Abstract: A small weapons shield for helicopters consisting of a protective shield (10), which consists of a light-weight, ballistic-resistant composite material, extension rods (20) made of steel, and support wires (30) made of steel cable. The support wires (30) are connected to the protective shield (10) through holes protected by eyelets (40) that protect the shield from fraying. The shield is supported away from the helicopter (1) to prevent transferring large impact forces directly to the helicopter (1).

Abstract: An apparatus and method for latching a canopy to a vehicle, such as an aircraft, that avoids plastic creep and crazing due to concentrated loads is provided. The apparatus includes first attachment components that are at least partially embedded within an injection-molded canopy and second attachment components that are connected to the canopy rail for attaching to the one or more first attachment components and thereby attaching the canopy to the canopy rail.

Abstract: The present invention is a hybrid engine exhaust heat shield assembly that includes a plurality of sections. The plurality of sections include one or more sections formed of titanium (or other high heat resistant material) by a casting process, and one or more sections formed of another heat resistant material produced in a manner other than a casting process. The plurality of sections are aerodynamically shaped for thermal protection of the aft pylon. The other heat resistant material is titanium (or other high heat resistant material) that is formed by a hot formed process, or by a super plastically-formed process. The one or more sections formed by the casting process includes heat (plume) deflector flanges.

Abstract: The invention provides an array of blast-resistant partitions arranged to subdivide a predetermined space into a multiplicity of interconnected subspaces and thereby to substantially confine an explosive blast to one or more of the subspaces while protecting the remaining subspaces in the predetermined space.

Abstract: An apparatus and method for lining a cargo hold, and an aircraft cargo hold so lined are provided. A plurality of liner panels have formed edges angling away from facing sides of the liner panels. A mounting channel mounted on a supporting structure has an opening for receiving the angled edges of the liner panels. The edges of the liner panels are inserted into the mounting channel. The liner panels are secured by a spline configured to forcibly lock the liner panels into the mounting channel when the spline is pressed against the angled edges of the cargo liner sections and into the mounting channel.

Abstract: A ballistic and/or fire barrier for protecting objects in an interior of a vehicle due to projectile penetration and/or fire includes one or more layers of high strength fabric positioned towards an outer shell of the vehicle. The high strength fabric is substantially fixedly or fixedly positioned with respect to the outer shell of the vehicle. In another embodiment, the ballistic and/or fire barrier protects objects in a structure from damage due to projectile penetration. The ballistic and/or fire barrier includes at least one layer of high strength fabric positioned towards an outer housing of the structure. The high strength fabric is substantially fixedly positioned with respect to the structure towards either the inner or outer surface of the outer housing. In another embodiment of the present invention, a ballistic barrier protects a wearer of the ballistic barrier from damage due to projectile penetration.

Abstract: A static discharge cable is attachable to a rescue hook or other component being lowered by an aircraft. The cable has a first fitting attachable to the hook or other component, a second fitting attached to the first fitting, and a conductive cable attached to the second fitting. The first and second fitting are attached using a shear pin. Attached to the other end of the cable is a light holder.

Abstract: Methods and compositions for fabricating composite parts including at least one structural material and at least one protective material that are integrally bonded without the use of secondary bonding operations. One or more of the materials forming the layers of the composite parts may be a ceramic composition with or without porosity and one or more of the materials may be a polymer composition. Methods including co-injection processes also are provided for fabricating multi-layered structures in which each layer serves a desired function while still being integrated into the overall structure.

Abstract: A method for mitigating toe strike in a cockpit of an aircraft includes providing an airbag module attached to an instrument console located in the cockpit of the aircraft; releasing an airbag from the airbag module after an ejection sequence begins; using the airbag to protect a pilot's lower limbs from striking the instrument console as the pilot begins ejecting.

Abstract: A method and system for attaching a canopy to a vehicle, such as an aircraft, is provided. The system includes first and second sections. The first section attaches to the second section with a portion of the canopy being secured between the attached first and second sections. The canopy is molded to conform with the secured first and second sections. In one embodiment, the canopy is molded to include one or more fastener receiving holes with or without bushings. In another embodiment, the first or second sections include one or more channels for receiving an inflatable bladder. The first or second sections are configured to be received by the vehicle.

Abstract: It guarantees the immediate disablement of any violent action bringing the perpetrators under control without any possibility of escape, attack or aggression. It includes an image transmission system with night-time and daytime vision in an angle of 360°, wide angle and zoom, the image being transmitted continuously to the cockpit (2) and to a security cabin (4), as well as providing images for ground. The cabins (2, 4) are sterile, with hermetic sealing, furthermore having an independent communication system between them and an independent aeration and ventilation system. Selective switched triggers for paralysing gas are provided in both cabins (2, 4) with independent action by the captain of the aircraft in order to inundate the passenger cabin with complete paralysis of everyone therein.

Abstract: The invention concerns a lighter-than-air craft for transporting by air equipment and passengers, more particularly, it concerns an aircraft whereof the frame (1) made of light metal and erected vertically, contains and protects the passenger compartment (4) of the invention, and all the components of the invention which, by a mass-reducing assembly (2-8-9-11-19), uses light gas power for neutralizing the earth's gravitational pull. Electric motors actuating propellers (6-7) with multiple blades and powered by a mini-electric power unit (5) enable to counter the force of mean winds, so to lift the neutralized mass and control the aircraft movements. The aircraft wide external surfaces (11-12) are used as wing system, a sailboat keel being replaced by a gyroscope (10) stabilizing effect and by the thrust of the lateral propellers (6).

Abstract: A ceramic element, e.g., a sapphire dome, is joined to a metallic element, e.g., a vehicle body comprising a titanium alloy, by an attachment structure, e.g., comprising niobium. The attachment structure comprises: (1) a form-factored, compliant metallic transition element having a “C” shape; (2) a first joint material connecting an upper portion of the transition element to the ceramic element; and (3) a second joint material connecting a lower portion of the transition element to the metallic element. A method is provided for attaching the ceramic element to the metallic element, using a single brazing operation. The presence of the attachment structure further minimizes the stresses related to the different coefficients of thermal expansion in the ceramic/attachment/titanium connection.

Abstract: This invention relates to a protection device (30) for an air intake structure (6) of a jet engine (1), said structure comprising an air intake cowl (8) and an air intake lip (10) that jointly delimit a fan case ducting (12), the cowl having a top portion provided with at least one ventilation scoop (20) and the lip defining a fan case ducting intake (14), the device comprising a protective tarpaulin (32) with a main portion (34) designed to close off the intake (14) when the device is assembled on the structure (6). According to the invention, the protective tarpaulin also comprises a secondary portion (40) fixed to the main portion, said secondary portion being provided with stiffening means (42) and designed to partially cover the cowl (8), to close off each ventilation scoop.

Abstract: The cockpit door has a hinge on one side and a latch device on the other side that can be operated only from the cockpit side. To the inner side of the door panel is mounted a reinforcement member 100 having a body formed by laminating layers of aromatic polyamide fiber sheets and thermoplastic adhesive and subjecting the same to hot pressing to form an integral member. Mounting portions 150 and 160 are formed to the rim portion of the reinforcement member body 110, and rivet inserting holes 180 are machined to the portions. The mounting portions are bent by 90 degrees, and fixed to a frame using rivets.

Abstract: A flexible insulation blanket having a ceramic matrix composite (CMC) outer layer, and a method of producing a flexible insulation blanket having a smooth, aerodynamically suitable, outer surface by infiltrating ceramic material within the outer ceramic fabric layer of the flexible insulation blanket and curing the ceramic material to form a CMC layer. The CMC layer is cured while the blanket is under compression such that the resulting CMC layer has a smooth surface.

Abstract: An apparatus and method for attaching an injection-molded canopy to a hinge assembly is provided. The apparatus includes attachment components that are at least partially embedded in the injection-molded canopy. A hinge assembly attaches to the attachment components for controlling the position of the canopy. The canopy is a polycarbonate or acrylic frameless canopy. The hinge assembly is hingedly attached to the vehicle. The hinge assembly includes a center support and port and starboard supports. The center support is located approximately along a centerline of the canopy, the port support is located on a port side of the vehicle, and the starboard support is located on a starboard side of the vehicle.

Abstract: Apparatuses and methods for preventing foreign object damage (FOD) to aircraft engines are disclosed. In one embodiment, a deployable blocker is coupled to a wing portion and/or a fuselage portion of the aircraft and is configured to prevent debris from travelling on a direct trajectory from a landing gear wheel to an engine air inlet. In other embodiments, the blocker can prevent debris from bouncing off the wing lower surface into the engine inlet, or sticking to the wing lower surface and falling into the engine inlet. The deployable blocker can cover at least a portion of the landing gear when the landing gear is retracted and the blocker assembly stowed. In another embodiment, the blocker can be mounted to the landing gear.

Abstract: Directed toward universal commercial-airliner application as an air/ground-lifesaving function, this cost-effective retrofitable system enables airliner-pilots to conveniently actuate an inconspicuous AIRCIA™/enable-switch,—thereby instantly disabling onboard flight-commands to render the airliner's guidance-system irretrievably placed into total reliance upon its existing autopilot-system in RF-communication with encrypted remote ground/air-intercept personnel. Acting to virtually confound any criminal-attempt by a hijacker to commandeer an airliner, the airliner thus becomes flown only as directed by an authorized remote/flight-control station in cooperation with the airliner's remotely-reprogrammed onboard avionics-system, automatically vectoring the airliner to land safely via the existing avionics/autopilot-system at a designated airport.

Abstract: A flexible insulation blanket having a ceramic matrix composite (CMC) outer layer, and a method of producing a flexible insulation blanket having a smooth, aerodynamically suitable, outer surface by infiltrating ceramic material within the outer ceramic fabric layer of the flexible insulation blanket and curing the ceramic material to form a CMC layer. The CMC layer is cured while the blanket is under compression such that the resulting CMC layer has a smooth surface.

Abstract: A fuel inerting system, comprising a first supply means (2) to supply an inert gas to a fuel tank (8) to scrub the fuel therein when the ullage (16) of the fuel tank is inert, and a second supply means (4) to supply the inert gas to scrub the fuel (6) therein when the ullage of the fuel tank is not inert, the first and second supply means (2, 4) being individually operable by means of a valve arrangement (10), in such a manner that only one of the supply means is operable at any given time. The inert gas consists of nitrogen enriched air, produced by passing air from a pressurized area of the aircraft through a nitrogen separator located within, but removable from, the aircraft.

Abstract: The present invention relates to a new type aircraft. The aircraft includes the airframe and wing, characterized in that the transverse section of airframe has an oblate (oval) profile with corrugated area on the ventral of airframe; the aircraft has uneven friction areas on the underside surface of wing; there are fireproof & anti-wear layers on the envelopes of airframe ventral and friction areas; the said fireproof & anti-wear layers have tire rubber material. When the aircraft is in motion with high velocity, the friction with air is increased, which produces bigger lift with more aircraft load and shortened takeoff & landing distance of aircraft, meanwhile the safe peril to aircraft caused by the shear transformation of wind in flight is prevented effectively; the fireproof & anti-wear layers on the envelopes of airframe ventral and friction areas have an effect on higher anti-wear proof and longer aircraft life.

Abstract: A system and method for attaching an injection molded canopy to a vehicle is provided. The system includes a canopy rail attached to the vehicle and an injection-molded canopy that is molded to be securely received by the canopy rail. The canopy is a polycarbonate or acrylic frameless canopy. The system also includes a seal, a canopy position sensor, a sealing component, and a canopy handle for controlling position of the canopy. The sealing component inflates the one or more seals with one of a liquid or gas when the canopy is sensed in the closed position. The system also includes a ground sensor. The sealing component deflates the seal if the canopy handle is in an open position and the aircraft is on the ground.

Abstract: An apparatus and method for attaching an injection-molded canopy to a hinge assembly is provided. The apparatus includes attachment components that are at least partially embedded in the injection-molded canopy. A hinge assembly attaches to the attachment components for controlling the position of the canopy. The canopy is a polycarbonate or acrylic frameless canopy. The hinge assembly is hingedly attached to the vehicle. The hinge assembly includes a center support and port and starboard supports. The center support is located approximately along a centerline of the canopy, the port support is located on a port side of the vehicle, and the starboard support is located on a starboard side of the vehicle.

Abstract: A latching system and method for a canopy are provided. Devices are partially embedded in the canopy and latches are slideably received within a canopy rail of the vehicle. The latches are controlled by a latch controller and lock the canopy to the vehicle. A canopy position sensor senses the position of the canopy, and a canopy controller controls the position of the canopy. The latch controllers control the position of the one or more latches based on the sensed position of the canopy or the status of the canopy controller. A latch position sensor senses the position of the latches and a vehicle position sensor senses the position of the vehicle. The canopy controller controls the position of the canopy based on the sensed position of the latches and the sensed position of the vehicle.

Abstract: A system and method for attaching an injection molded canopy to a vehicle is provided. The system includes a canopy rail attached to the vehicle and an injection-molded canopy that is molded to be securely received by the canopy rail. The canopy is a polycarbonate or acrylic frameless canopy. The system also includes a seal, a canopy position sensor, a sealing component, and a canopy handle for controlling position of the canopy. The sealing component inflates the one or more seals with one of a liquid or gas when the canopy is sensed in the closed position. The system also includes a ground sensor. The sealing component deflates the seal if the canopy handle is in an open position and the aircraft is on the ground.

Abstract: An apparatus and method for latching a canopy to a vehicle, such as an aircraft, that avoids plastic creep and crazing due to concentrated loads is provided. The apparatus includes first attachment components that are at least partially embedded within an injection-molded canopy and second attachment components that are connected to the canopy rail for attaching to the one or more first attachment components and thereby attaching the canopy to the canopy rail.

Abstract: A method and system for attaching a canopy to a vehicle, such as an aircraft, is provided. The system includes first and second sections. The first section attaches to the second section with a portion of the canopy being secured between the attached first and second sections. The canopy is molded to conform with the secured first and second sections. In one embodiment, the canopy is molded to include one or more fastener receiving holes with or without bushings. In another embodiment, the first or second sections include one or more channels for receiving an inflatable bladder. The first or second sections are configured to be received by the vehicle.

Abstract: A latching system includes a flexible hydraulic latch male portion, and a receiving rail female portion. The receiving rail female portion receives the hydraulic latch male portion therein. The latching system includes a hydraulic system for providing hydraulic fluid into the flexible hydraulic latch. The latching system includes a controlling device for controlling operation and hydraulic fluid insertion by the hydraulic system into the flexible hydraulic latch. The latching system includes an ejection system coupled to the hydraulic system or flexible hydraulic latch for reducing hydraulic fluid pressure within the flexible hydraulic latch during an ejection evolution.

Abstract: The inventions described here apply to the design of the canopy of a small airplane. The geometry of the joint between the canopy and fuselage is such that no water is allowed to enter the cockpit when flying in wet weather. The joint between the canopy and fuselage is not sealed. Small amounts of water can get thru the joint. This is carried away by a gravity operated rain gutter system before it enters any space in the fuselage occupied by people, instruments, or luggage.

Abstract: An impact resistant insulation tile is provided that is capable of withstanding the impact of Micrometeriods and Other Debris (MMOD). The tiles are secured to an exterior surface of a Reusable Launch Vehicle (RLV). A durable coating is applied to the exterior surface of a thermally insulative layer to fragment and slow down MMOD that collide with the tile. In addition, a shock layer may be embedded within the thermal insulator to further reduce the size and speed of MMOD particles. A ballistic strain isolator pad may also be located between the thermal insulator and the RLV structure to capture fragmented particles.

Abstract: A multi-section aircraft door includes a sliding joint permitting a lower door section displacement into the flight deck area. The door includes an upper door section having a lower edge. The lower edge is connectably joined to an upper member of a two-member sliding joint. The upper member slidably joins to a sliding joint lower member. The sliding joint lower member is connectably joined to a lower door section upper edge. The upper member and the lower member of the two-member sliding joint include paired apertured embossments. A frangible pin slidably mates in each apertured embossment pair. A lever and cam form a frangible pin removal assembly. The lever is held in a normally upright position by either a spring device or a clevis and pin assembly. A rotating clasp or a ball détente system can also replace the frangible pin/apertured embossment and cam/lever.

Abstract: A two layer door is provided. The first layer is made of a plurality of metallic members with a portion of the metallic members having one or more channels adapted to receive one or more armor panels. The second layer is made of the channels of the metallic members and armor panels disposed within the channels. The door also has one or more pivotally attached panels to the door that are adapted to open at a preselected pressure differential across the door. The door is also available as a kit.

Abstract: An airborne platform comprising: (a) an aerodynamic body; (b) a protected element within the aerodynamic body; and (c) a cover, reversibly secured to the aerodynamic body, for protecting the protected element from an external atmosphere. The present invention is particularly suited for an electro-optical detection system equipped with an optical dome or window. Optical windows carried on airborne platforms are known to be particularly sensitive to the high temperatures generated by air friction at super-sonic speeds. By covering such a window when the airborne platform is in flight, and releasing the cover just before use, the electro-optical detection system equipped with the optical window can be made operative, even at airborne platform speeds of several Mach and higher.

Abstract: A movable structural component for a thermomechanically stressed assembly at least partially from fiber reinforced ceramic is disclosed, wherein the movable structural component comprises at least one structural element made by an polymer infiltration and pyrolysis process and at least one structural element made by a chemical vapor process.

Abstract: The present invention is a hybrid engine exhaust heat shield assembly that includes a plurality of sections. The plurality of sections include one or more sections formed of titanium (or other high heat resistant material) by a casting process, and one or more sections formed of another heat resistant material produced in a manner other than a casting process. The plurality of sections are aerodynamically shaped for thermal protection of the aft pylon. The other heat resistant material is titanium (or other high heat resistant material) that is formed by a hot formed process, or by a super plastically-formed process. The one or more sections formed by the casting process includes heat (plume) deflector flanges.

Abstract: A pitot tube cover that is arranged with a cavity to encompass the pitot tube, a central vertical split separates the cover and allows it to separate from the pitot tube. A wind surfaces channel the wind into the split, and a spring holds the cover onto the pitot tube. Once the aircraft reaches a predetermined speed, the wind is forced by the front angled wind surfaces into the split, thus separating the cover from the pitot tube and exposing the tube's opening to the oncoming wind pressure.

Abstract: A ballistic barrier for protecting an aircraft from damage due to projectile penetration, the aircraft having a fuselage including an outer skin, an inner panel and a structure. The ballistic barrier includes at least one layer of high strength fabric disposed between the outer skin and the inner panel of the aircraft which is substantially fixedly positioned with respect to the fuselage of the aircraft. Preferably, the at least one layer of high strength fabric comprises a plurality of plies. One of the plies can be a felt. Another of the plies can comprise woven fibers. Also preferably, the at least one layer of high strength fabric comprises a polymer material such as one or more of aramid material, polyethylene material, and polybenzoxazole material.

Abstract: A multi-layer tile material produced from layers of alumina enhanced thermal barrier material having different densities. The insulation layers are bound together by a high strength, high temperature alumina or silica binder having a coefficient of thermal expansion similar to that of the insulation layers. Use of the multi-layered tile allows the problems of tile slumping and of insufficient heat management associated with low density alumina enhanced thermal barrier tile to be overcome.

Abstract: A security screen device for protecting persons and property is provided. The security screen device comprises an enclosed screen housing defining a screen receiving area. A screen material made of high strength fibers is receivable within the screen housing in an undeployed condition with the screen material having a first edge and a second edge. The first edge is secured within the screen receiving area and a weighted bar is secured to the second edge of the screen material. An activation mechanism opens one side of the screen housing releasing the screen material from the housing into a deployed condition such that the second edge of the screen material travels in a direction generally away from the enclosed screen housing thereby pulling the screen material from the enclosed screen housing.

Abstract: A layer (16, 24) of a mesh or mail material is bonded to the opposite sides of a ballistic layer (14, 22) a bullet resistant composite material. The layer (18, 26) of relatively lightweight body material, e.g. structural honeycomb, is bonded to the outside of each layer (16, 24) of mesh or mail material. A ballistic layer (28) may be provided on the outside of each layer (26) of relatively lightweight body material. Adhesive material secures the layers together to provide a unified panel. The panel may be a part of the door that is between the cockpit of an airplane and the region in the airplane rearwardly of the cockpit.

Abstract: An encapsulated insulation composite system for increasing the burn through resistance of an aircraft fuselage includes: an insulation layer of glass fiber or foam insulation and a coating or interleaf barrier layer of a high temperature resistant material and/or a coating or barrier layer of a high temperature resistant material on an outer major surface of the insulation layer of the composite and a film encapsulating the composite. Preferably, the barrier layer or layers include a reflective mineral, such as a reflective mineral containing coating carried on a sheet material. Preferably, the encapsulating film is a polymeric film such as a polyimide film.

Abstract: The underwater exterior surface of a watercraft is covered by a deformable protective covering formed from compartmental sections that are dimensionally sized, shaped and mechanically connected to each other for effective attachment of the assembled covering to and removal from the hull of the watercraft. The protective covering is of a cross-sectional construction arranged to provide protection against the damaging effects of underwater explosions by minimizing related adverse physical effects on the entire hull of the watercraft as well as mechanical and electrical components associated therewith.

Abstract: A bullet proof armor plate fabricated of layered ceramic material is mounted on the outer bottom wall of a helicopter in spaced relationship to such wall. A frame is used to support the armor plate, this frame being removably attached to mounts supported on the bottom wall of the helicopter at points where there are existing apertures. The front end of the support frame for the armor plate is aero-dynamically configured to minimize drag.

Abstract: A protective panel for a reusable launch vehicle provides enhanced moisture protection, simplified maintenance, and increased temperature resistance. The protective panel includes an outer ceramic matrix composite (CMC) panel, and an insulative bag assembly coupled to the outer CMC panel for isolating the launch vehicle from elevated temperatures and moisture. A standoff attachment system attaches the outer CMC panel and the bag assembly to the primary structure of the launch vehicle. The insulative bag assembly includes a foil bag having a first opening shrink fitted to the outer CMC panel such that the first opening and the outer CMC panel form a water tight seal at temperatures below a desired temperature threshold. Fibrous insulation is contained within the foil bag for protecting the launch vehicle from elevated temperatures.

Abstract: To respond to internal threats to the aircraft, an incapacitating aerosol can be released into the cabin of the aircraft. The incapacitating aerosol prevents the hijackers or terrorists from accomplishing their goals. While the hijackers or terrorists are incapacitated, the pilot can land the aircraft at the first opportunity and let trained security forces, such as the police, board the aircraft and deal with the hijackers/terrorists.

Abstract: An environment control system for a body of an aircraft that provides controlled ventilation of the interior space of an aircraft body, facilitating reduction of volatile organic compounds (VOCs) within cabin air, dehumidifying and reducing moisture condensation and thus corrosion and other moisture related problems within the envelope, allowing increased humidification of cabin air, and allowing suppression of fires within the envelope. The environment control system includes at least a cabin and an envelope. It includes supply means for supplying a flow of dry ventilation air to the aircraft body. An airflow control device is capable of dividing the flow of ventilation air onto an envelope ventilation air stream and a cabin ventilation air stream. An envelope ventilation duct system directs the envelope ventilation air stream into the envelope, and a cabin duct system directs the cabin ventilation air stream into the cabin.

Abstract: A ballistic shield containment system for preventing fragments expelled from an engine assembly from penetrating the casing of an adjacently disposed engine is provided. In a turboprop engine assembly having two power sections connected through a combining gearbox to a single propeller shaft, it is imperative that failure of the rotor disks in one engine not cause failure of the remaining engine. A substantially rectangular shaped panel member is supported at approximately the mid-point between the power sections by a support truss system extending from the panel to a space frame. The space frame is supported by a separate truss system connected to fixed bulkhead. The panel includes reinforcing ribs to prevent fragment penetration and excessive deformation. Each of the truss members is attached at either end to a spherical bearing capable of transmitting force loads while preventing transmission of moment loads.

Abstract: A canopy fragilization system comprising an ordnance-free breakable canopy for aircraft and other transport vehicles. A breakable portion of the canopy includes embedded wiring that is installed along selected portions of the canopy to be cut out or fragilized in a desired pattern. A flux compression generator (FCG) is located on board the vehicle to power the fragilization system wherein an electrical surge is generated by the FCG during an ejection sequence. The electrical surge generated by the FCG is delivered through an electrically conductive cable to the wired canopy thereby fragilizing and structurally weakening the canopy. Methods and apparatus are further provided for fragilizing an aircraft canopy by delivering an electrical surge from a compact FCG to a pre-wired canopy.

Abstract: An improved vehicle glareshield having a structural body having a predetermined size and shape adapted to protect an instrument panel in a vehicle from glare; and a plurality of controlled strength members carried in said structural body which collapse in a controlled manner upon high force impact by an occupant in order to reduce a deceleration force experienced by an occupant upon impact with said instrument panel.