Abstract: An aircraft surface for use on composite structure. The detail surface includes a conductive foil, a conductive double pulled expanded screen, and an adhesive for joining the conductive foil and screen to a composite material. The conductive screen is layered between the conductive foil and composite structure, providing electrical contact between the foil and the composite structure.

Abstract: A ram wing vehicle comprises a main structure extending between a nose end and a tail end, including an aerodynamic lifting body having an aspect ratio less than approximately 1.0 and extending between a leading edge and a trailing edge. The ratio of the thickness of the lifting body intermediate the leading edge and the trailing edge to the length of the chord thereof is greater than approximately 1:8. A propulsion source is provided adjacent the nose end for generating an efflux and for directing the efflux beyond the tail end in a direction away from the nose end. A directional control mechanism is positioned adjacent the nose end for turning the vehicle about the yaw axis into a curve having a center and so vectoring the efflux from the propulsion source as to direct the efflux to the outside of the turn and the nose end toward the center of the curve.

Abstract: A missile having an improved dome mounting arrangement, and a method for mounting a sapphire dome to a titanium missile turret that provides for minimum surface deformation and environmental sealing of the dome. A sealing material such as silicone rubber compound that is capable of enduring high temperatures attained during high speed missile flight is employed. The missile has a body with a nose and the dome mounting arrangement is attached to the nose. The dome mounting arrangement comprises a turret secured to the nose, the dome, and a retainer ring attached to the turret for securing the dome to the turret. An annular gap is formed between an outer surface of the dome and an inner surface of the retainer ring. The silicone rubber compound is disposed in the annular gap and cured to seal the dome. A plurality of shims may be disposed between the dome and the turret in a radial gap formed therebetween.

Abstract: A cover and method for applying the cover unto the wing comprising a flexible material to cover the top surface of said wing, said material having a leading edge to cover the leading edge of said wing and a trailing edge to cover trailing edge of said wing; a first set of spaced apart attachment straps each said first attachment strap extending from said trailing edge of said cover under said wing for quick release attachment to said leading edge of said cover, so as to attach and quickly release said cover to said wing; a second set of spaced apart removal straps, each said straps extending from said leading edge of said cover over said wing for quick release attachment to said trailing edge of said cover so as to remove said cover from said leading edge to said trailing edge of said wing by pulling said removal straps.

Abstract: A carbon-fiber reinforced plastic sheet is excellent in tensile strength and modulus of elasticity, but defective in impact resistance and fracture toughness. To overcome the defect, two aramid fiber reinforced plastic sheets are adhered to the opposite surfaces of the carbon-fiber reinforced plastic sheet to thereby provide a laminated structure and the aramid fibers are skewed at angles of +30.degree. to +60.degree. with respect to the direction of an impact load. This arrangement exhibits an improved shock absorbing efficiency and eliminates surface distortion which would otherwise take place during lamination. Further, a shock-absorbing structure may be produced from combining a plurality of sheets assembled crosswise such that surfaces of the respective sheets lie parallel to the direction of the impact load, and a cutout recess and a bulged portion are formed at an end of at least one sheet adjacent an intersection of the structure.

Abstract: The invention relates to a mass transit method including a docking terminal where passengers are loaded onto a craft with integral passenger pod. The craft lifts vertically from the docking terminal until it reaches an appropriate commuting altitude within 1,000 feet of the ground at which time the craft will fly to a second docking terminal and vertically descend to the second terminal for unloading of passengers. The commuting routes are networked to create an urban-suburban-rural mass transit system. The utility area of the craft can be detached and replaced. For instance, a passenger pod can be interchanged with a cargo, an emergency medical service (rescue) or a military unit pod for an innovative and versatile means of transportation.

Abstract: An attenuated aircraft seat back assembly for use on an aircraft passenger seat of the type which includes a seat back frame with a front side and a rear side, the attenuated assembly comprising a mount assembly structured to be secured at the rear side of the seat back frame, preferably at an upper end thereof, and an impact absorbent, generally rigid material panel fixedly secured thereto. The mount assembly is structured to securely maintain the rigid material panel in a generally parallel orientation relative to the seat back frame, and spaced apart from the seat back frame by a predetermined distance.

Abstract: A radome structure having an integrally attached attaching structure for attachment to an aircraft is disclosed, the attaching structure being affixed to a rearward portion of the radome. The attaching structure preferably comprises, at least in part, a core material which is capable of strengthening the attaching structure, thereby making it stronger than the material from which the radome shell is fabricated.

Abstract: A composite laminate, an aircraft skin panel, an airfoil, an aircraft and a method of manufacturing such a composite laminate are provided. The laminate includes at least three layers, namely a first layer of fiber reinforced composite material, a second layer usually metallic and usually forming a surface of the component and a third layer of impact energy-absorbing material interposed between the first and second layers, wherein the second and third layers protect the first layer from impact damage. The method of manufacture involves placing all three layers, including a said third layer of foaming adhesive, in a closed mould and foaming the adhesive to form a component to shape.

Abstract: The invention relates to a system for removing the heat that is incident upon an aircraft, and especially a supersonic aircraft, during flight. The incident heat is generated by the constant heating effect of aerodynamic friction on the outer skin of the fuselage, by compression heating at the ram or stagnation point and stagnation edges of the aircraft fuselage, and by the heating of external air as it is compressed to cabin pressure. In the present system, the used cabin air is exhausted out of the cabin through a space between the cabin interior panels and the fuselage outer skin, where the airflow absorbs the heat incident through the outer skin and is heated to approximately the temperature of the outer skin. Next, the heated airflow is preferably first filtered through a filter and is then expanded and cooled through an expansion turbine. The output shaft of the turbine can drive a generator to recover useful electrical energy.

Abstract: The present invention relates to a method for three-dimensional flight control based generally upon measuring and comparing actual air pressures at or near various surfaces of an aircraft during flight. Sensors are provided for measuring air pressure acting on the aircraft surface. The method includes measuring air pressure differentials between two or more sensors to evaluate certain critical flight parameters, such as the actual lift being produced, the air direction and speed relative to the aircraft, the air density, and the aircraft position and trajectory. The actual and comparative data provide information about the present flight conditions and performance if the aircraft, such as whether there is ice formed or forming on the wings, the direction and approach of wind shear, whether a stall is approaching, etc. The information can be evaluated by a computer, the aircraft's automatic flight control system ("AFCS"), or flight crew so that appropriate flight control measures can be taken.

Abstract: An energy attenuation system for absorbing at least a portion of the force impulse imparted to an occupant of an aircraft during a crash. The energy attenuation system comprises a seat and an air bag module. The air bag module includes an air bag positioned and deployable below the seat. The air bag allows the seat and its occupant to move in the direction of the applied impact forces under a controlled stroking force. Accordingly, the occupant may be exposed to a force having a magnitude substantially less than the magnitude of the force on the aircraft.

Abstract: An aircraft fuselage insulation blanket of the flexible type including an insulator core (24), including a predetermined volume contained by a vented flexible blanket casing (26) having a vented plurality of seam joined tailored panels (30), in which the seams are hermetically sealed. The panels include a flexible encasement material (29), having at least direct sealing properties to form hermetic seals (33), including at least a flexible plastic barrier film (52). The casing (26) has at least one vent (34), attached to at least one hermetic joined gas flow adapter (36), to displace air and to be connected by gas flow connector (38) to a substantially inert gas pressure source (39), to inflate blanket (14). Pressure source (39) includes a modular control (37), by which the blanket can be regulated to a predetermined substantially positive pressure relative to the cabin compartment (10) atmosphere's pressure, to displace and to occlude moist air from the blanket.

Abstract: A heat shield for thermally insulating the leading edge of a wing of a spacecraft during ascent and reentry includes a plurality of rigid tiles. Each tile is formed with a pie-shaped element which interlocks with the complementarily-formed element of another tile. The combination of structure afforded by the pie-shaped elements substantially impedes hypersonic flow of any gases that might enter the gaps between tiles.

Abstract: A process and apparatus for bonding together two layers of dissimilar material, yielding a composite structure which is substantially stress-free at a selectable reference temperature and reference isostatic pressure, which includes providing a first layer and a second layer; determining a critical line for the first layer and second layer in a pressure-temperature plane wherein a location of the critical line depends on the selectable reference temperature and reference isostatic pressure and depends on coefficients of thermal expansion and bulk moduli material constants of the first layer and the second layer, wherein the critical line sets forth a plurality of temperature-pressure pairs at which the composite structure will be substantially stress-free; controlling a temperature and an isostatic pressure during bonding such that the temperature and the isostatic pressure represent a point on the critical line; bonding the first layer and the second layer at the temperature and the isostatic pressure; and r

Abstract: To enable intervention personnel to directly enter from the outside the flight deck or cockpit of an aircraft, e.g. in the case of an accident, it is proposed that a window (14) opening from the inside of the cockpit be transformed into an emergency exit accessible from the outside of the aircraft. For this purpose, addition takes place to the existing mechnisms of a handle (50) placed in a recess (52) opening to the outside, as well as manipulating mechanisms. These mechanisms consist of a first linkage acting on the bolts of the window (14) and a second linkage (72) acting by a roller (106) on a cam surface (108) formed on a lever (32) of the window displacement control mechanism.

Abstract: A helicopter safety system provides an increased likelihood of survivability without injury during "survivable" helicopter crashes. The system provides spinal compression for precompressing an operator's spine in response to a crash signal from a crash sensor. Also included is a strap tensioning device which tensions an inertia reel strap and thus restraining the operator's upper body more effectively in the helicopter seat. Preferably, the strap tensioning device is initiated simultaneously with the spinal compression. Also included are energy absorbers connected to the seat pan, for example, between the seat pan and the seat frame, and airbags connected to the harness. The harness also includes a cross coupling element to provide for a lateral support configuration.

Abstract: A ballistic shield (10) for mounting to an aircraft fuselage (14) is formed of lightweight, composite material and shaped to conform to the shape of the fuselage belly that when mounted creates a space (30) between the shield (10) and the belly (14) to enable energy-absorbing deflection of the shield (10). Compartments (36) formed in the shield midsection (24) receive removable inserts (44) that can be constructed of different ballistic-resistant materials to enable field modification of the shield (10) to meet a perceived threat level.

Abstract: A launch vehicle payload housing and assembly joint for a launch vehicle, the housing comprising a shroud having first and second shell sections, and a frusto-conical payload adapter mounted in the shroud. The shell sections are connected together to form a housing. A peripherally extending explosive seam and a pair of longitudinally extending explosive seams hold the shell sections together. Each seam comprises a plurality of seam elements which include a pair of brackets attached to opposed ends of those parts of the shell abutting the longitudinally and peripherally extending seams. The brackets are spaced from one another to define a cavity. The cavity accommodates a deformable tube which houses explosive material in the form of an explosive cord. Detonation of the explosive material causes the shell sections to separate from one another.

Abstract: A projectile includes a mechanism which allows the fin position to be reved after the projectile leaves the launch tube thus allowing the fins to have reversed leading edges, which avoids the costly weight of the one-piece design in the prior art, which is a parasitic weight that will result in a lower velocity, and consequently lower kinetic energy, from the same propellant charge. This mechanism also avoids having extra pieces falling from the muzzle and near the firing team or troops near the gun, and has the advantage of a simple, low-weight deployment mechanism which results in the least aerodynamic resistance after full deployment. The mechanism has at least one small winglet on each reversible fin which generates an aerodynamic lifting force to provide reversal of the fin after the projectile leaves the launch tube. These winglets are positioned and designed to cause the least increase in aerodynamic drag.

Abstract: A thrusting rail-joint assembly for joining and rapidly separating two host structures is disclosed. Each of the two host structures may include a fairing structure, and is connected to a latching member, which may include a rail segment. An outer latching member, having a first joining end and a first latching end, is secured to the first host structure at the first joining end. The outer latching member includes a number of latching arms at the first latching end. The latching arms extend from the outer latching member in a direction from the first joining end to the first latching end. An inner latching member has a second joining end and a second latching end. The inner latching member is secured to the second host structure at the second joining end, and has a number of recesses at the second latching end. The recesses are adapted to receive the latching arms when the outer latching member is latched onto the inner latching member.

Abstract: An 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 apparatus a) measures an actual differential pressure between the upper and lower lift surfaces for a given aircraft speed, b) transmits this actual differential pressure measurement to a computer, c) compares the actual differential pressure measurement with an optimal pressure differential for the same aircraft speed, and d) evaluates performance of the aircraft based on the result of the comparison. 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 hydrofoil comprising a flat vessel of aerodynamic profile which, together with small planes, produces an aerodynamic lift, and the broad base of the hull contains a set of flexible fins whose cross-sections reduce from relatively thick inner ends of relatively large cross-section to relative thin outer ends of relatively small cross-section, that are fixed at their thicker end, that are inclined toward the end opposite the forward movement of the vessel, constructed and arranged to meet the water at their large surfaces, and to generate a hydrodynamic lift, with air flow propulsion, by the, for example, propeller, turboprop, or turbofan type turbodrive engines in the upper part.

Abstract: A protective covering for a swim platform located on a boat is provided. The protective covering may be detachably attached over the top of a swim platform, such as those platforms which are located about the rear of boats or other marine craft. Use of the protective covering will prevent waterfowl or other animals from defecating, loitering or nesting on the swim platform. The covering includes a generally rectangular portion located intermediate a right wing portion and a left wing portion. A plurality of apertures designed to secure the covering to the swim platform are provided on the rectangular portion, right wing portion and left wing portion. Both the right wing and the left wing fold forming a right sidewall and a left sidewall. The sidewalls and rectangular portion form a hollow, generally triangular structure which is placed atop and resides in the area immediately atop the swim platform. The covering is securely attached to the swim platform by any of a variety of attachment means.

Abstract: An inflatable restraint is disclosed, and includes an elongated poncho having therein an air-tight bladder and a cervical aperture for insertion of the head of the individual. A front portion of the poncho is adapted for juxtaposition with a rear surface of a forward seat and a rear portion is adapted for juxtaposition with and between the back of the torso and a forward surface of a rearward seat when inflated. The front portion is longer than the rear portion and has a larger volumetric displacement when inflated and extends over the front torso and lower extremities of the individual. The rear portion extends over the back torso of the individual. An inflation means inflates the bladder and restrains the individual between the forward and rearward seats for protection of the individual during an emergency while traveling in a vehicle.

Abstract: A secondary heat shield is positioned within a heat shielding radome and spaced from the nose of the radome in order to protect an antenna against thermal radiation from the inner surface of the radome. The secondary heat shield can be a single unitary component integrally formed of a lightweight ceramic which can be easily fabricated in the desired shape and which maintains its shape. The secondary heat shield can be formed of a lightweight ceramic material having a dielectric constant at 17 GHz and 21.degree. C. in the range of about 1 to about 3.5, a thermal conductivity of less than 0.7 W/M-K, and a density at 21.degree. C. of less than 3.2 g/cc. The most preferred ceramic material has a dielectric constant at 17 GHz and 21.degree. C. in the range of about 1.01 to about 2.0, a thermal conductivity in the range of about 0.04 to about 0.08 W/M-K, and a density at 21.degree. C. of less than about 1.0 g/cc.

Abstract: A truss type extruded aluminum section (1) is formed of a pair of planar plates (2)(3) and ribs (4)(5)(6), wherein hollow portions (7)(8)(9) are formed within the section (1) by the ribs (4)(5)(6) and the planar plates (2)(3). Vibration-damping resin is provided on the inner surfaces of hollow portions (7)(8)(9), and particularly on the inner surface of the planar plate (3) and on a single surface of the inclined rib (4). With this arrangement, the vibration energy bending the planar plate (3) and the rib (4) is converted into a heat energy. In the case of manufacturing such truss type extruded aluminum vibration-damping section (1), for making easy the insertion of the vibration-damping resin in the hollow portion, the vibration-damping resin is stuck on a plastic film (11) to form a long planar body. The plastic film (11) serves as a cover or an adhesive.

Abstract: An insect abatement system prevents adhesion of insect debris to surfaces which must be kept substantially free of insect debris. An article is coated with an insect abatement coating comprising polyorganosiloxane with a Shore A hardness of less than 50 and a tensile strength of less than 4 MPa. A method for preventing the adhesion of insect debris to surfaces includes the step of applying an insect abatement coating to a surface which must be kept substantially free of insect debris.

Abstract: Insect debris is removed from or prevented from adhering to insect impingement areas of an aircraft, particularly on an inlet cowl of an engine, by heating the area to 180.degree.-500.degree. C. An apparatus comprising a means to bring hot air from the aircraft engine to a plenum contiguous to the insect impingement area provides for the heating of the insect impingement areas to the required temperatures. The plenum can include at least one tube with a plurality of holes contained in a cavity within the inlet cowl. It can also include an envelope with a plurality of holes on its surface contained in a cavity within the inlet cowl.

Abstract: A radome for protecting electromagnetic equipment includes a polyimide foam that preferably is a closed cell foam. The polyimide foam imparts improved impact and moisture resistance to the radome without adversely affecting electromagnetic transmission thereof.

Abstract: A missile engine inlet cover has an elongate air scoop having a rigid forward shell and a rearward attached flexible molded end piece. The missile engine inlet cover is held in place by the launch rail with the flexible molded end piece releasably inserted into or over the missile engine inlet. During missile launch, flow of air into the open end of the air scoop forces the air scoop to rotate rearward and dislodges the flexible molded end piece from the missile engine inlet to allow operation of the missile engine.

Abstract: A recline safety lock assembly to be secured to an aircraft passenger seat of the type including a reclining seat back portion, a seat foundation and at least one recline cylinder structured to permit reclining of the seat back portion. The recline safety lock assembly includes at least one lock plate having an upper mount portion to be secured to a side rail of the seat back portion, and an engagement end having a downwardly depending lip formed therein. Additionally, the assembly includes at least one lock pin having a main shaft with a transverse notch formed therein. The lock pin is rotatably and axially mounted adjacent the engagement end of the lock plate and is rotatable between a disengaged orientation and an engaged orientation. In the engaged orientation the transverse notch is in a generally upwardly angled orientation such that the lock pin engages the downwardly depending lip of the lock plate and rear reclining of the seat back portion relative to the seat foundation portion is prevented.

Abstract: The disclosed invention is a bulkhead mounted energy absorbing pad especially useful to protect the head of a passenger seated immediately aft of that bulkhead in a vehicle undergoing a severe frontal crash event. The energy absorbing structure of the pad is a thick panel of low strength aluminum foil honeycomb having its cells aligned essentially with the impact vector. Thin, protective and aesthetic cover sheets and protective edge closeout structure is disclosed.

Abstract: The present invention relates to a protective cover for an airplane nose-wheel fairing. The protective cover prevents a nose-wheel fairing from becoming cracked or scratched as an airplane tow bar is attached or removed from the nose-wheel strut.

Abstract: A ceramic material which is (1) ceramics based on monoclinic BaO.multidot.sub.2 O.sub.3 .multidot.2SiO.sub.2 ; (2) ceramics based on monoclinic SrO.multidot.Al.sub.2 O.sub.3 .multidot.2SiO.sub.2 ; or (3) ceramics based on monoclinic solid solution of BaO.multidot.Al.sub.2 O.sub.3 .multidot.2SiO.sub.2 and SrO.multidot.Al.sub.2 O.sub.3 .multidot.2SiO.sub.2.

Abstract: A craft for ground effect and aerodynamic flight has, in addition to the usual vertical and horizontal stabilizer(s), a primary, upper airfoil, a lower secondary airfoil and a pivotable flap. The upper surface of the primary airfoil forms the primary lifting surface for aerodynamic flight while the lower surface forms, at its anterior and, an air intake for the compressors powering the craft and, to the rear, the upper surface of a plenum for ground effect flight. The upper surface of the secondary airfoil forms the lower surface of the compressor air intake at its anterior end and a compressed air exhaust at its other end. The lower surface forms the anterior end of the plenum when the pivotable flap is in the down position. The pivotable flap is attached near the forward end of the lower surface of the secondary airfoil to block the flow of compressed gases out the front of the craft during landing and while in hovercraft mode. Preferred models have a vertical stabilizer forward of the cockpit.

Abstract: A passive intermodulation shield (10) for a spacecraft is made from a substrate (12) and a vacuum deposited aluminum layer (14) over the substrate (12). The substrate (12) can include a polyimide sheet such as Kapton. The vacuum deposited aluminum layer (14) has a thickness (16) to produce a surface resistivity which maintains both the inherent passive intermodulation generation and the passive intermodulation passthrough below a predetermined value. Preferably, the surface resistivity is selected between 10 ohms per square and 40 ohms per square. Spacecraft multilayer insulation blankets (30, 40, 50, 60) are formed by disposing the passive intermodulation shield (10) between a pair of outer layers.

Abstract: A guard shield is provided as a protective security device in the cockpit of an aircraft to prevent instruments in the aircraft control panel from being removed by thieves. The guard shield is formed of a flat, laterally expansive, rigid plate with a pair of parallel slots defined in its lower edge. The slots extend upwardly into the interior of the plate and terminate in blind ends. The slots are laterally spaced from each other a distance equal to the distance of the separation of the steering columns for the steering yokes utilized by the pilot and copilot. The guard shield is mounted so as to rest upon the steering columns with the steering columns residing at the upper extremities of the slots in the blind ends thereof. A locking mechanism is employed to hold the guard shield closely adjacent to the surface of the instrument control panel, so as to prevent the removal of instruments therefrom.

Abstract: A surface effect vehicle for traversing a water or ground surface is provided. The surface effect vehicle comprises an elongate body and forward and rear scoops, preferably having a large angle of attack inducing stall conditions on the scoops. Each scoop has an arched leading edge defining, in conjunction with the surface, a forwardly facing opening. Preferably, each scoop also has an opening with a fan mounted therein. Forward and rear skirts are movably mounted relative to the forward and rear scoops. Propulsion apparatus are provided for moving the surface effect vehicle across the surface. When the forward and rear skirts are placed in extended positions covering the forwardly facing openings and the front and rear fans are activated, the surface effect vehicle may be lifted relative to the surface to be traversed.

Abstract: A method and apparatus are disclosed for providing an aircraft thermal protection system for hypersonic cruise and space launch vehicles. A flexible outer skin formed from a metal super alloy is designed to flex and accommodate thermal growth in the vehicle structure. The flexible super alloy skin is made from a plurality of hexagonal shaped cups which are welded together at the edges in a honeycomb type of array with thermal expansion gaps provided between the outermost surfaces of the hexagonal cups. Gap covers extend across the thermal expansion gaps to reduce aerodynamic drag. The flexible outer skin extends over hexagonal shaped, high temperature ceramic blocks, which provide both an insulation layer and support for the outer skin. The flexible outer skin distributes airloads across various ones of the rigid ceramic blocks.

Abstract: An aircraft airbag module and an energy or impact absorbing and shock reducing control yoke are disclosed, the airbag module using non toxic compressed gas to provide either pyrotechnic or non-pyrotechnic inflation of an airbag independent of other aircraft operational systems. An airbag with one or more sections, when inflated, provides pilot protection without physically engaging the aircraft's control yoke, thus affording the possibility of continued aircraft control by the pilot. The aircraft control yoke includes a mechanically keyed and physically compressible section, as well as padding, thus providing the pilot with additional impact protection with or without airbag deployment. The airbag is retractable or releasable mounted so as to allow the airbag to be manually or automatically removed from the airbag module after an airbag inflation/deflation cycle.

Abstract: An airbag assembly is positioned relative to an aircraft control yoke in a manner to minimize the application of an undesired force to the control yoke when the airbag assembly is inflated. A disc-shaped airbag assembly is horizontally rod-supported from an aircraft's instrument panel so as to surround the aircraft's horizontally extending control yoke and so as to be independent mechanically thereof. The rods that support the airbag assembly may be spring biased to a quiescent position, and may then be of the telescoping type to accommodate full inward movement of the control yoke as the aircraft's pitch attitude is controlled.

Abstract: This invention, and the associated methods, relate to fighting fires from aircraft. The invention, and the associated methods, also relate to early detection of fires; delivering liquids (primarily fire retardant or water) in a timely and accurate manner for the suppression of fires; and performing those functions under conditions of smoke obscuration and darkness which currently inhibit or prohibit aerial fire fighting. The novel capabilities detailed in this patent also allow for useful functions not now performed by airtankers such as, but not limited to, search and rescue; disaster damage assessment and recovery; law enforcement; natural resource protection such as dispersant spraying on oil spills, and avalanche control.

Abstract: Airbags are positioned in a general aviation aircraft cockpit relative to a control yoke, a pilot, and a front seat passenger. Airbag actuation is controlled by a adaptive programmable controller such as a microcomputer. Airbag actuation is based upon information that the controller receives from multiple acceleration sensors. The outputs of the acceleration sensors are subjected to thresholding techniques, such as output signal weighting and/or majority voting. A programmable threshold is adaptively established for the controller based upon unique aircraft parameters, such as weight, altitude, angle of attack, ground and/or air speed, etc. The controller ignores all acceleration sensor inputs that do not meet this adaptive threshold. Thus, airbag actuation takes place only when a sufficient acceleration event occurs concurrently with the presence or absence of defined aircraft parameters that establish a proper threshold for the acceleration event.

Abstract: An energy absorbing structural unit is attached outside the fuselage belly of an aircraft having at least two decks arranged one over another. At least the lower deck, of which the floor is adjacent to the fuselage belly, includes passenger cabin compartments and/or service facilities. The energy absorbing structure is an energy absorbing structural unit (5) that is attached outside of the existing aircraft fuselage (2) approximately vertically below the passenger cabin compartment (9) and/or service facilities provided on the lower deck of the aircraft. The energy absorbing structural unit absorbs impact energy arising in a crash or emergency landing of the aircraft. Because impact energy is absorbed by the external structural unit rather than or in addition to the structure of the aircraft fuselage and air frame, it is possible to provide lower deck passenger cabin space that may be continuously occupied by passengers and crew even during the take-off and landing phases of a flight.

Abstract: A quick release coupling apparatus and method used to connect and quickly disengage a night vision assembly from a pilot's helmet. The quick release coupling apparatus includes a locking element disposed on a pilot's helmet. An aperture is disposed on the night vision assembly to be attached to the pilot's helmet. The locking element of the pilot's helmet is passed into the aperture of the night vision assembly wherein the locking element is engaged and retained by a collet. The collet is biased against the locking element by a wire that is wrapped around the collet. As such, the collet engages the locking element and prevents the locking element from being withdrawn out of the night vision assembly, thereby firmly joining the night vision assembly to the pilot's helmet.Springs or similar repelling elements are disposed between the night vision assembly and the pilot's helmet.

Abstract: The invention is a ballonet system for a lighter-than-air-vehicle, the vehicle having a lift producing gas bag and a longitudinal, vertical and lateral axis. In detail, the ballonet system includes a plurality of ballonets located within the gas bag positioned along the longitudinal axis and on each side of the vertical axis of the vehicle. Each of the ballonets include a flexible sheet joined at its periphery thereof to a portion of the wall of the gas bag. A ballonet pressurization system is coupled to each ballonet for pressurizing them with air that includes the portion of the wall of the gas bag forming the ballonet having a plurality of holes therethrough. A manifold having an inlet port is joined to the wall covering the holes therein and is adapted to diffuse the pressurized air entering therein.

Abstract: A low-density resin impregnated ceramic article advantageously employed as a structural ceramic ablator comprising a fired preform of ceramic fibers. The fibers of the ceramic preform are coated with an organic resin film. The organic resin can be a thermoplastic resin or a cured thermosetting resin. In one embodiment, the resin is uniformly distributed within the ceramic article. In a second embodiment, the resin is distributed so as to provide a density gradient along at least one direction of the ceramic article. The resin impregnated ceramic article is prepared by providing a fired preform of ceramic fibers; immersing the preform of ceramic fibers in a solution of a solvent and an organic resin infiltrant; and removing the solvent to form a resin film on the ceramic fibers.

Abstract: A system for protecting the strut and wing structure of an airplane from high temperatures proximate the exhaust nozzle end of a jet engine employs a set of outer spring metal fingers attached to the exhaust nozzle outer sleeve and which bear against the strut structure, and a second set of inner spring metal fingers, interleaved with the first, which close off interfinger slots in the first or outer set whereby to maintain firewall integrity. Hot gases are thereby prevented from passing forwardly into the strut structure and wing area so as to protect the same in the event of an engine fire.

Abstract: The thermal protection device is made up of a plurality of juxtaposed unit modules each comprising a fairing element provided with fixing tabs and thermal insulation integrated in the fairing element. The gap between neighboring fairing elements is limited to the minimum width necessary for accommodating thermal expansion thereof. The connection means which releasably connect the fixing tab to a primary structure to be protected comprise a ball fixed to the fixing tab in adjustable manner and capable of being locked in a corresponding socket of a retaining part fixed to the primary structure. The ball is locked in its socket by means of a bolt capable of being released by action exerted against a resilient return force.