Abstract: A strain compatible attachment arrangement for releasably securing a plurality of metallic thermal protection system (TPS) panels to a space vehicle substructure to provide an outer mold line of the aeroshell of the vehicle. The TPS panels are spaced from the substructure to support aerodynamic loading on the TPS outer panel surface while isolating the outer panel surface from strains in the substructure and to isolate the vehicle substructure from direct thermal energy conductance though the outer TPS panel surface of the space vehicle. The attachment arrangement provides for a stand-off leg member to be secured at an inner end to the substructure and at its outer end to be releasably secured to a corner of a TPS panel, such panels being arranged in an edge abutting relationship.

Abstract: An aircraft mechanical structural system which provides an improvement to the existing aircraft structure by reinforcing the fuselage frame aluminum skin (3) and fuselage frame (5), without replacement of any of the existing structural elements. The improvement is comprised of high performance, solid fabric (1) fuselage section jackets (13), fuselage frame metal external paneling (4), and a thermal and cryogenic resistant adhesive (23). The jackets (13) are installed between the aluminum skin (3) and fuselage frame metal external paneling (4). The external paneling (4) is installed between the jackets (13) and entire outside surface of the fuselage frame (5). The external paneling (4) provides a solid foundation for the jackets (13) by preventing sagging into openings in the fuselage frame (5). The adhesive (23) bonds the jackets (13) to the aluminum skin (3) and to the external paneling (4). The adhesive (23) prevents premature crimping, abrasion and tearing of the jackets (13), and rivet (22) failure.

Abstract: The present invention provides a tailcone and power assembly mountable to the body of an aircraft using a height adjustable dolly. The tailcone assembly comprises a longitudinal support member, a gas turbine engine mounted to the support member; a firewall; two curved rotatable casings hingeably connected to the support member; an inlet duct extending from an aperture in one of the rotatable casings to the engine inlet; an integral exhaust casing, and interface means for making necessary engine accessory connections to the aircraft. The tailcone is installed on the aircraft by mounting the tailcone in the adjustable dolly, rolling the dolly up to the aircraft, adjusting the dolly until the auxiliary power assembly is properly aligned for attachment to the aircraft, connecting the engine accessories to the aircraft, and bolting the assembly to the aircraft.

Abstract: A self-contained airliner passenger safety module. A module is preferably made of a lightweight material, such as fiberglass, capable of absorbing at least some of the energy generated when an airliner inadvertently impacts with the ground. Passenger seat bases are molded into the module and are provided with slots through which passenger safety belts are passed; thus, a passenger is belted directly to each module. Each seat back is further provided with a deployable safety member, such as an airbag. A module is also equipped with electricity, water, air conditioning, and a fire extinguisher at each end. A module is also provided with sealable doorways. The number of modules to be used in a given airliner is governed by the size and type of airliner in which the modules are to be placed. The modules are designed to be positioned in the interior of an airliner fuselage. They are secured to the floor of a fuselage with a series of graduated shear pins and anti-vibration hold down pins.

Abstract: A variable bodied helicopter is disclosed. The helicopter is of a type that has tandem lifting rotors (1, 2) with a body consisting of a front section (3) and a rear section (4). The rear section of the body is narrower than the front section of the body, thereby allowing the rear section to travel into the front section. Channelled railings (5, 6) attached to the front section of the body firmly hold the rear section through railings (7, 8) attached to the rear section. These railings guide the movement of the rear section relative to the front section. A shaft consisting of two sections (9, 10) is used to synchronize the tandem arranged rotors. The narrower section (9) of the shaft slides into the wider section (10) of the shaft when the rear section of the body moves into the front section of the body. Bearings (11, 12, 13) support the synchronizing shaft.

Abstract: A modular rotary wing aircraft includes a modular cockpit, central frame section, tailboom assembly, landing gear, flight control components and other modular parts so that those parts can be interchanged and interconnected to form differing helicopters to accommodate the requirement of differing tasks. A drive train platform is releasably mounted atop the fuselage formed by the interconnection of the cockpit, central frame section, and tailboom assembly. Modular hydraulic servos, a transmission and rotary propulsion unit, a gas turbine engine, and an engine oil cooling system are releasably mounted to the drive train platform. The drive train platform and all components mounted on it are removable as a unit from the fuselage so that inspection, repair, and maintenance can be performed at bench top level in a controlled environment.

Abstract: The invention provides a hybrid laminate and skin panels of hybrid laminate structure that are suitable for a supersonic civilian aircraft. The hybrid laminates include layups of layers of titanium alloy foil and composite plies, that are optimally oriented to counteract forces encountered in use, that are bonded to a central core structure, such as titanium alloy honeycomb. The reinforcing fibers of the composite plies are selected from carbon and boron, and the fibers are continuous and parallel oriented within each ply. However, some plies may be oriented at angles to other plies. Nevertheless, in a preferred embodiment of the invention, a substantial majority of, or all of, the fibers of the hybrid laminates are oriented in a common direction. The outer surfaces of the laminates include a layer of titanium foil to protect the underlying composite-containing structure from the environment, and attack by solvents, and the like.

Abstract: An apparatus and method for forming an aircraft fuselage having at least one doubly curved portion. A plurality of fuselage panels are extruded with integrally formed stiffening portions extending preferably longitudinally the full length of each fuselage panel. The stiffening portions are further formed so as to be generally parallel to one another. The fuselage panels are then formed into skin panels having a desired curvature and trimmed into gores, and the stiffening portions trimmed at end portions that run out toward longitudinal edges of the panels. When adjacent panels are affixed together, the stiffening portions run out toward longitudinal edges of adjacent panels. The longitudinal edges are secured by splice longerons which are riveted or welded to the longitudinal edges of the skin panels. Independent fastening members are then secured to the stiffening portions and the splice longerons at the points where the stiffening portions run out to positions closely adjacent the splice longerons.

Abstract: A connection is described for connecting two tubular fuselage portions of a missile. The inner diameter of the rim of a first tubular fuselage portion to be connected with a second tubular fuselage portion corresponds to the outer diameter of the rim of the second tubular fuselage portion to be connected to the first tubular fuselage portion, deducting a jointing tolerance, The rims of the tubular fuselage portion to be connected are provided with radial bores to accommodate connection screws, Clamp segments are mounted in the second tubular fuselage portion along the inner circumference thereof. The clamp segments define threaded bores, connection screws being screwed into these threaded bores.

Abstract: Aircraft for carrying passengers and/or freight based on a known aircraft design with a fuselage having a nose section, center section, and tail section and with airfoils mounted on the center section near the center of gravity of the aircraft and calculated for the required lift and with vertical and/or horizontal stabilizers located in the vicinity of the tail section for creating stabilizing and steering moments, with the fuselage of said aircraft being stretched by means of an additional section inserted between the nose section and the center of gravity of the aircraft model in order to increase the carrying capacity of the aircraft based on predetermined known aircraft designs, and with the additional section, as viewed in the direction of flight, being equipped forward of the airfoils of the aircraft model that serve as the main airfoils with airfoils that serve as additional airfoils, with previously designed and calculated airfoils of suitable size from a known aircraft design being used as the addit

Abstract: A method of manufacture of an aircraft comprising the manufacture of a range of interconnectable demountable structural modules and assembly of one of a plurality of aircraft variants by the selection and assembly of a pre-determined set of said structural modules.

Abstract: The present invention is generally comprised of a sonotube-compatible unmanned aerial vehicle apparatus, hereinafter referred to as a UAV, and systems for launch and control of the UAV. The UAV is generally comprised of modular sections including a nose section, a payload section, a wing and fuel tank section, and a powerplant section. The modular sections are attached to adjacent sections by uniform lock sealing rings and related components. The present invention comprises an apparatus enabling very small, man portable, ballistically launched, autonomously or semi-autonomously controlled vehicle to be deployed with preprogrammed, communicated, or telemetry mission programming. A wide range of payload packages, including emergency supplies, sensors, and antenna assemblies, may be carried, used or deployed in flight. Man-portable operation is accomplished by the use of a launch canister apparatus.

Abstract: A releasable coupling for a power transmission line to a tail rotor of a foldable-tail-section helicopter, the coupling having a first and a second coupling assembly fitted respectively to the body and the tail of the helicopter, and which cooperate with each other when the tail is in the work position; the two coupling assemblies having respective transmission members in turn having respective radial toothings cooperating telescopically with each other, and respective conical male and female lead-in members which are brought into contact with each other prior to the respective toothings to guide connection of the transmission members; at least one of the transmission members being supported orientably.

Abstract: An aircraft having a central fuselage, a first side fuselage positioned immediately adjacent to and independent of the central fuselage, and a second side fuselage positioned immediately adjacent to and independent of the central fuselage located on the opposite side of the first side fuselage is disclosed. All of the engines powering the aircraft are located either on the wings outboard of the side fuselages or in the rear of the aircraft aft of the wings. Further, the aircraft may include wings positioned laterally from both side fuselages which may be partially retracted during flight.

Abstract: The present invention provides a tailcone and power assembly mountable to the body of an aircraft using a height adjustable dolly. The tailcone assembly comprises a longitudinal support member, a gas turbine engine mounted to the support member; a firewall; two curved rotatable casings hingeably connected to the support member; an inlet duct extending from an aperture in one of the rotatable casings to the engine inlet; an integral exhaust casing, and interface means for making necessary engine accessory connections to the aircraft. The tailcone is installed on the aircraft by mounting the tailcone in the adjustable dolly, rolling the dolly up to the aircraft, adjusting the dolly until the auxiliary power assembly is properly aligned for attachment to the aircraft, connecting the engine accessories to the aircraft, and bolting the assembly to the aircraft.

Abstract: An improvement to a subsonic passenger aircraft is provided. The passenger aircraft has a fuselage including a main passenger seating deck (14) including forward, middle, and aft regions. The fuselage includes an upper forward deck (16) located above the main passenger seating deck forward region and accessible thereto. Both the main deck and upper forward deck having doors (30), (26) therein for passenger and supplies ingress and egress. The fuselage includes an aft upper deck (18) located above the main passenger seating deck aft region and accessible from the main deck. An upper middle region (20) is located above the main deck middle region. In one embodiment, the upper middle region (20) is of a height elevationally less than either of the forward and aft upper decks. The cross-sectional area of the fuselage at the upper middle region is less than the cross-sectional area of the fuselage at either the forward upper deck region or the aft upper deck region.

Abstract: An aircraft includes a forward fuselage segment, an aft fuselage segment, a wing structure supported from the aft fuselage segment, a tail structure supported from either the aft fuselage segment or the wing structure, and an engine supported from either the aft fuselage segment or the wing structure. A payload module is disposed between and connects the forward fuselage segment and the aft fuselage segment, so as to form the structural attachment between the forward fuselage segment and the aft fuselage segment. The payload module is disconnectable from the forward fuselage segment and the aft fuselage segment such that the forward fuselage segment and the aft fuselage segment are not connected to each other when the payload module is disconnected from the forward fuselage segment and the aft fuselage segment.

Abstract: A mechanism for quickly removing and installing the free wings and/or the tail booms of a freewing aircraft to the fuselage. The fuselage includes a free wing cross tube extending transversely through the fuselage at the spanwise axis, and each of the left and right free wings includes a support tube disposed therein, also along the spanwise axis, with a portion of the wing structural tube being received within the fuselage cross tube. A quick-release pin is insertable in holes disposed in both the structural tube and the cross tube when the holes are placed in alignment. A second cross tube extends transversely through the rear end of the fuselage at the tail boom pivot axis. At least a portion of each tail boom member is disposed in surrounding relationship to the cross tube. In a preferred embodiment, a quick-release pin is insertable in holes disposed in both the tail boom member portion and the cross tube when the holes are placed in alignment.

Abstract: An aircraft passenger extraction system having a fuselage and a tail section removably attached to the fuselage. A plurality of interconnected passenger modules are removably disposed within the fuselage. Four I-beam rails are longitudinally mounted about the inside circumference of the fuselage, and the passenger modules have four sets of wheels that slide on the rails. The tail section has four pairs of separation flaps and four extraction flaps to assist in the separation of the tail section in the event of an airborne emergency. Upon separation of the tail section of the fuselage, the interconnected passenger modules are slidingly withdrawn from the fuselage. Once the passenger modules clear the fuselage, the interconnections of each passenger module are severed in sequence, and a series of parachutes are deployed to safely float each passenger compartment to earth.

Abstract: An air vehicle defining a plane of symmetry includes a pair of outboard panels which are rotatably mounted on the lifting body of the vehicle and respectively extend in opposite directions from the plane of symmetry. A control system collectively rotates the outboard panels to selectively contribute forces from the panels to the lift on the air vehicle. The control system also differentially rotates the outboard panels to control roll of the air vehicle. A pair of empennage panels are also rotatably mounted on the lifting body to establish a dihedral angle centered on the plane of symmetry. The control system collectively rotates these empennage panels to control pitch, and differentially rotates the empennage panels to control yaw, of the air vehicle. In a high speed flight regime the lifting body alone is sufficient and the outboard panels are collectively rotated to reduce drag and contribute substantially zero lift.

Abstract: A treatment for an aircraft interior has a plurality of panels for assembly to the interior, including side and center ceiling panels, and sidewall panels. The panels control overhead liquids and water and divert them away from the interior. The panels have features that permit them to flex and slide in relation to each other while still retaining the ability to transmit liquids from the side ceiling panels outwardly to exterior surfaces of the sidewall panels and away from the interior. The center ceiling panel has features that block liquids thereon from moving outwardly toward the side ceiling panels, and features that transmit such liquids rearwardly and away from the aircraft interior.

Abstract: A modular approach to the manufacture of high performance military aircraft allows different aircraft to be manufactured at affordable cost and with high part number commonality. An aircraft so constructed includes a delta wing; a forebody section, including a cockpit, which is mounted to the front of the wing; and a propulsion system support frame mounted beneath the forebody section and the underside of the wing. The propulsion system is supported within this frame. The aircraft can also include an aftbody section mounted to the aft end of the wing, which includes a 2-D variable thrust vectoring nozzle and a pair of canted vertical tails. The forebody section includes a chin inlet below the cockpit. The wing is preferably constructed using thermoplastic welding.

Abstract: A reduced amplitude corrugated web spar for use in airplane wings and the like is disclosed. The amplitude of the corrugation is determined based upon general stability requirements of the spar, and the fasteners are offset from the center line of the web corrugations. The resulting spar is easier to manufacture and still provides the structural integrity required of the wings.

Abstract: Rib and spar webs are joined in a composite wingbox to eliminate fasteners by welding the webs along bond lines defined by overlapping sections of the webs. Heat to produce the weld is generally achieved resistively by connecting a multistrip susceptor positioned along the bond line to a current source, since the geometry makes it difficult to heat these web joints inductively. The wingbox is completed without fasteners by welding skins to the rib-spar wingbox.

Abstract: An airplane fuselage including a plurality of individual subassemblies having components that are aligned using coordination holes. The components include an assembly of panels, a plurality of stringer clips, a plurality of frame members, shear ties, and a floor grid made of a plurality of crossmembers. The coordination holes are drilled in selected components and are located at positions on the subassemblies to accurately align the subassemblies relative to each other so the spatial relationship between key features of the subassemblies make them self-locating and intrinsically determinant of the final contour and configuration of the airplane fuselage, independent of hard tooling.

Abstract: The invention provides a modular system including one or more interchangeable pressurizable body sections, a front end cap and a rear end cap. A tendon array assembly is coupled between the front endcap and the rear endcap. The body sections are preferably coupled together by a flexible seal. The interchangeable pressurizable body sections may be preloaded prior to launch or left vacant for cargo retrieval from an orbiting facility. Once loaded, the various elements of the modular system may be easily assembled with other elements into a plurality of configurations. The modular system can be attached to an orbiting space structure or utilized within the cargo bay of the NSTS Orbiter to provide a wide range of mission objectives.

Abstract: Tandem-engine aircraft propulsion module attachable to an aircraft fuselage and/or to the aircraft wings directly. This propulsion module contains fore-and-aft in-line engines and an intermediate fuel compartment. A subhousing of this module has engine instrumentation and controls placed for overhead introduction into an underlying aircraft fuselage cabin when the module is secured on top thereof. Propulsion modules of this invention are readily removable and replaceable for ease of inspection and maintenance, and if like-sized are mutually interchangeable. These modules are inherently economical and enable cost-effective fuselage and dry-wing construction. They also enhance flight safety, not only in comparison with single-engine aircraft but also especially as compared with off-axial twin-engine aircraft.

Abstract: An unmanned aerial vehicle that includes symmetrical wings, tail section and internal compartments. The wings which include the only control surfaces can be attached to either side of the aircraft. An engine and a payload are non-symmetrically attached modules. Assembly and disassembly is performed with quick release pin and plate latches, quarter turn fasteners and guides that prevent improper assembly. The compartments include quick release hatch covers for the various internal craft compartments.

Abstract: An aircraft having an elliptical fuselage and low skin friction drag. The aircraft includes(a) a lifting fuselage having a cross-section constituting an airfoil in a majority of vertical planes taken parallel to the flight direction, an aspect ratio (AR.sub.f) of 0.33 to 1.10, a forebody having a substantially elliptic cross-section in all planes taken normal to the flight direction, and a substantially elliptic planform leading edge;(b) wings fixed to the fuselage having an aspect ratio (AR.sub.w) of at least 5.0;(c) a mechanism controlling aircraft attitude; and(d) a mechanism propelling the aircraft;wherein the wings and fuselage produce lift in varying proportions depending upon flight conditions as follows:(i) the aircraft has a cruise design point in which the fuselage lift coefficient (C.sub.LF) is 0.08 or less, and(ii) the fuselage lift coefficient is at least 0.50 at an angle of attack (.alpha..sub.LZo) of 10.degree.

Abstract: An aircraft control system for controlling an aircraft, particularly a free wing aircraft in low speed or hover regimes. An air speed sensor measures air speed of the aircraft and outputs an air speed signal to a control processor which processes the air speed signal with a speed control input signal. A control actuator actuates an aircraft control surface in response to the control surface control signal. The air speed sensor may include a shaft mounted impeller located in an airstream of the aircraft. A rotational speed sensor, coupled to the impeller, measures a rotational speed of the impeller and outputs a rotational speed signal as the air speed signal. In an alternative embodiment, the air speed sensor may include a vane located in an airstream of the aircraft and deflected in response to air flow in the airstream.

Abstract: It is a problem in conventional aircraft having a fuselage of substantially circular cross-section, that a conventional lower deck would have an insufficient standing height for passengers if the lower deck were to be equipped as a passenger cabin space including seats, sleeping cabins, or other passenger service facilities. In the present aircraft, the lower deck floor (2, 2') is depressed or dropped at least in a certain area (14) that will form an aisle (16), so that the free height of the lower deck in the area of the depressed floor provides at least the normal standing height (HS) for a person. A module (15, 15') containing passenger service facilities is arranged in the lower deck area at least to one side of the depressed floor area. A modular construction provides a great flexibility and convenience in reconfiguring a lower deck from a cargo hold configuration to a passenger cabin configuration and vice versa.

Abstract: A semi-rigid, light weight insulation blanket is composed of a skeleton having porous cavities sandwiched between layers of fiber glass. The polyimide foam skeleton prevents sagging particularly in crown and upper sidewall areas of an aircraft thereby maintaining a predetermined offset from the skin fuselage reducing corrosion of the primary structure from moisture condensate. This configuration provides similar acoustic performance with reduced weight.

Abstract: A method of making a large airplane structure from a plurality of subassemblies. The method comprises drilling coordination holes in selected components which are made for accurate assembly of the subassemblies, and that will be located on the subassemblies in a position to be used to accurately position the subassemblies relative to each other so the spatial relationships between key features of the subassemblies as defined by the coordination holes make the subassemblies self-locating and intrinsically determinate of the final contour and configuration of the large airplane structure, independent of tooling. The drilling of coordination holes in the selected components is done using an end effector carried by a precision computer controlled robot that is directed to the drilling locations using a digital dataset taken directly from original digital part definition records.

Abstract: The invention relates to a helicopter fuselage of the type including a central structure to which are linked a front structure, a rear structure and a landing gear, and which supports a transmission gearbox, a main rotor and at least one engine (50), and of the type in which the central structure includes a skeleton (16) fitted with covering elements which define the external shape of the fuselage.According to the invention, the skeleton (16) of the central structure exhibits substantially the shape of a regular hexahedron consisting of skeleton panels (28, 30, 32, 34, 36, 38) assembled together.The invention finds an application especially for producing light helicopters.

Abstract: Apparatus and method for recovering and arresting an aircraft on a floating platform is disclosed. The aircraft has a fuselage, a wing, and a source of propulsion for propelling the aircraft in flight. During landing approach, an inflatable cushion attached to the fuselage is deployed below the fuselage via inflation. In the inflated condition, a fastening material disposed on a downward facing surface of the cushion is thereby adapted to adhesively contact the floating platform deck so that the forward motion of the aircraft is slowed and arrested. In the preferred embodiment, the fastening material is one of male or female VELCRO.RTM. which is adapted to mate with corresponding VELCRO.RTM. material covering the platform deck.

Abstract: An aircraft construction which enables visual inspection of critical body skin/stringer circumferential splice failure lines from the interior of an aircraft comprises a bulkhead member with an alternating shear tie foot pattern such that in alternating stringer bays the critical failure path along one skin portion of the aircraft is not obscured by the bulkhead shear ties. The skin joint for an adjacent skin is similarly provided with an alternating shear tie foot pattern offset by one stringer bay from the pattern for the first skin such that the critical failure path on the opposite side of the bulkhead member is also visible in alternate stringer bays.

Abstract: Synthetic resin composite profile, in particular wing spar for aircraft construction, comprising at least two flanges (1) provided with adhesive bonding flanges and at least one web (2) interconnecting the flanges (1) and inserted into the adhesive bonded flanges, the flanges (1) being constructed of resin impregnated rovings and the web (2) of resin impregnated woven or non-woven fabrics and the flanges (1) and the web (2) being adhesively interconnected. The flanges (1) are pultruded, the web (2) being inserted into the adhesive bonding flanges of both flanges (1) and fixed therein by means of a thixotropic adhesive (4). This manner of construction ensures that the full flange adhesive bonding width is retained even if the component height should change.

Abstract: An improved insulation system for vehicles and method of making and using the same are disclosed. The insulation system comprises one or more layers of insulative material sealed within a case which is impermeable to liquids while being at least in part moisture vapor permeable. When installed within a sealed vehicle where moisture vapor build-up is a problem, the insulation of the present invention serves to isolate condensed moisture from causing damage to the vehicle's contents or its shell. When moisture levels decrease within the vehicle, moisture is free to evaporate from the insulation and dissipate from the vehicle, thus reducing the vehicle's weight and the costs inherent in excessive moisture retention within a vehicle.

Abstract: A plurality of latch pins are locked into a latch position by primary locks and secondary locks. Each primary lock mechanically blocks movement of its corresponding secondary lock into the secondary lock's locked position when the primary lock is out of its locked position. The secondary locks are ganged together to cause them to move together into and out from their locked positions. A follow-up switch senses movement of the ganging mechanism. A latch pin inhibitor blocks movement of the latch pin into the latch position and is moved away to permit latching by spreading of the wing tip. The inhibitor is linked to a valve to shift the valve and thereby cause hydraulic pressure to be supplied to extend the latch pin. When the locks are in their looked positions, the secondary locks mechanically block the primary locks from moving out of their locked positions. The secondary locks are biased into their locked positions. During flight, the latch pins and locks are isolated from hydraulic pressure.

Abstract: A guided missile for air to ground deployment having a modular construction which can be readily configured to suit varying deployment roles. The missile comprises a common central fuselage 1, 2, 3 carrying a fuel tank and mounting points for an engine, wings and nose-cone 7. Bolted onto either side of the fuselage are panniers 6a, 6b of variable length and payload capacity. In one embodiment the panniers 6a, 6b carry munitions for lateral ejection through frangile panels. In an alternative embodiment, munitions are mounted in the fuselage and the panniers carry fuel.

Abstract: This invention involves a simple but radical approach to airplane design. Many advantages and benefits result therefrom including improved flight efficiency, better handling and control response, less tail area required, increased safety, increased utility of airplanes, and reduced ground handling and hangar facility requirements. A solution is provided for the inherent problems of combining the utility of a surface conveyance with the freedom and swiftness of flight.

Abstract: A locking device for a band or the like comprising a housing having one end fastened to a first portion of the band. The housing extends in the direction of the prevailing tensile force and is formed with a guide for guiding a link means. This comprises a fastening element fastened at its first end to the second portion of the band and at its second end journally connected to a second link at a distance from its first end. The second link is, at its first end, journaled around an axis provided in the housing transverse to the longitudinal direction of the housing. The locking device also comprises a third link journaled at the first end of the housing and a dowel element which, l via the third link, is able to prevent the second link from being turned around the axis to a position where it is released from the axis so that the locking device is opened.

Abstract: An improved fighter aircraft has three primary lifting surfaces acting as wings on the airframe. The lifting surfaces are attached 120 degrees apart on the airframe so the fighter may turn in any direction without prior movements. The pilot has means to position himself to feel only positive g's in these maneuvers. A rotatable cockpit section, for example, moves independent of the airframe with the canard wings thereon. The pilot flies the cockpit section and the airframe with wings thereon responds accordingly.

Abstract: A Variable Geometry Remotely Piloted Vehicle (VG-RPV) has a main fuselage portion supporting at one end main wing panels and a forward fuselage portion. In the stowed position, the main wings and forward fuselage portion are laterally adjacent the main fuselage. This provides compact volume of small dimensions for stowage inside a canister. When deployed for flight, the wings are inclined at a large angle to the main fuselage, and a fuselage forebody is positioned upstream of the main fuselage, to establish a vehicle center of gravity adjacent to the deployed wings. Folding panels are mounted on chordwise hinges at the tip of the main wing panels. These panels overlap the main wing panels in the stowed configuration, inside the canister or on deck, and extend the span and area of the deployed main panels in the flight configuration. In-flight deployment is provided to launch the VG-RPV with a reduced span and area with the folding panels placed under the main panels.

Abstract: A vehicle chassis is supported on front and rear wheels for road and runway engagement. A propeller assembly is disposed between the front and rear wheels and faces the rear. Wing assemblies on opposite sides of the chassis are foldable along the sides of the chassis to form side panels for the road form of the vehicle. A tail assembly on the chassis is shiftable forwardly and rearwardly and has a pair of vertical stabilizers connected together at the top by a horizontal laterally extending stabilizer. A pressure regulated retractable stabilizing wheel is provided between the front and rear wheels and is arranged to engage a runway and provide stabilizing functions for take off and landing.

Abstract: The invention is a rotatable, non-circular forebody flow controller. The apparatus comprises a small geometric device located at a nose of a forebody of an aircraft or missile. The geometric device has a circular base that fits flush upon the remaining forebody of the aircraft and a non-circular cross-sectional area that extends toward the apex of the aircraft. The device is symmetrical about a reference plane and preferably attaches to an axle which in turn attaches to a rotating motor. The motor rotates the device about an axis of rotation. Preferably, a control unit connected to an aircraft flight control computer signals to the rotating motor the proper rotational positioning of the geometric device.

Abstract: In order to obtain in a cockpit for a helicopter which is provided with a support frame work consisting of hollow profile parts dimensionally stiffly connected to each other and defining the door and window cutouts of the cockpit and an outer covering and is usually fabricated for cost reasons in view of the relatively limited lot sizes of aircraft in differential design to obtain not only a more weight-saving but also overall a more cost effective cockpit design, at least the hollow profile parts extending around the cockpit cutouts are made as an integral, spatially closed support profile structure such that they are formed and hardened together from composite fiber material or superplastically deformable metal in a forming tool having the forming surfaces with the profile shape of the hollow profile parts around to the cockpit cutouts.

Abstract: A terrain surveillance, powered aircraft is disclosed to have an on-board video camera that is not gimballed relative to the aircraft, the aircraft typically comprising multiple components; the method of the invention including: assembling the components into aircraft configuration at or near a launch site; launching the aircraft at that site with no human pilot on board same; remotely controlling the flight path of the aircraft by radio or cable link, to fly to a location for terrain surveillance; operating the on-board video camera to survey the terrain while varying yaw of the aircraft to provide sweep viewing of the terrain; and recovering the aircraft by controlling its flight to steeply descend to a landing zone.

Abstract: In order to reinforce a working hull, such as the fuselage of an aircraft and in particular that of a helicopter, a frame (C) is embodied made of a composite material in the form of a monolithic monobloc structure. This structure is constituted by a profile whose internal flange (16) and the external half-flanges (18) principally comprise unidirectional fibers which extend over its entire length. As a variant, the lower section of the frame is embodied separately in the form of a panel bordered over its entire periphery by lateral half-flanges which also principally comprise unidirectional fibers. After assembling the two sections of the frame, the half-flanges are then opposite each other in the elongation.

Abstract: This invention relates to aircraft and specifically to devices for disconnecting the winds in a rapid manner. The frame of the wings is atached to the frame of the fuselage with exploding bolts. The skin of the wings is secured to the skin of the fuselage with rivets that also explode or a burnable tape is placed under the skin to sever the skin. A control arrangement is provided that simultaneously ignites the exploding bolts and the rivets or the tape to disconnect the wings from the fuselage.