Abstract: A system and an apparatus for matching infrared radiation emitted from aircraft skins to background infrared radiation in order to minimize the contrast between the two radiations, and to thereby camouflage the aircraft from electro-optical detection systems. In particular, there are employed heat pipe systems and apparatus for cooling the internal surface of an aircraft skin, and especially the bottom portion of an airframe, for the camouflage of the aircraft from the look-up viewing aspect angles of electro-optical detection systems by transferring heat otherwise emitted by the skin to the fuel which is carried by the aircraft.

Abstract: Lightning protection utilizing lightweight electrically conductive coatings with a conductance of approximately 220 to 350 mhos per square co-cured or secondarily bonded to the outer surface of thin skin composite structure. Selection of either 2 to 3 ounces per square yard or aluminum mesh of 1 to 1.5 ounces per square yard, depending on corrosion compatibility, satisfy the conductance requirement and has shown superior lightning protection over heavier weight conductive coatings.

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: An inflatable restraint system for holding and securing an aircrew member in his seat during ejection from an aircraft has one or more members forming a shield around him or her. The system is controlled to inflate after the aircrew member has started the sequence of ejection and before the rockets that power the seat from the aircraft are ignited. The forces of windblast are deflected by the inflatable restraint from the aircrew member as the aircrew member enters into and remains in the windblast and in his seat.

Abstract: A fairing for protecting a payload from excessive acoustic energy is disclosed. The fairing can be used with a launch vehicle for launching payloads such as satellites or the like. The invention provides structure to surround a payload and absorbs acoustic energy so that the noise is suppressed to acceptable levels and the payload is not damaged. The fairing comprises a two dimensional honeycomb core having composite face sheets and load skins bonded to each side of the core. A water barrier is connected to the inner side of the fairing to prevent moisture from entering the payload area. The fairing wall further includes a liquid which is added to the two dimensional honeycomb layer. The liquid is jettisoned during the launch of the vehicle at a predetermined time when the additional acoustic suppression provided by the mass of liquid is no longer needed.

Abstract: The present invention is a nanocomposite layer applied to the leading edge of an airfoil. The nanocomposite is an elastomeric matrix reinforced with nanosized reinforcing particles ranging in size from about 0.5 to 1000 nanometers and preferably ranging in size from about 5 to 100 nanometers. These nanosized reinforcing particles improve the mechanical properties of a pure elastomer. Improving such properties assists the nanocomposite layer in absorbing and dissipating the impact energy caused by the repeated impact of particulate matter, such as sand and rain. Adding the nanosized reinforcing particles to an elastomer allows the nanocomposite to absorb the impact energy over a larger volume in comparison to a pure elastomeric material. The nanocomposite layer is, therefore, capable of withstanding the repeated impact caused by the particulate matter for a greater length of time compared to a pure elastomer.

Abstract: Inflation of impact absorbing bags is effected in time delayed relation to selective jettisoning of damaged landing gear on a helicopter prior to landing for replacement of the landing gear by the bags, without puncture thereof by the landing gear being jettisoned.

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: On an aircraft, particularly of the commercial type, a landing gear (16) placed in front of a fuel tank (18) comprises a rod system (32) capable of coming into contact with a sliding rail (52) formed on a reinforced structural part (48) of the aircraft, in the event of accidental tilting of the gear to the rear. The deformation resulting from the rod system (32) then successively induces the complete slackening of the damper (24) of the gear, the rupture of its slack limit stop (25), followed by the rupture of a part of the rod system (32). The lower part of the gear (16) is then ejected and guided by a rear part (52b) of the sliding rail (52), with no risk of perforation of the tank (18).

Abstract: A countermeasure device for the in-band frequency agile laser threat posed to the eyes of operator(s) comprises a rotating shutter operating at a predetermined speed and with alternating clear and nearly opaque sectors. The shutter is designed to spin in front of the operator's field of vision at a rate sufficient to avid a flickering image. The device significantly increases operator protection from an initial laser pulse over existing devices while allowing sufficient ambient light to reach the retina for clear vision. This device will eliminate dazzling which interferes with operator's ability to pinpoint the location of the laser source for neutralization. The device also eliminates the occurrence of damage to both eyes simultaneously.

Abstract: Lightning protection utilizing lightweight electrically conductive coatings with a conductance of approximately 220 to 350 mhos per square co-cured or secondarily bonded to the outer surface of thin skin composite structure. Selection of either 2 to 3 ounces per square yard or aluminum mesh of 1 to 1.5 ounces per square yard, depending on corrosion compatibility, satisfy the conductance requirement and has shown superior lightning protection over heavier weight conductive coatings.

Abstract: A vehicle restraint system for a seated occupant including a lap belt system and an inflatable member mounted on the lab belt and restrained by the belt when inflated. The restraint system is applicable to multi-row seated vehicles in which a control system controls air bag deployment in rows located at first, second and other vehicle locations. Further, the system may include a device for detecting an impending collision of the vehicle and an object and deploy bags in anticipation of such collision.

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

Abstract: A thermal blanket (28) for use in connection with a spacecraft (10) or spacecraft component for providing a thermal control coating. The thermal blanket (28) includes a plastic substrate (22) on which is deposited a silicon film (24) by a vacuum deposition process. The silicon film (24) provides a relatively high infrared light transmission and moderate absorption of high energy bandwidths in the solar spectrum that allows for the reflectance of high energy visible light and the emittance of infrared radiation. Additionally, the silicon film (24) is a hard, robust coating that provides resistance to humidity and other corrosive environments.

Abstract: Disclosed is a first miniature digital video camera in a streamlined configuration mounted on or in proximity to the vertical stabilizer of an aircraft and in communication preferably with both remote digital video recording apparatus and at least one cockpit video monitor. The video recording apparatus is preferably one or more channels on the flight data recorder for postcrash investigation. The preferred embodiment would employ two video cameras, one on anterior or front of the tail assembly, and one of the posterior or rear of it. One alternative embodiment would consist of only one video camera, fastened to an extension of the tail assembly. The second preferred embodiment would include two video cameras, one of which would be mounted on the posterior end of the tail assembly, the other on the under side of the plane, just behind the wings.

Abstract: An aircraft landing gear (16) located in front of a fuel tank is equipped with a protection device (22) designed to at least partially automatically disconnect the landing gear (16) from the structure that supports it. For example, the protection device (22) comprises a part (40) hinged on the landing gear, and mechanisms (42) connecting this part to pins (38) through which the landing gear (16) is installed on the aircraft. In the case of a bad landing, the landing gear pivots backwards and the part (40) collides with a reinforcement wall placed on the tank. The part (40) then pivots about its axis and releases the pins (38) from their housing. Perforation of the tank is thus prevented.

Abstract: A missile has a body with a substantially circular nose opening therein, and a ceramic radome sized to cover the nose opening. A compliant metallic circular transition element is disposed structurally between the radome and the body. The transition element includes an elongated compliant arm region and an upper crossbar region positioned adjacent to the radome such that the lower margin surface of the radome is adjacent to an upper side of the crossbar region. A brazed butt joint is formed between the lower margin surface of the radome and the upper side of the crossbar region of the transition element. A second brazed butt joint is formed between the vehicle body and the lower side of a lower crossbar region joined to the arm region. The brazed joints are formed with a single active braze alloy which permits the entire joining operation to be accomplished in a single furnace cycle.

Abstract: A device for retaining an element ejected by a pyrotechnic device when it is fired comprises at least one metal cap placed behind the nozzle of the device and designed to receive the ejected element, the cap being held in position by curved rigid links. The kinetic energy of the captured element carries along the cap and the captured element and the motion of the assembly is braked by the deformation of the rigid links. Application especially to the retaining of the rear igniter of a missile.

Abstract: A occupant protection system for protecting an occupant of a motor vehicle, boat, or airplane during a crash. The occupant protection system includes a chair positioned inside a vehicle such as an airplane, automobile, truck, or a boat. The chair has a seat portion and a backrest portion. The seat portion has a pair of leg clamp panels pivotally coupled to it to lock a pair of legs to the seat portion in anticipation of a crash. The backrest portion has a pair of arm clamp panels pivotally coupled to it to press the arms and torso of a user towards the backrest and hold them tightly therebetween. Also disclosed is a capsule in which the chair is disposed. The capsule has several protective layers. An emergency raft forms part of the backrest of the chair when not in use, and is removable for use in case of an accident on or above water.

Abstract: A vehicle that combines the freedom and swiftness of flight with the utility of surface travel. A simple, light weight, safe and stable conveyance with positive yaw-roll coupling, special safety features, no fold wing stowage and a unique single power source. It can be built using common tools and techniques with readily available materials at a cost competitive with the family automobile.

Abstract: The present invention is a dissipating protection energy system designed to receive and safely dissipate the kinetic energy from high energy fragments. The energy dissipation system dissipates energy transferred to it by the incremental and progressive rupturing at an approximately constant force of strategically placed sacrificial stitching applied to a number of high strength straps, such as an aromatic polymide fiber of extremely high tensile strength. Thus, the energy dissipation system provides a lightweight device for controlling and dissipating the dangerous and destructive energy stored in high strength fragments released by catastrophic failures of machinery minimizing damage to other critical components.

Abstract: A missile includes a fuselage with a roll axis and a nod axis perpendicular to the roll axis, and a conformal window mounted to a forward-facing end of the fuselage. There is a sensor system with a field of regard through the window and a line of sight, and a sensor system pointing mechanism affixed to the airframe and upon which the sensor system is supported. The sensor system pointing mechanism includes a gimbal structure having a first degree of rotational freedom about the roll axis and a second degree of rotational freedom about the nod axis, and a linear translational mechanism connected to the sensor system. The linear translational mechanism is operable to translate the sensor system away from the window with increasing angular deviation of the line of sight of the sensor system from the roll axis. Preferably, the translational mechanism is a slider-crank mechanism.

Abstract: A light weight decoy for deceiving radar and forward looking infrared tracking systems. The decoy provides the same radar cross-section as that of an intercontinental ballistic missile (ICBM) and is thermally massive across the entire black body spectrum. Thermal massiveness is accomplished by measuring the temperature of the decoy outer surface and the temperature of the space surrounding the decoy, obtaining the differential temperature, and radiating heat within the decoy to maintain the surface thereof at a temperature similar to that of an ICBM.

Abstract: A protective mat to indicate load bearing and non-load bearing flat surfaces on an aircraft. The mat is formed of a flexible non-slip material and has indicia that correspond to indicia upon aircraft flat surfaces, the indicia on the aircraft flat surfaces indicating the weight bearing capability of those surfaces. The mat is manufactured so that its configuration are aircraft make and model specific.

Abstract: A helicopter main rotor pylon support structure including a framing structure for supporting the loads applied to the main rotor pylon, and a fire shield for preventing fire from transmitting from an engine or exhaust compartment into an adjacent compartment. The framing structure includes first and second composite main beams, each beam extending adjacent to a engine compartment and an exhaust duct compartment. A plurality of bridge members preferably extend between and connect with the first and second main beams and are formed integral therewith. A plurality of vertical posts are attached to and spaced along the main beams. The vertical posts are engaged with discrete attachment points on the helicopter. There is at least one fire panel mounted to each main beam. The fire panel has side edges which are slidingly engaged with the vertical posts, and a lower edge which is slidingly engaged with a flange formed on the helicopter.

Abstract: This relates to a helicopter in which the outlet nozzle from the turbine engine is provided with an exhaust pipe which mixes the combustion gases with fresh air and directs the mixture downward. Viewed from the outside of the helicopter, the exhaust pipe is completely concealed by a cowling which is separated from said exhaust pipe by an empty intermediate space, air intakes being provided to create a flow of ambient air, including during hovering flight, along the intermediate space as far as an outlet which is open substantially vertically downward.

Abstract: Lightning protection utilizing lightweight electrically conductive coatings with a conductance of approximately 220 to 350 mhos per square co-cured or secondarily bonded to the outer surface of thin skin composite structure. Selection of either 2 to 3 ounces per square yard or aluminum mesh of 1 to 1.5 ounces per square yard, depending on corrosion compatibility, satisfy the conductance requirement and has shown superior lightning protection over heavier weight conductive coatings.

Abstract: In accordance with the present invention, there is provided an aerodynamic control device for integrated use with an aircraft having an inboard lifting member. The inboard lifting member having a leading edge, a pair of opposing distal edges and a trailing edge. The control device is provided with a movable outboard member which extends substantially about the leading, distal and trailing edges of the inboard lifting member and is spaced apart therefrom. The outboard member is provided with a leading edge portion, a pair of opposing distal edge portions, and a trailing edge portion which are collectively movable in unison in relation to the inboard lifting member to form an uninterrupted airfoil surface extending about the inboard lifting member and the outboard member for achieving desired aerodynamic control of the aircraft.

Abstract: An aircraft gas turbine-engine thrust-reverser specifically designed to withstand impacts possibly caused by objects propelled from the engines around which they are mounted, for instance disk or blade fragments. These impacts have the energy to distort the annular thrust-reverser structure or to break its bracing components. An emergency locking system for such thrust reverser (35) each comprises a hinging latch (38) of which one end is in the form of a hook (40) partly enclosing the lock-interfacing mechanism (43) with the latch (38) being automatically biased into closing by an elastic arrangement (47). Such a configuration allows setting up additional mechanical connections which are able to compensate for any distortion of the thrust-reverser's annular structure or for any ruptured bracing component in the event of impact by an engine piece.

Abstract: A Satellite Weather Modification System (SWMS) uses earth satellites to harness solar energy to modify the thermodynamics and composition of the earth's atmosphere. SWMS has three subsystems: The first subsystem includes a network of earth satellites called Satellite Engines (SEs) used to reflect solar energy and/or transform solar energy into other forms of energy beams discharged at specified locations. The media at these locations and the media through which the energy beams pass absorb these energies and change them into heat. The second subsystem includes a large network of Remote Sensing Devices (RSDs). These sensors are used to measure local media compositions, dynamic parameters and thermodynamic properties. Sensor measurements are fed back to the third subsystem, which includes a network of Ground Control Stations (GCSs). GCSs provide energy beam guidance by estimating each beam's characteristics and its aim point trajectory as functions of time.

Abstract: A STOL aircraft has a fuselage 22 vertical 26 and horizontal 27 rear stabilizers and at least one wing made up of a lower primary airfoil 10 and an upper complementary airfoil 11 which, between them, form the inlet 12 and exhaust 14 air ducts. The craft is propelled by one or more cross flow fans 13 contained in a housing(s) 63 (FIG. 7) between the primary 10 and complementary 11 airfoils. The primary 10 and complementary 11 airfoils can be extended and flexed downwardly, by various means.

Abstract: A surface effect craft of simple construction achieving improved operational stability and performance at various speeds. The craft includes first and second main wing sections merge into the central hull to form a continuous aerodynamic wing structure. The wing structures are very thick with maximum thickness ratio of wing thickness to chord length on the order of 25-30% with the first and second wing sections being swept back, merging into first and second vertical side wall directional stabilizers, the wing shaped structure forming a generally U-shaped rear section (as best viewed from a rear plan or sectional view). The craft preferably includes an aft elevated secondary wing structure extending between the first and second vertical side wall directional stabilizers whereby both the main wing sections and the aft elevated secondary wing structure provide lift.

Abstract: A rigid cargo barrier for a cargo airplane includes a lightweight structural bulkhead that is attached to the floor and fuselage shell of the aircraft and a plurality of compact attachments that connect the bulkhead to the floor and fuselage shell of the aircraft. The rigid cargo barrier also includes a restraint system that connects the bulkhead to the aircraft floor and fuselage shell. The restraint system restrains fuselage expansion under crash loads to maintain the bulkhead in place during a crash event and, hence, provide protection to the crew from shifting cargo.

Abstract: A method and apparatus for measuring the lift generated by airfoils of an aircraft. This real-time analysis is accomplished by measuring a differential pressure between the upper and lower lift surfaces of the airfoils. The system comprises the steps of: a) measuring an actual differential pressure between the upper and lower lift surfaces for a given aircraft speed, b) transmitting this actual differential pressure measurement to a computer, c) comparing the actual differential pressure measurement with an optimal pressure differential for the same aircraft speed. The apparatus comprises a fixed array of differential pressure sensor mechanisms for measuring actual pressure differentials and a computer for comparing optimal differential pressure measurements to the actual differential pressure measurements. Each sensor mechanism preferably contains a piezoelectric sensor that communicates with the upper and lower lift surfaces.

Abstract: A barrier membrane for use with articulating mechanical devices includes hinges formed along preferred folding lines. The hinges encourage the membrane to fold in a predetermined manner in response to articulation of the mechanical device. In a preferred embodiment, the membrane is composed of flexible outer thermal layers encasing rigid panels that are spaced apart from each other at the hinges.

Abstract: A surface-protected composite article, such as a missile component, is prepared with a heat-sink substrate, a first composite layer of an pre-ceramic-matrix structural composite material, and a second composite layer of a reinforced silicone pre-ceramic material. The silicone material is co-curable with the organic matrix of the first composite layer. The silicone at the surface of the article is thereafter converted to a silica refractory by an appropriate treatment such as exposure to an oxygen-rich plasma or a high-surface temperature. The silica protects the surface of the composite material.

Abstract: A safety system for visual flight reference system for simulating the geography around an airplane during the landing and the take-off under zero visibility conditions. The inventive device includes a display screen, a keyboard, a hold-down bracket and a central processing unit.

Abstract: A coated ceramic has alumina as an amorphous residue from an alumina sol containing alumina powder or and, optionally, a high emittance powder. The alumina powder alters the rheology and wetting characteristics of the sol to aid in forming the residue and increases the alumina concentration (% solids) in the residue. The high emittance powder radiates heat out of the residue and away from the ceramic when the coated ceramic is heated, such as during orbital reentry.

Abstract: An aircraft canopy fracturing system includes a canopy having fore and aft portions and a region that is severable from the canopy to provide an opening therethrough for the egress of aircraft occupants. The severable region has a shape that inhibits passage of the severable region through the opening created in the canopy once the severable region is freed from the canopy and is displaced aftward relative to the canopy. The canopy fracturing system also may include one or more mechanisms that will impart an aftward impulse to the severable region of the canopy once it has been severed and freed from the remainder of the canopy.

Abstract: An emergency vision device for use in a smoke emergency to enable an user to look through a windshield or view an instrument, comprises a housing; an inflatable enclosure having a first end for being disposed toward an user, a second end for being disposed toward the windshield or the instrument, the inflatable enclosure being stored within the housing when not in use, the first and second ends having first and second transparent panels, respectively, such that visual information from beyond the windshield or from the instrument is transmitted through the second panel to the user through the first panel; a blower operably connected to the inflatable enclosure adapted to inflate the enclosure; a first switch for operating the blower; and a member operably connected to the inflatable enclosure and the first switch such that the switch is activated when the inflatable enclosure is removed from the housing.

Abstract: A missile has a body with a substantially circular nose opening therein, and a ceramic radome sized to cover the nose opening. A compliant metallic circular "T"-flexure element is disposed structurally between the radome and the body and is integral with the body. A niobium-containing washer is disposed between the radome and the "T"-flexure element. The "T"-flexure element includes an elongated compliant arm region and a cross bar region positioned adjacent the radome such that the niobium-containing washer is situated between a lower margin surface of the radome and an upper side of the crossbar region. A first brazed butt joint is formed between the lower margin surface of the radome and an upper surface of the niobium-containing washer, while a second brazed butt joint is formed between a lower surface of the niobium-containing washer and the crossbar region of the "T"-flexure element.

Abstract: A pitot tube cover is arranged with a slot to encompass the pitot tube and a wind surface that is perpendicular to the direction of travel of the vehicle upon which the pitot tube is mounted. Once the vehicle reaches a predetermined speed, sufficient force is applied against the wind surface that causes the cover to rotate about a pivot area, freeing itself from the pitot tube and allowing the pitot tube to operate normally.

Abstract: An airbag module is positioned relative to an aircraft control yoke or shaft, the airbag being actuated by majority voting sensors that are responsive to acceleration forces upon the aircraft. The aircraft control yoke or control yoke post is constructed to telescope, extend, or move a limited distance toward the pilot as the airbag inflates. The yoke carries telescoping, extendable, or movable handle portions that allow left and right hand pilot grip handles to move, if necessary, under the force of the expanding airbag. Hand sleeves may be provided to help maintain the pilot's hands on the grip handles during airbag expansion. The movable yoke and handle portions may be manually or automatically restored to normal operative positions after airbag deflation. The yoke may be formed so as to provide a U shaped section that accommodates a horizontal support or table for holding the airbag module, a map, or a like device.

Abstract: A cargo barrier net installation for a cargo airplane is connected to the floor and fuselage shell of the aircraft. The cargo barrier net installation includes a pair of C-shaped beams that secure the horizontal net straps to the fuselage. The C-shaped beams have a primary portion that is secured to an existing fitting of cargo planes to attempt to eliminate unrestrained movement of the beam assemblies, which movement can cause damage to the aircraft structure.

Abstract: A turbine airfoil unit is described which enables an aircraft to ascend and descend vertically. Multiple turbine airfoil units may be arranged within a large disk-like structure and thereby overcome size limitations placed on helicopters by their rotors. One or more central engines providing a flow of air under pressure relative to ambient air supplies power to one or multiple turbine airfoil units. The pressurized air from the engines is funneled into the containing disk-like structure and distributed to all turbine airfoil units encompassed therein. The supplied air acts on the turbines to rotate the airfoils and thus create lift. The lift is transmitted to the disk-like structure and to the remainder of the aircraft by bearings between the turbine airfoil unit and the containing portion of the disk-like structure. The large disk-like structure is known in the popular culture as a flying saucer.

Abstract: A semiautonomously directed, autonomously controlled, gyroscopically stabilized, horizontal or vertical take off and landing (HOVTOL) flying apparatus employing two vertical lift devices equally and longitudinally spaced from the center of gravity of the apparatus; continuously integrated with a drive train apparatus, optional single or multiple power means; congruously connected thereto horizontal thrust devices. Integral to the vertical lift devices; pitch axis control devices situated at the exhaust orifices therein to vector said devices exhaust slip stream by a autonomous flight control system providing pitch stability. The autonomous flight control system providing continuously all flight control of the apparatus and said system being interfaced to a semiautonomous flight director device providing discrete flight direction function codes thereto.

Abstract: A missile has a body with a substantially circular nose opening therein, and a ceramic radome sized to cover the nose opening. A compliant metallic circular transition element is disposed structurally between the radome and the body. The transition element includes an elongated compliant arm region and a crossbar region positioned adjacent to the radome such that a lower margin surface of the radome rests against an upper side of the crossbar region. A brazed butt joint is formed between the lower margin surface of the radome and the upper side of the crossbar region of the transition element. A second brazed lap joint is formed between the vehicle body and the elongated compliant arm of the transition element.

Abstract: An element made of a reinforced low density heat protective material including an elastomer and/or a silicon resin matrix loaded with organic and/or inorganic components, wherein the reinforcement is formed of glass or ceramic thread sections or the like or organic materials fitted in the mass of the matrix along directions approximately orthogonal to at least one of the faces of the element and being flush, at least at one of their extremities, with at least one of the faces. The method for obtaining this element, includes, after molding to the general dimensions and shapes of the element with the aid of a loaded silicon matrix, placing the thread sections by stitching.

Abstract: An aircraft-luggage-bomb protection system has a blow-away plug (1) for each of a plurality luggage-storage units of a cargo section (4) of a commercial airplane (5). Luggage (3) is placed in explosion containers (2, 8, 20) that are positioned over the blow-away plugs. The explosion containers can be structured for select handling equipment such as luggage carts and pallets (23). The cargo sections are structured for quick and easy conversion between passenger use and airfreight use of planes. Procedural methods are provided.

Abstract: A safety device for luggage compartments is disclosed. The device comprises a barrier which substantially covers the opening in a luggage compartment. The barrier is attached to the luggage compartment above the opening and the barrier may be releasably fastened to the luggage compartment below the opening. When in place, the barrier is strong enough to prevent objects from falling out of the luggage compartment. The fastening means of the barrier may be released and a user can access the interior of the luggage compartment. An alternative embodiment is disclosed in which the luggage compartment comprises a slot for storing the barrier. When the barrier is not in use, the barrier may be inserted into the slot where it does not interfere with luggage. A spring means may be provided within the slot for automatically retracting the barrier. The barrier may also comprise a guide track and guide balls for keeping the barrier in its proper position when it is being withdrawn from or inserted into the slot.