation of the door toward the open position relieves and releases contact between the door and the port inlet seal surface.

Abstract: A propelling nozzle has upper and lower primary and secondary flaps which are disposed opposite one another at a mutual distance and which are sealingly movably guided between lateral wall portions of a four-cornered nozzle housing. The primary flaps are arranged pivotally about a fixed axis of rotation on the nozzle housing. The secondary flaps, in each case upstream of levers non-rotatably connected with the primary flaps, are pivotally linked to pivots situated on the side facing away from the nozzle flow. The secondary flaps change into the primary flaps with a surface section which is bent concentrically with respect to the pivots. The primary and secondary flaps are arranged in a four-cornered nozzle housing which is itself closed in. In each case the secondary flaps are arranged on the nozzle housing in an axially movable and angularly adjustable manner at the downstream end. The levers are formed on interior sections which are bent away from the primary flaps in a toggle-lever-type manner.

Abstract: A superagile tactical fighter aircraft and a method of flying it are disclosed. The superagile aircraft is characterized by articulatable air inlets, articulatable exhaust nozzles, highly deflectable canard surfaces, and control thruster jets located around the nose of the fuselage, on the top and bottom surfaces of the propulsion system near the exhaust nozzles, and on both sides of at least one vertical tail. The method of operating the superagile aircraft comprises the step of articulating the air inlets and exhaust nozzles, deflecting the canard surfaces, and vectoring the thruster jets so that supernormal flight is attained. Supernormal flight may be defined as flight at which the superagile aircraft operates at an angle of attack much greater than the angle of attack which produces maximum lift. In supernormal flight, the superagile aircraft is capable of almost vertical ascents, sharp turns, and very steep descents without losing control.