Abstract: A barrier supported by an object, such as a satellite or missile for use in space, for scattering a coherent beam of electromagnetic radiation having a wavelength in a predetermined range of wavelengths which range is within, but does not necessarily fully include, the range of about 0.2 micron to about 11 microns and emanating from a distant source of such radiation. The barrier includes a non-metallic layer formed by a large number of first components and large number of second components with each of the second components spacing adjacent ones of the first components. The first components have a relative high index refraction and the second components have a relatively low index of refraction. The optical thickness of at least a majority of the first and second components is within an order of magnitude of the wavelength of the radiation and both of the components are transparent at the wavelength of the radiation. The layer has a thickness between 0.2 micron and 1000 microns.

Abstract: An unmanned aircraft is provided which dual turbo shaft engines diving contra-rotating propellers. A bow plane provides pitch control during normal aircraft cruising. The contra-rotating propellers generate a slipstream for wing and tail sections that permit the aircraft to execute hover without the use of complicated tiltable rotor or jet assemblies.

Abstract: The present invention is a folding protective cover primarily for openings which are generally circular in shape, particularly the air inlet and exhaust ducts of a stopped turbo-engine as used by aircraft. The invention is comprised of a generally circular ring shaped frame which is made up of four arc shaped sections of approximately 90 degrees each. Three hinges are mounted between the sections in such a manner that the frame may be folded into an arc of approximately 90 degrees. Affixed to the outer edge of the frame is a resilient gasket and affixed across the center of the frame is a waterproof fabric panel.

Abstract: A canopy locking system includes a series of locking hooks and bolts interconnected with a common torque tube 30 which is turned to lock or unlock the canopy. The shaft may be turned in routine operation by a motor 36 or, in emergency operation by firing a pair of jacks 37.

Abstract: The structural and gas-light bond between a radome and a fuselage in a missile cna be simultaneously fabricated in an improved methodology which reduces the numbers of fixtures required to be utilized, dramatically reduces the time for cure, simplifies the procedure, reduces the cost of fabrication and increases the yield. The fabrication process is comprised of the steps of applying an HT-424 film adhesive on the vertical flange of an etched surface of a fuselage. The film is spaced apart from the butt surface of the flange. A fillet of EA-934 paste adhesive is laid and formed into the corner of the flange between its vertical surface and the radially extending butt surface. The radome is then assembled onto the flange with all the paste adhesive which is extruded from the flange during assembly being immediately removed with a dampened cloth saturated with isopropyl alcohol.

Abstract: The removalbe radome cover shown here is suitable for protecting the radome at the nose of a high speed missile before the radar is turned on. An outer layer lies over, but is not bonded to, an inner layer, and is divided into longitudinal sheets by tear lines. When the radar is to be turned on, a pyrotechnic device at the nose of the radome drives a piston-operated cone forward. Knives on the outside of the cone start to tear the tear lines. The cone lifts the sheets from the inner layer. A spreader lies under each sheet and, rotated by the piston, spreads the sheet further from the inner layer. Air catches the sheets and tears then back to the base of the nose cone. A metal strip along the center of each sheet prevents it from disintegrating before being fully torn back, and provides an engaging surface for the spreader. Thus, only the inner layer will be presented to the radar after the radar is turned on.

Abstract: This invention relates to a shroud or flexible wall cover which is adapted to be placed onto the nacelle of an aircraft engine. The shroud is positioned to cover the nacelle discharge port through which hot, high velocity exhaust gases normally are discharged. The formation of a provisional closure across the exhaust gas discharge port precludes the entry of fumes and/or mist from inadvertently spilled fuel entering the discharge port and igniting when coming into contact with hot engine parts. The shroud is provisionally placed into operating position immediately prior to a transfer of fuel from a fueling vehicle into the wind tanks of the aircraft.

Abstract: A multi-disc brake assembly having a plurality of interleaved stator and rotor brake discs that are cooperative with a cylindrically shaped or cone shaped heat shield that has a honeycomb open cell structure which controllably limits the radiant and convection heat energy transfer out and away from the brake discs on frictional engagement and generation of heat therefrom.

Abstract: A reentry body nose tip constructed from materials and produced by a proc such that shape stability is maintained under ablative erosion occurring during atmospheric reentry.

Abstract: An improved seal assembly positionable to cover a gap between aircraft panels. The seal assembly includes an umbrella seal and primary nodes extending therefrom into the gap. The seal assembly also includes secondary nodes in the gaps secured with respect to the panels and positioned between the primary nodes. The primary and secondary nodes having apertures aligned along a common axis. An elongated pin extends through the apertures of the primary and secondary nodes. The assembly further includes a cross seal positionable with its ends secured over ends of adjacent umbrella seals.

Abstract: A canopy assembly for an aircraft includes a forward canopy panel and a rear canopy panel carried by a support frame. The canopy panels are mounted on the support frame by buttstraps. The bottom edges of the forward canopy panel and the rear canopy panel are set in a bed of sealing compound. A bed of a release agent prevents adhesion between the front part of the forward canopy panel and the bed.The canopy panels are attached to one another at a central region by internal and external buttstraps. The adjacent parts of the panels are contained in beds of sealing compound, and a release agent is applied to said adjacent parts. The rear edge of the canopy panel and the front edge of the canopy panel are scalloped adjacent each clamping bolt.In the event of a birdstrike the forward canopy panel deforms and moves locally rearwardly with respect to the aircraft fuselage. The central buttstraps may also move locally rearwardly with respect to the aircraft fuselage and rear panel.

Abstract: A device for separating a space for cargo in a vehicle, for example in an aircraft cabin or compartment, is constructed for keeping pieces of cargo, for example baggage, in place and to even intercept cargo pieces that may have gotten loose. Such a structure is secured to the vehicle, e.g. an aircraft body, by ceiling brackets and floor mountings. The wall itself is a multilayer structure with different layers provided for different purposes. At least one layer or strut structure is arranged for taking up impact energy effective in a direction in which impact forces are effective, primarily in the travel direction of the vehicle.

Abstract: An expandable throat plug for use in the recovery of a rocket engine nozzle in an engine assembly is disclosed herein having a deployment device carried on the exterior of the engine assembly including an actuator for advancing an extendable column and an arm normal thereto so that the expandable throat plug can be deployed into and inside the nozzle. A telescoping extension shaft deploys the plug interiorly of the nozzle whereby a pressurized medium expands the plug into conformal engagement with the inner surface of the nozzle to seal and close the throat opening.

Abstract: Aircraft engine deactivation apparatus for stopping an aircraft engine while the aircraft is on the ground. The apparatus is for safety purposes and is used to prevent a detected object from coming into contact with an engine driven propeller or a jet propulsion intake. A detector, preferably an infra-red radiation sensor, detects an object or person within a selected distance and within a seleced area about the engine. Upon detection, a mechanical engine deactivator, such as brake calipers engageable with the engine flywheel, or an electronic deactivator, such as an electronic switch operable to ground magnetos, shuts down the engine. A by-pass switch renders the system inoperable, when desired.

Abstract: In the representative embodiment of the invention disclosed herein a load limiting, energy absorbing net is arranged to overlay a normally-covered vent opening in the rear bulkhead of the space orbiter vehicle. Spatially-disposed flexible retainer straps are extended from the net and respectively secured to bulkhead brackets spaced around the vent opening. The intermediate portions of the straps are doubled over and stitched together in a pattern enabling the doubled-over portions to progressively separate at a predicable load designed to be well below the tensile capability of the straps as the stitches are successively torn apart by the forces imposed on the retainer members whenever the cover plate is explosively separated from the bulkhead and propelled into the net.

Abstract: A high lift vertical takeoff and landing aircraft has first and second fuselages connected by a central airfoil. Jet engines at the leading edge of the airfoil expel propulsive streams simultaneously over top and bottom surfaces of the foil. Extendable flaps are utilized at a trailing edge of the airfoil with a horizontal control blade being attached to the leading edge of the foil. The control blade is within the jet's propulsive stream to permit proportioning of the stream above and below the airfoil.An extendable augmenter wing is attached between the fuselages aft and above the main airfoil to permit airflow in this region to be directed downwardly, accelerating the flow and providing additional lift.The main airfoil is positioned so that the fuselage walls extend above and below the foil. Lateral flow of the main engine exhaust is restrained by these walls. Above the wing the walls and airfoil create a venturi to speed airflow and decrease pressure.

Abstract: An improved ground-surface-effect winged craft has a main body in the shape of an airfoil, side plates extending nearly vertically at the opposite lateral sides of the main body for intercepting air flowing outwards from the underside of the main body, side plate floats provided at the side plates, a float provided at a central lower portion of the main body, an operator's seat provided on the float, vertical and horizontal tails provided at a rear portion of the main body, and a propelling device for lifting and propelling the airframe of the craft by making use of both a power augment ramwing effect with the horizontal tail and a ground-surface-effect generated between the main body and a flat surface such as a water surface or a ground surface.

Abstract: Cushioned packaging and protecting with laminate of a thin resilient resin foam layer adhered to a strong supporting sheet. Laminate may also have metal foil or metallized layer, and/or water-repellent surface layer, and/or antistat surface layer and/or volatile corrosion inhibitor and/or a cohesive-nonadhesive surface coating or a low-tack pressure-sensitive adhesive coating. Automatic packaging of a series of articles between long webs of wide cushioning laminates having faces of heat-sealable foam. One web is fed foam-face-up across a table, the articles to be packaged placed on it in spaced locations, heat applied to foam edges to just about melt the foam there, and a second web applied foam-face-down over the spaced articles and heat-sealed to the lower web at its edges. Tranverse heat sealing and severings are effected between successive articles. The heat sealings can be set by cold pressings. Web backings can be made relatively non-porous to minimize bleed-through of melted foam.

Abstract: A helmet for aircrew in a highly manueverable aircraft has six air bags which are inflated or deflated by a control system so as to counteract acceleration forces on the wearer's head and helmet. Two pairs of air bags engage the wearer's body, and two bags engage the seat headrest so that restoring forces in yaw, pitch and lateral directions can be applied. A position sensor determines the actual position of the helmet which is compared with the predicted position, as derived from an inertial sensor or inputs from the aircraft flight control system, the difference between these two positions being used to control operation of the air bags. A memory module programmed with information about the behavior of the wearer's head and helmet characterizes the control system to the particular wearer and is removable for use in other systems.

Abstract: In order to increase the lift supporting underpressure force on top of the inlet fairing of a shrouded fan of a lifting engine and in order to reduce the negative lift generating force of the inlet momentum acting on the rotor area of the fan, a particular geometry of the inlet fairing contour in connection with a particular twist of the fan rotor blades (3) is applied. This results in large differences of static pressures between front side and rear side of the fan at outer radii and there will be more small pressure difference at inner radii. This causes an apparent small change of the blade angle .beta. along a mean radial range of the rotor blades. Guide vanes ( 25) which might follow downstream of the fan rotor blades in some design cases, will have an arrangement of radial twist distribution mirror symmetrical to that of the rotor blades.

Abstract: A thrust-producing device comprises a body having a surface and a periphery and disposed in a first fluid; a generator for imparting energy to a second fluid; and a distributor connected to the generator, disposed adjacent the surface, for distributing the second fluid in a first stream over and adjacent the surface for blanketing and enclosing at least a portion of the surface with the first stream and causing the first stream to be initially sufficiently unattached to the surface to define a closed volume between the surface and the first stream.

Abstract: There is provided a passenger carrying aircraft having a cabin and outer walls. The aircraft includes a safety net located between the cabin and the outer walls. The safety net covers substantially the entire fuselage. If a part of the outer walls fails while the cabin is pressurized and detaches from the fuselage, the safety net will restrain the passengers from being sucked out of the cabin.

Abstract: Safety enclosures for use in high speed vehicles such as aircraft and high speed trains. The safety enclosures include an enclosure shell which preferably has two shell walls separated by a crash resistant intermediate material which also provides thermal insulation against fires and acoustic attenuation. The enclosures also advantageously include cooling systems which utilize a refrigerant which is expanded through tubes connected along the inner wall of the enclosure shell. A compressed air supply is provided which supplies breathing air to passengers and is used to expand a crash bag. Air is supplied through both the crash bag at passenger contacting panels and through supply lines which exhaust near the passengers' heads. A motor driven door assembly is controlled to close as the crash bag is being deployed. Exhaust ports having check valves allow positive pressure to be maintained in the cabin of the enclosures to exclude smoke and fire.

Abstract: Amphibious aircraft having an aerodynamic wing attached to a main fuselage with a centrally positioned channel flow tunnel under the middle thereof. At least one large diameter in-fuselage ducted fan assembly is housed in a duct extending through the fuselage. At least one main helicopter-like rotary assembly provided on a supporting superstructure above the main fuselage. A tail is connected to the main fuselage and has areas appropriate anti-torque mechanisms. A common drive assembly is operatively linked to the fan assembly, the helicopter-like rotary assembly, and the anti-torque device.

Abstract: A basic airfoil has its operating performance improved by incorporating one or more apertures in the airfoil adjacent its trailing edge. These apertures extend from the upper surface of the airfoil down through to the lower surface of the airfoil. The entry port and the exit port of these apertures has a greater circumference than that of the throat circumference which is intermediate thereto. This structure forms a venturi having a vertical axis. Spaced below the throat of the aperture are a plurality of air nozzles that communicate with an air plenum chamber within the airfoil. A source of pressurized air is connected to the plenum chamber. The leading edge of the airfoil causes air to flow across both the upper surface and lower surface of the airfoil. The venturi creates a strong suction on the upper surface of the airfoil to enhance the airfoil's pressure differential.

Abstract: The invention provides a system for selective reduction of infrared signature of a vehicle subjected to aerodynamic heating. Liquid coolant under pressure vaporizes in porous sections of the skin of the vehicle to transpiration-cool the skin. Adjacent downstream solid skin sections are film-cooled by the vapor introduced in the boundary layer. Coolant flow control is achieved by pressurizing the liquid coolant, by modulating flow control valves, and, optionally, by configuring the porous section to operate as a cavitating venturi, or combinations of these methods.

Abstract: A spacecraft having a plurality of concentric balloons (1a,1b), 1c) as protection means, wherein inside the innermost balloon (1c) is located a spacecraft (2) or living facility for human being, together with adequate gaseous material favorable for such equipment or human activity. The outer balloons having progressively lower gas pressures. The multiple balloon system has improved degree of protection against cosmic vacuum environment, improved degree of prevention of escaping of material, with less pressure difference across each balloon membrane and more mechanical strength as compared with a single balloon system. Strings (3a,3b) or similar support members are placed in each inter-balloon space so as to prevent touching or cling of the balloons.

Abstract: An aircrew support system for supporting a pilot's head, and optionally his torso, during high g maneuvers, enabling him to maintain his head in an upright position and thereby increasing his awareness of the situation at all times outside the cockpit comprises at least one head support line (3) adapted for connection between the pilot's head/helmet (4) and the seat (1), accelerometers for measuring the g force acting on the pilot/aircraft and a tension structure for applying a continuously variable tension to said support line of a magnitude determined by the magnitude of the current g force acting on the pilot/aircraft. The support system may include a restraint system, for restraining the pilot in a predetermined position during ejection and for disconnecting the support line on ejection.

Abstract: A method and device for protecting a first stage liquid rocket booster from impact damage and environmental damage so as to permit recovery from a sea water landing and reuse without major rehaul of the rocket engine of the booster. A cylindrical double walled structural member encircles the nozzles of the rocket engine and precludes impact damage after the booster has landed nose first in the water. A flexible water impervious sleeve means is carried within the double walled structural member and deployed prior to impact. The sleeve extends from the booster and collapses inwardly upon itself to prevent entry of sea water into the rocket engine and associated equipment.

Abstract: A device for intercepting and retaining of cargo that may have become loose in a transport or baggage compartment or cabin of an aircraft, is located between a freight compartment and a passenger compartment of an aircraft. The device forms an additional protective screen or wall connected to a mounting structure by connection flanges, e.g. the air frame or cabin structures such as the floor and ceiling. The protective screen has at least two wall sections arranged one behind the other with a spacing between the wall sections. The wall sections are joined to each other by energy absorbing elements inserted in the spacing to form a composite, laminated structure. Each wall section has an external covering. The passenger cabin facing wall section may have a decorated surface. The baggage compartment facing wall has a tough material covering to take up impacts, when a piece of cargo should hit the wall surface.

Abstract: A radome type nose cone shell subjected to aerodynamic heating during protile travel, is ablatively cooled by evaporation of metal coolant from a solidified coating thereof adhering to the external surface of a porous section of the cone shell through which the coolant seeps from internal storage at a rate regulated by formation of the solidified coating. The evaporating coolant from the coating mixes with the air in the flow stream to form a protective a boundary layer extending downstream from the porous section of the nose cone shell. The coolant is melted by said aerodynamic heating during internal storage within the nose cone shell for seepage outflow from the porous section and has the requisite heats of vaporation and fusion to effect alternate freezing and thawing thereof in response to withdrawal of heat by the cooling process for establishment and maintenance of the flow regulating coating.

Abstract: A radar attenuator shield for a space vehicle is described having an open shell of radar attenuating material presenting a smooth external surface on one side and open on the opposite side in the general shape of a bathtub. The space vehicle is ensconced within the open side for minimizing radar echo. In a preferred embodiment the external surface of the radar attenuator shield is in the form of a semi-cylinder with one-fourth of a sphere at each end thereof.

Abstract: An aircraft converting aerodynamic compression ram thermal stream energy into thrust power generation comprising:(a) an aerodynamic compression ram thermal stream generating multiple vane diffuser as the air-inlet to a pressure plenum;(b) a ram thermal-pressure stream induction double throttle duct consisting of a main ramflow inducing nozzle and a fuel injection ramflow inducing nozzle wihch coalesce to form the air-oulet of a pressure plenum-engine pod;(c) a compressed air shooting annular slotted ignition chamber downstream of the fuel injecting ramflow inducing nozzle with flame bed-walled combustion chamber forming a ramjet engine;(d) a ram thermal-pressure stream induction annular slotted thrust nozzle extending rearward from the combustion chamber of the ramjets and exit nozzle of a turbojet engine thereby creating a tailpipe for the turbo-ram induction jet engine; and(e) an aerodynamic compression ram thermal stream sink double-walled shockcone airframe, the double walled shockcone housing the ram the

Abstract: A method and apparatus for maintaining useful conciousness and reducing the risk of injury for a subject exposed to high levels of acceleration while in a vehicle. A buoyancy force suit is provided for supporting the subject with a buoyancy force. The buoyancy force suit includes at least two layers of flexible material, each layer being relatively impermeable to a substantially incompressible fluid locatable in a space between the layers. The suit fits over substantially the entire subject, including the subject's neck. A fluid reservoir is provided for maintaining a constant fluid level within the buoyancy force suit during acceleration. The fluid reservoir is supported at substantially the subject's eye level for maintaining an optimal fluid pressure gradient for ensuring an efficient blood supply to the subject's brain. Means are provided for securely suspending the buoyancy suit within the vehicle.

Abstract: An aircraft structure for the minimization of microwave energy reflection from the aircraft back to a receiver. The provision of structural configurations and materials operate to reduce microwave energy reflection toward its source or another receiver located at a level below the aircraft and laterally or forward thereof.

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: An aircraft windshield transparency includes a base frame defining an opening into which an inboard-positioned transparency is mounted with at least one outboard-positioned transparency and an interlayer between the two transparencies. The interlayer exhibits a stronger adhesion to the outboard transparency than to the inboard transparency. The peripheries of the outboard transparency and interlayer carry a means which functions to expose a groove penetrating to the surface of the inboard transparency such that the outboard transparency and interlayer may be removed and the inboard transparency thereafter functions as the primary windshield transparency of the aircraft.

Abstract: A control system for an anti-G suit for aircraft pilots anticipates G-forces before they are incurred. The system has an available load circuit which receives the actual airspeed signal and computes an available load factor. The system is connected to the command stick of the pilot. The signal from the command stick is multiplied by the available load factor to provide an anticipated G-force. A selector monitors the actual acceleration with the anticipated signal and passes the higher of the two to a valve. The valve controls air pressure leading to the anti-G suit.

Abstract: Apparatus for and a method of rendering selected areas 17, 18 of an aircraft canopy 2 receptive to an adhesive by means of which a detonating cord 7 is attached in loop form to the canopy, to facilitate fracture of the canopy for pilot ejection in an emergency, comprises pretreating those areas 17, 18 by corona discharge. The canopy 2 is mounted in a jig 10 shaped to conform with the canopy and having rebates 11 for accommodating discharge electrodes 12 located at a distance from the canopy 2. A pump 16 is provided to remove ozone formed due to the discharge and trapped between the canopy 2 and the jig 10.

Abstract: An apparatus for producing lift in a flying vehicle comprising a top deck of a flying vehicle having a cylindrical well formed thereinto, a discoidal member positioned within the cylindrical well, an air intake system formed in the center of the discoidal member for drawing air through the discoidal member for use elsewhere in the flying vehicle, and a labyrinth member formed on the periphery of the discoidal member for restricting the clearance between the discoidal member and the wall of the cylindrical well. The discoidal member is adapted and powered for rotating within the well. The top deck has a generally flat exterior surface. A fluid passageway extends through the interior of the flying vehicle for passing air from the air intake system. The discoidal member has a flat top surface generally parallel to the top deck of the flying vehicle. The top surface of the discoidal member is positioned within the well below the upper surface of the top deck.

Abstract: Lightweight armor or high impact structures comprising lamina-like structures comprising zones of decreasing Young's modulus and increasing elongation characteristics. The structure contains at least one ionomer composite having aramid or linearly crystalline polyethylene fibers arranged to dissipate impact forces laterally.

Abstract: A system for protecting the cockpit of an aircraft from airborne contamination is described which comprises a generally tubular curtain of size corresponding to that of the canopy and cockpit and being pleated and collapsible along its length between an extended condition and a folded condition; a tray, attachable to and co-extensive with the canopy sill of the aircraft, the tray having a floor and inner and outer walls defining a circumferential recess for receiving the curtain in the folded condition; a lid for covering the tray with the bottom surface thereof in substantial contact with the inner and outer walls of the tray; a circumferential crimpable lip on each the floor of the tray and on the bottom surface of the lid for engaging respective ends of the curtain and providing peripheral hermetic seals between curtain and tray and between curtain and lid; inflatable circumferential seals in the sill and canopy for releasably attaching the tray to the sill and the lid to the canopy for providing hermetic

Abstract: An in-flight jettisonable protective cover device for protecting fragile, accurate, radomes or signal-responsive components for the major portion of a flight which is capable of being jettisoned in one piece at supersonic speeds from a guided missile, other air vehicles, or space vehicles. The cover device is for use, for example, in combination with a guided missile having a shell structure, a nose portion, and a radome in the missile nose. The cover device is attached to the missile nose for covering the radome such that an inner space is defined. A plurality of shear pins or other quick-release mechanisms attach and retain the cover device to the missile shell. A source of low pressure gas pressurizes the inner space to approximately 50 psi. A rapid-discharging, high pressure gas cartridge produces a high pressure gas for exerting a pressure force on the aft face of the cover device.

Abstract: There is provided apparatus which has an elongated, preferably telescopingly adjustable member having at one end thereof a latch engaging the vertically extending pole or standard of a free-wheeling IV mechanism, and a machanism on the opposite end thereof for attaching the same to a vehicle, preferably a wheelchair. In a preferred embodiment, the latch engaging the vertically extending pole or standard has a symmetrical pair of hingedly joined hemicylindrical pieces which are adapted to encircle the pole or standard, one of the pieces being fixedly attached to the elongated member, and there is on one of the two hemicylindrical pieces a locking pin and on the other one of the two hemicylindrical pieces a latch for engaging locking pin. With the aid of such apparatus, a person acting unaided may safely and conveniently transport a passenger-patient connected to IV equipment or apparatus, despite the need to traverse places where the flooring is uneven.

Abstract: A wing structure for controlling hydrodynamic ram and which includes a substructure having a plurality of individual cells each with a respective boundary, a composite skin disposed on the substructure, and perforations disposed through the composite skin which define a plurality of sections in the composite skin such that each section of the plurality of sections of the composite skin is disposed within the confines of each respective boundary of each of the plurality of individual cells of the substructure so that each section of the plurality of sections of the composite skin forms a blow off panel for relieving pressure created by hydrodynamic ram in a respective individual cell of the plurality of individual cells of the substructure.

Abstract: An active, automatic-firing, impact responsive cable-cutting apparatus for use on conventional aircraft such as helicopters for virtually instantaneously forcibly severing obstructive cables. A lightweight, non-corrosive frame comprising a mounting base portion and an integral, outwardly extending, angular deflection arm is adapted to be selectively mounted on an aircraft or on an extension pole which extends downwardly toward the ground or forward of the nose of the aircraft. Mechanical firing components of the assembly are housed within a cylindrical sleeve adapted to be accessed for maintenance through a removable butt. Sharpened, serrated guide blades extending along outwardly angled forward edges of the frame are adapted to strain the outer periphery of a cable as it is forcibly deflected and guided into a central mouth. A removable cutting block is provided at the interior of the apparatus adjacent the cutting assembly mouth in operative association with a rigid, angular, cutter knife.

Abstract: A safety chamber of the telescopic type usable for an airplane includes a plurality of wall segments, granular cushioning materials and a parachute. As long as it is not in use, the wall segments are accommodated in a contracted state in the space on the ceiling of the airplace. In the event of an occurrence of emergency the wall segments are lowered one after another to constitute a chamber in which a single seat assembly is incased together with passengers sitting thereon. When the lowermost wall segment reaches the floor of the airplace, a plurality of hooks around the lower edge thereof are engaged with recessed parts on the bottom of the seat assembly and at the same time the cushioning materials fall down from the ceiling while expanding by themselves whereby the hollow space in the expanded chamber surrounding the passengers is filled with cushioning materials for the purpose of preventing the passengers from the influence of shocks.

Abstract: An impact-resistant laminate has a front glass sheet which receives an impact such as a bullet, and a rear polycarbonate sheet. A thin polycarbonate sheet up to about 1 mm thick is adhered to the rear polycarbonate sheet, and carries a self-healing polyurethane coating.

Abstract: An aircraft windshield system which employs a relatively thin outer windshield member in combination with a thicker ballistic protection inner windshield member and a plurality of electively disposable specific threat protecting panel members is disclosed. The specific threat protecting panel members are arranged for storage during normal peacetime use of the aircraft, and for rapid and selective deployment into protecting positions when elected by the aircrew or as determined by a mission knowledgeable computer apparatus or other means. The results of studies indicating the desirability of multiple-panel windshield structures from both cost and performance viewpoints are also disclosed. The disclosed windshield system is especially applicable to future military aircraft such as the Advanced Tactical Fighter (ATF) and Advanced Tactical Bomber, and may also be retrofitted to existing aircraft for upgrading purposes.