Abstract: The invention is directed a laminate structure using a reticulated adhesive material positioned between the honeycomb core and a perforate sheet and a precured reticulated adhesive between the perforated sheet and an outer layer of wire screen or other porous fibrous materials with similar pore openings therethrough through which the cells of the honeycomb core can communicate the atmosphere adjacent to the opposite side of the outer layer of porous material and a method of manufacturing same. During the manufacturing process of honeycomb noise attenuation structures which includes an imperforate sheet, an open cell honeycomb core, a perforated sheet and a layer of porous material stacked in that order a thin sheet of a reticulative adhesive material is positioned between the honeycomb core and perforated sheet and between the perforated sheet and the outer porous layer.

Abstract: An improved means for convection cooling the skin surfaces of an atmospheric flight craft such as are subject to air friction-induced overheating when the craft operates at high speed, featuring employment of multiple layered, spaced apart skin members separated and relatively braced by web and post members. Fresh coolant fluid is simultaneously flushed against and contiguously covers a multiplicity of relatively small patches of the inside surface of the outer skin member to be protected, and the spent coolant from each patch is separately removed therefrom and returned to the craft's refrigeration facility. The web and post members also act to direct the pattern of coolant flow so as to provide a much improved heat transfer coefficient than can be attained by other coolant path configurations when an equal pressure drop is applied.

Abstract: In a heat-insulating device comprising radiation-reflecting elements and a conduction-insulating material, the reflecting elements comprise a large number or reflecting flakes that are inserted into and distributed in the insulating material facing the surface through which the radiation has to be stopped. The said flakes are juxtaposed and partially overlap one another so as to conceal the said surface.

Abstract: The composite structural panel has bottom, top and edge layers which enclose a primary core. The core provides additional structural strength to the panel. The edge layer forms a desired panel edge angle of approximately 20.degree. to 45.degree.. The primary core is trimmed at an angle of approximately one-half the desired edge angle to form a first pressure reaction surface. A peripheral core is positioned on the tapered portion of the primary core so that the axis of the peripheral core is perpendicular to the first pressure reaction surface. The peripheral core is trimmed to form a second pressure reaction surface beneath the edge of the panel. The structure is lightweight and resists deformation of the panel edge when the panel is cured under elevated pressure in an autoclave.

Abstract: In the context of a fan assembly for an air system comprising a bulkhead (20) and at least one fan (2) which extends through the bulkhead (20) and whose intake on the aspiration side and whose outlet on the pressure side are located in chambers (21 and 22) separated from each other by the said bulkhead (20), it is possible to obtain reproducible conditions for determining the volumetric performance if adjacent to the two sides of the bulkhead (20) there is in each case at least one pressure sensor (24 and 25) provided with a pressure gage connection (26 and 27).

Abstract: A twin-engine supersonic airplane having an arrow-shaped wing and an elongated fuselage extending approximately equally forward and rearward of the wing. The fuselage is configured for six passengers in a staggered two-abreast seating arrangement and for two pilots seated in tandem. A forebody section of the fuselage, which extends substantially forward of the wing, is of a specific geometric cross-sectional design, i.e., it is an egg-shaped cross section with opposite sidewalls sloping vertically inward in an upward direction. The sidewalls are only of a single curvature in a fore-and-aft direction, and this substantially flat surface has windows installed therein which have an optically flat surface in order that a minimum of visual distortion is produced due to thermal expansion during supersonic flight. Twin vertical stabilizers are spaced apart and each is mounted near a wing tip; and the stabilizers extend both vertically above and below the wing chord plane for functioning as wing tip end plates.

Abstract: A method and apparatus for damping the vibration of a reinforced skin structure (e.g., the fuselage of an aircraft) over a wide frequency range (wideband) in order to reduce the vibration and transmitted noise, and improve the sonic fatigue life, of the structure is disclosed. Wide range damping is accomplished by viscoelastically attaching constraining elements, which can be continuous or segmented, to the skin and to the reinforcing members that support the skin. The viscoelastic attachment between the constraining elements and the reinforcing members directly damp the vibrations of the reinforcing members; and, the viscoelastic attachment between the constraining elements and the skin directly damp the vibrations of the skin.

Abstract: An aircraft cowl, and in particular a translating cowl, used as a component of a thrust reverser, formed of at least one one-piece bondment cured in a single operation. Preferably, a one-piece inner bondment and a one-piece outer bondment fastened together at a joining region. The bondments have constant density cores and tapered closures. Acoustically absorbing materials are part of the lay up for one of the bondments and are integrally cured therein.

Abstract: A design and construction method, for a graduated series of aircraft of various sizes, in which development costs are minimized by maintaining a consistent scale configuration from model to model, and production costs are minimized through the use of a universal tooling concept for the manufacturing of detail parts, subsassemblies and components of the airframes. For each model (M11, M12 . . . M1n) of a series size-graduated elements such as the main wing airfoils (31, 32, 33) are designed with similar characteristics and overlapping dimensions. A common set of tools for constructing these elements is built to accommodate the largest dimension, such as the root cord (34) of the largest airfoil (31) down to the smallest dimension, such as the tip cord (35) of the smallest airfoil (33).

Abstract: A pair of specially reinforced skin-spar joints in combination with a honeycomb core are used to build up a wing spar for a composite airplane wing. A series of contoured mandrels with a covering of fuel resistant material and a wrapped reinforced plastic are aligned one above the other. The wing spar materials are placed between the mandrels, honeycomb core is located alongside as well as wing skins to form a wing buildup. The buildup is placed in a mold, pressure applied to each mandrel forcing all the parts together, and the buildup heated to cure the resins and form a composite wing structure.

Abstract: This invention relates to removable systems for supporting interior passenger elements within an aircraft fuselage (1). The invention is directed toward increasing the efficiency of load transfer, providing quick conversion, and maximizing cargo space. A plurality of longitudinal sections (2, 2') are arranged end-to-end along an axis and connected together by extension/retraction joints (14, 28, 28'). A first end of a diagonal strut (8, 50, 50') is nontranslatably connected to a section (2, 2') just forward of each joint (14, 28, 28'). The other end of strut (8, 50, 50') is nontranslatably connected to the fuselage (1) aft of joint (14, 28, 28'). Axial loads on sections (2, 2') cause sections (2, 2') to slip axially relative to each other, and such loads are transferred from sections (2, 2') to struts (8, 50, 50') and are reacted through fuselage (1). Vertical and side loads are reacted by transverse members (4, 4') that are slip-connected to fuselage ( 1) and by vertical trusses (6, 40).

Abstract: Sidewall vent valves for aircraft having one or more above deck compartments (29) designed to be convertible between passenger and cargo configurations is disclosed. The sidewall vent valves (52, 91 or 121) are located in the deck (27) of the aircraft between the skin (25) of the aircraft fuselage and the sidewall panels (37) of the convertible compartment. The sidewall vent valves (51, 92 or 121) are opened and closed by an electrical actuator that is common to several valves. In the open position holes in the deck are uncovered to allow air to flow from the convertible compartment (29) to the below deck cargo compartment (31) of the aircraft. In the closed position such air flow is prevented. The sidewall vent valves may be reciprocal (121) or rotary (51,91) and, preferably, include membranes (107, 127, 133) designed to "blowout" in the event of an explosive decompression in the below deck cargo compartment (31).

Abstract: A fiberglass fabric wherein a selected number and pattern of yarns have been coated with an aluminum coating is preimpregnated with epoxy or other resin system and laid up as an integral part of a composite structure of the type having a honeycomb core and a plurality of fiberglass plies. Multiple plies of fiberglass fabric which include the yarns coated with an aluminum coating may be utilized in edgeband fastener areas for increased electrical continuity without loss of mechanical strength of composite parts.

Abstract: An energy absorber is provided. The energy absorber includes a thin panel (78) formed of composite materials (84) for reacting compression forces in the plane of the panel (78) between two opposed edges thereof. The panel (78) is constructed to resist overall bending failure when force is applied to the opposite edges. The energy absorber further includes force receiving structure (90, 92) for receiving forces directly to one of the edges and for receiving forces to the opposite edge of the panel (78) to initiate local folding parallel to the other edge for progressing crushing and local folding of the panel (78).

Abstract: A pilot module for a lightweight aircraft having a fuselage primary structure that includes a longitudinally disposed support structure, or boom and also having a wing structure attached to the fuselage primary structure, a tail structure attached aft of the wing structure to the fuselage primary structure, and a propeller assembly attached to the fuselage primary structure. The pilot module includes a pilot support shell constructed of a composite material formed to support the seat, legs, and back of a pilot positioned on it and forming an integral part of the fuselage primary structure. The pilot support shell is positioned at least partially forward of the forward end of the boom. At least one reinforcing member is connected to the pilot support shell and to the boom and is constructed in a single piece with the support shell. The reinforcing member also forms an integral part of the fuselage primary structure. An external fairing is positioned behind and attached to the pilot support shell.

Abstract: A fiberglass fabric wherein a selected number and pattern of yarns have been coated with an aluminum coating is preimpregnated with epoxy or other resin system and laid up as an integral part of a composite structure of the type having a honeycomb core and a plurality of fiberglass plies. Multiple plies of fiberglass fabric which include the yarns coated with an aluminum coating may be utilized in edgeband fastener areas for increased electrical continuity without loss of mechanical strength of composite parts.

Abstract: The fuselage (cabin) (15) of a propeller (45) driven aircraft (10) is isolated from vibration associated with the wake (46) of the propeller by vibration isolators (50, 55 and 110) in the wing and tail surfaces of the aircraft.

Abstract: An invention is disclosed for the attachment of a yoke to a laminated material composed of a medial matrix laminated between first and second skins. Two elongated parallel brackets are attached to the laminated material, the brackets each having a first segment fastened to the first skin, a second segment fastened to a first region of the second skin, and a third segment fastened to a second region of the second skin. The first and second regions are separated by a cavity in the second skin. The yoke is positioned in the cavity and fastened to the two brackets to provide a thrust point approximately coplanar with the second skin. The invention can be used to attach an actuator rod at the thrust point when the laminated material is that used in a cowling associated with a thrust reverser in a gas turbine aircraft engine.

Abstract: A structural material is provided with a surface having a selected pattern of indentations which disperse a radar beam on reflection therefrom so that the radar signal returned to the radar apparatus has an intensity less than 0.1% of the signal reflected from a smooth surface. The material is covered with a plurality of closely spaced indentations and/or raised portions in a random or systematic pattern having a depth or height or a radius of curvature in the range from about 0.2 to about 5.0 times the length of the waves used for normal radar detection of distant objects, e.g. airplanes, missiles, etc. Radar wave lengths are typically in the range from several millimeters to several hundred millimeters. The indentations or raised portions vary in depth or radius of curvature within the stated range and are variably positioned on the surface. A radar signal reflected from a properly constructed surface of this pattern is 99.995% less than a radar signal reflected from a smooth surface.

Abstract: A floor construction for the upper compartment of an aircraft having an about circular fuselage cross-section. A one piece floor plate provides bending supports and extends over nearly the full inner diameter of the fuselage. A connection is provided between the edge of the floor plate and the fuselage outer structure for transmitting forces directed predominantly in the longitudinal direction of the aircraft. Vertically running planar structural members provide side support elements for the floor plate. The construction results in a decrease of the construction weight as well as of the costs, in particular if the floor plates are provided from fiber reinforced plastic. The connection between the floor plates and the fuselage frame can be provided by rods running at an angle forwardly, which transmit preferably forces acting in the longitudinal direction of the aircraft.

Abstract: An aircraft vertical fin-fuselage structural integration system wherein a plurality of vertical tail fin spars, extending transversely across the fin and fuselage and substantially parallel to the longitudinal axis of the fin, are integrally connected directly to the fuselage pressure bulkhead so as to directly transmit or transfer the vertical fin and horizontal stabilizer empennage loads to the fuselage structural network. The system can be adapted to any type of aircraft, and in the case of an aircraft of the BOEING 727 class, the spars accommodate the air intake S-duct operatively associated with the craft's rear engine housed within the rearwardmost portion of the fuselage. The spars also have their lateral configurations fabricated so as to match the fuselage loft lines.

Abstract: A pressure relief device extends between the double side walls of a passenger compartment of an airplane to communicate with an adjacent cargo compartment. A duct is formed between a perforated section of an inside wall and a panel extending from the inside to the outside wall. A spring closing, pivotally mounted valve extends across to close off the duct and has perforations to permit air flow through the closed valve at low pressure differential between the compartments, but the valve will open at sudden high differential pressures.

Abstract: A design system for aircraft that allows wings of various different planforms to be mounted interchangeably on a common fuselage. Each of the wings has wing semi-spans joined by a center section torque box that mounts the wing in a cut-out in the aircraft fuselage. The torque box has a quadrilateral structure including front and rear main center section spars. These center section spars have their ends connected to the front and rear main spars of the semi-spans to transmit wing loads into the fuselage. The length of the main center section spars are designed in accordance with the invention such that they can connect with the main spars of the wing semi-spans to position the quarter chord of the wing properly with respect to the center of gravity of the aircraft irrespective of the wing planform. Thus, aft-swept, forward-swept, or straight wings can be routinely interchanged on a common fuselage without effecting the positive static longitudinal stability of the aircraft.

Abstract: A thick panel is provided constructed of resilient deformable material and of a plan, size and shape to be snugly received in an airframe opening formed by the removal of an airframe stress panel. The resilient panel is positionable within the airframe opening in a manner fully closing the latter against the entrance of foreign material into the interior of the airframe from the exterior thereof. The thick panel includes an outer surface provided with a peripheral rabbet formed therein whereby the outer margin of the thick panel may be received beneath the airframe outer skin portions disposed about and defining the opening in which the thick panel is received. Further, the outer surface of the thick panel includes a flexible coating of substantially fluid impervious material.

Abstract: A vent assembly for rapidly depressurizing a compartment in an aircraft upon accidental depressurization of another compartment, including an apertured grille through which a circulation of return air normally passes, but which is mounted to swing into a hollow wall of the aircraft to pass a greatly increased flow of depressurizing air into the wall when desired. Two actuator plates are hinged together for differential pressure induced relative pivotal movement, and act upon such movement to swing the grille to its open or venting position. The hinged plates form a wall of a plenum chamber behind the grille, and the normal circulation of return air is so directed as to flow first through the grille, then through the plenum chamber, and then into the interior of the hollow wall beyond the plenum chamber to thereby assure positive and direct exposure of the plates to a change in compartment pressure.

Abstract: A wing is secured to the body of a craft, for example an aircraft, at least t four support points interconnected in pairs by a respective clamping bolt. The metal planking of the upper and lower wing structure forms two wing forks each having a respective securing end and two forked legs. One wing fork is secured with its forked legs to the upper wing structure surface. The other wing fork is secured with its forked legs to the lower wing structure surface. Each of the four support points of the craft body forms a forked bracket so that each support point has two half brackets. The half brackets of a pair are vertically aligned so that the respective clamping bolt may pass through these aligned half brackets and through the respective securing ends of the wing forks extending into the space between two half brackets.

Abstract: A graphite containing composite structure having a fastener area for joining the composite to other structures terminates the graphite reinforced laminate adjacent to the fastener area. Kevlar reinforced laminates abut the graphite laminate and extend over the fastener area and are further reinforced with Kevlar laminates that overlap the graphite then extend over the fastener area.

Abstract: This invention relates to an add-on reinforcement to an aft arch assembly for a transparency system for aircraft that improves the resistance to penetration of a windshield secured to the aircraft or its crew module via said aft arch assembly. This invention also relates to a simple method of securing the add-on reinforcement to the aft arch assembly without requiring substantial disassembly of the windshield.

Abstract: Composite honeycomb core structures, such as airplane control surface structures, capable of withstanding bending and shear stresses, are disclosed along with a single stage hot bonding process of manufacturing such structures. The composite structures include: a primary load carrying member formed of a high density honeycomb core, two spar caps, each having a predetermined thickness, bonded to opposing surfaces of the high density honeycomb core; a low density honeycomb core bonded to the high density honeycomb core along one edge thereof; and, a skin superposed on, and bonded to, the spar caps and the low density honeycomb core. (In some cases, depending upon the structural strength needed, the high density honeycomb core may be replaced by a low density honeycomb core and formed in a unitary manner with the low density honeycomb core to which the skin is bonded. Or, both can be high density honeycomb cores formed in a unitary manner and machined to the desired shape.

Abstract: Disclosed is a process for fabrication and assembly of airframes and airframe components utilizing the principles of diffusion bonding and superplastic forming. A preform blank or blank sheet of material capable of being superplastically formed and diffusion bonded is attached to an airframe body or casing by diffusion bonding and superplastically deformed to form a structural airframe component. The superplastically formed structural component may be diffusion bonded to other airframe components and the superplastic forming and diffusion bonding steps may be performed simultaneously or successively to progressively fabricate and assembly an airframe having unique structural geometries and characteristics without conventional machining or welding of component parts.

Abstract: Explosive decompressions in an aircraft or in a spaceship are controlled in individual rooms or compartments thereof by including in the walls, which separate these rooms or compartments, zones or boundaries of such zones which have an inherent rated or predetermined breaking characteristic whereby these zones or boundaries may break in one or the other direction depending on which compartment the decompression started.

Abstract: A model aircraft of the glider or motor-driven type can be provided with one or more different types of wing according to requirements by interposition between the respective pairs of wings and the fuselage of intermediate members adapted on the one hand to the fuselage of the aeroplane and on the other hand to the associated wings and ensuring an aerodynamically smooth transition from the fuselage to the wing. The fuselage can have a pair of lateral surfaces adapted in accordance with the cross-section of one specific wing construction so that intermediate members are only required if it is desired to employ wings differing from those having such a cross-section.

Abstract: A carpet installation for use with a frangible panel to assist in the disintegration and breakup of the panel permitting ventilation through an aircraft floor. The carpet installation utilizes positioning and hold-down tiles to reduce adhesive contact with the frangible panel and isolators to limit the support for the panel and increase the shear forces on the panel during breakup of the panel.

Abstract: The present invention relates to a process for making a thin-walled composite structure having resistance profiled elements, wherein a rotational-moulding mould is made, in the shape of said structure, then resistant profiled elements made of heat-conductive material are positioned in said mould, in order to form a main resistant frame-work for said structure, after which a suitable synthetic material is introduced into the mould and the known operations of rotational moulding are carried out. The structure thus produced may be used for the construction of aerodynes, and in particular in helicopter construction.

Abstract: A form-fitting or conformal load carrying pallet for aircraft to improve the load carrying capacity of aircraft where the load may be fuel, electronic gear, aerial photography equipment or other items. The pallet is arranged for rapid installation and removal from a position against the side of the fuselage so that there is little or no adverse effect on the aircraft weight distribution, so the wetted area of the fuselage is not appreciably increased, so that the effect on aerodynamic characteristics is minimized, and so the pallet does not become a structural part of the aircraft.

Abstract: The upper floor of a multi-deck pressurized aircraft having frangible floor panels sealing the floor during normal flight conditions yet rupturable under a predetermined environmental condition such as when a relatively high pressure differential exists between the upper cabin and lower cargo compartments. This may occur, for example, when the cargo compartment is depressurized by inflight explosion or collision. Differential pressure activates the panel destruction apparatus which strikes the frangible floor panels in such manner as to cause them to disintegrate or crumble into small pieces. Typical panels may be chemically strengthened glass, ceramics, etc.

Abstract: A system for lowering the level of turbulence in an opening over which a eam of air is flowing at a subsonic velocity wherein a fence positioned adjacent to the opening at an upstream location is provided with a plurality of apertures in the distal portion thereof. The apertures in the distal portion of the fence spread the shear layer of air flowing over the top edge of the fence and substantially reduce turbulence within the opening.