Abstract: The disclosed embodiments relate essentially to a primary structure of an aircraft fuselage that has at least a first strut linked at one end to a crossbeam and at the other end to a reinforcing frame. A second strut has one end fastened to the structure below the end of the first strut, and another end linked to the first strut through an intermediate sliding linkage. A deformable member is linked to the struts so that in case of a crash, the compressive forces press against the second strut, so that the end of the second strut slides along the first strut so as to stretch the deformable member longitudinally to absorb the shock.

Abstract: The invention is an unmanned flying helicopter aircraft platform (“aircraft platform”) that can be powered by either interchangeable electric motors or by fuel powered internal combustion engines. The aircraft platform is surrounded by a lightweight exoskeleton cage that protects the rotor blades from coming into contact with external objects. The aircraft platform uses a weight located on the bottom side of the aircraft platform that can be remotely moved to adjust the center of gravity in order to navigate in any direction. The aircraft platform has a place on its bottom side where attachments can be added or removed which allows the aircraft platform to be used for multiple different purposes. The aircraft platform can be flown and operated either remotely using a hand held control unit or it can be flown and operated by an onboard pilot located in the human carrying attachment.

Abstract: The present invention provides an inherently rigid fuselage of an aircraft or spacecraft comprising shell elements or fuselage barrels of CRP construction, wherein the shell elements or fuselage barrels each have an outer skin and an inner skin, which each at least partially or completely consist of a CRP material, wherein a composite core element is provided between the outer skin and the inner skin, and wherein the fuselage in the interior has a metal framework which is connected to the shell elements or fuselage barrels.

Abstract: A missile includes a radome-seeker airframe assembly that has a single-piece composite material forebody. The forebody is made of a high-temperature composite material that can withstand heat with little or no ablation. The forebody has a front part with an ogive shape and an aft part that has a cylindrical shape. The front part acts as a radome for a seeker located within the forebody. Patch antennas are attached to an inside surface of the cylindrical aft part. The aft part acts as a radome for the patch antennas, allowing signals to be sent and received by the patch antennas without a need for cutouts. A single seal may be used to seal the guidance system and seeker within the forebody, allowing the equipment to be hermetically sealed within the forebody.

Abstract: A radome system for fastening an aircraft radome, wherein the system includes a plurality of first fasteners each designed to put the radome into a position along two distinct axes contained in a plane approximately perpendicular to the longitudinal axis (L) of this fastener; and a plurality of second fasteners each designed to put the radome into a position along a single axis of a plane approximately perpendicular to the longitudinal axis (L) of this fastener.

Abstract: The invention relates to an aircraft with a protection shield for the rear composite material, fuselage 25) for conducting tail impact tests, in addition to a tail absorber, the shield (11) being formed by a plurality of pieces (21) joined to supports (23) fixed to the rear fuselage (25) behind the tail absorber (1), said pieces (21) having a laminar structure with an outer steel sheet (13), an inner composite sheet (17) and an intermediate high resistance silicon sheet (15).

Abstract: The tires that equip airplane wheels have elastomer treads from which a piece may detach and damage a zone of the airplane. Shredding means, situated between wheel and another part of the airplane, shred the piece of tread, which detaches from the tire and is projected onto the other part of the airplane, into several small pieces. These shredding means, such as a grid with blades that can cut the tread material, are arranged so as to disperse the pieces. A process reinforces the tolerance of an airplane to impacts of a detached piece of the tread, by shredding the piece into several small pieces between the instant when the piece is detached and the instant when the piece would have struck airplane.

Abstract: A jettisonable nosecone (10) for a missile is specified, which nosecone (10) is longitudinally split into at least two parts (15, 16) and is held together by detachable connecting structures, in which case the connecting structures are designed to actively move the at least two parts (15, 16) away from one another when released. A missile having a correspondingly designed nosecone (10) is also provided. A nosecone (10) of this type allows simple jettisoning during every flight phase of the missile, and is also suitable for retrofitting to an already existing missile.

Abstract: A protective liner includes a base layer that can be affixed to an aircraft canopy or other substrate, a conductive polymeric interlayer positioned over the base layer, and a conductive top layer containing a reactive organic salt, or a hygroscopic salt, positioned over the conductive polymeric interlayer. The substrate can also be treated with a multilayer stack (including a substrate base coat layer, a metal layer positioned over the substrate base layer, a metal oxide layer positioned over the metal layer, and a tie layer positioned over the metal oxide layer). The protective liner can be affixed to a pretreated substrate by lamination or other means to form an enhanced, multilayer stack having beneficial properties.

Abstract: Systems and methods for providing a structural adhesive film that includes a conductive scrim layer are disclosed. In one embodiment, a method for producing a structural adhesive film includes providing a first resin adhesive layer. The first resin adhesive layer is configured to bind to a first carbon fiber ply. The method also includes providing a second resin adhesive layer. The second adhesive layer is configured to bind to a second carbon fiber ply. The method also includes providing a conductive scrim that is embedded between the first resin adhesive layer and the second resin adhesive layer. In some embodiments, the conductive scrim is infused with resin adhesive.

Abstract: A fuselage structure for an aircraft or similar vehicle may include an upper fuselage portion and a lower fuselage portion. A floor may be disposed between the upper fuselage portion and the lower fuselage portion. At least one unitized stanchion may be disposed between the floor and the lower fuselage portion. The at least one unitized stanchion may form the only structural support between the floor and the lower fuselage portion without any vertical beams.

Abstract: Systems and methods are provided for regulating the pressure within an aircraft flight crew area during and/or after a decompression event. For example, an aircraft may include a flight crew area, at least one pressure sensor for detecting the pressure of the atmosphere within the flight crew area, and at least one regulated decompression panel that is operatively associated with the pressure sensor, for regulating the pressure within the flight crew area during and/or after a decompression event.

Abstract: A pressure bulkhead assembly adapted for installation in an aircraft fuselage includes a bulkhead web and a reinforcing structure. The bulkhead web has a first side facing the pressurized compartment and a second side opposite the first side. The reinforcing structure, which is formed from a series of primary beam members, secondary beam members, and connecting elements, is provided on the second side of the bulkhead web.

Abstract: In a preferred embodiment, a restraint system is described for restraining a standing occupant in a vehicle such as a plane or helicopter. The restraint system includes a webbing strap that winds and unwinds from a spool assembly. The spool assembly includes a trigger assembly that locks a spool from rotation, a manual release assembly for manually releasing the trigger assembly and lock, and an adjustable payout assembly that determines the maximum length that the webbing strap can be pulled out before stopping (i.e., the number of rotations of the spool). The trigger assembly can trigger the lock assembly from one or more sensors. Further, the trigger assembly can be arranged to automatically unlock after a triggering event, manually unlocked after a triggering event or a combination of the two for different sensors.

Abstract: Methods and systems for alerting airline personnel to potential aircraft data network security breaches is provided. The airline personnel includes at least one of flight crew personnel and maintenance crew personnel. The method includes detecting and categorizing potential aircraft data network security breaches, and recording said potential aircraft data network security breaches within an aircraft's existing crew alerting and maintenance data storage and reporting system.

Abstract: Energy absorbing structure disposed beneath the cargo area of an aircraft provides maximum energy absorption and structural strength using carbon fiber reinforced epoxy composites. The energy absorbing structure uses laminated stanchions having ply drop-offs to produce stable, progressive crushing of the stanchions during a wheels-up crash landing. Integrally formed flanges on the stanchions allow direct mounting of the stanchions on the structural members of the aircraft, without the need for specialized fittings.

Abstract: The invention relates to a door (8) designed to be inserted between a cockpit and a cabin of an aircraft, the door comprising a cockpit side (8a) and a cabin side (8b). According to the invention, the door comprises at least one trapdoor (22) capable of closing off a passageway (20) passing through the door and secondly being opened towards the cabin side, the door also comprising a locking/unlocking mechanism (30) of the trapdoor arranged on the cockpit side and that can automatically unlock the trapdoor when the difference between a cockpit pressure and a cabin pressure corresponding to the air pressures applied on the cockpit side and the cabin side of the door respectively is greater than a predetermined value.

Abstract: The present invention relates to a method for insulating an aircraft cabin 6 and for the cooling or heating of cabin air in an aircraft, respectively with the method comprising the steps of: introducing aircraft cabin air into an aircraft cabin wall 6; guiding this aircraft cabin air along a section of this aircraft cabin wall 6; and leading this aircraft cabin air away from the aircraft cabin wall 6.

Abstract: A window assembly is provided to prevent the migration of the window seal. The window assembly includes an outer window pane, an inner window pane and a seal. The outer window pane having a geometric feature configured to become parallel relative to another structure while the outer window pane rotates from a first position to a second position. The window assembly may further include a stiffening ring and a clamping ring which act to further secure the window seal in the desired position.

Abstract: An optical element mount is effective in high G environments to protect brittle optical elements in which tensile stresses are generated on surface S2 without degrading optical performance. A flexible spacer formed of a relatively low-stiffness material supports an optical element having a tapered outer periphery in an optical seat having a complementary tapered surface. When the optical assembly is exposed to the high G environment, the inertial loading drives the optical element in the aft direction into the flexible spacer and seat. This puts the optical element into a plate bending condition thereby inducing tensile stress on S2 which is at least partially offset by a compressive stress caused by the reaction force normal to the tapered interface. The stresses, both compressive and tensile, placed on the optical element in the high G environment can be very large.

Abstract: The present invention relates to a component, in particular in the field of aviation and spaceflight, having a resin matrix in which carbon nanotubes are embedded for high conductivity of the component.

Abstract: A flexible composite multiple layer fire-resistant insulation structure has a primary facing surface and a secondary facing surface. There is at least one dimensionally stable membrane having a primary membrane surface and a secondary membrane surface. At least a portion of the secondary facing surface is attached to the primary membrane surface. There is also at least one lofted insulative layer having a primary insulative surface and a secondary insulative surface. The at least one woven fabric facing layer may be formed of various materials, including amorphous silica glass and S-glass fiberglass. Different weaving patterns may be used to weave the facing layer. The facing layer may include a fire resistive treatment, which may in turn include a phosphate containing compound, and more particularly, may include dicalcium phosphate. In certain embodiments, multiple layers of the above are provided, and the structure may be enclosed in an abrasion resisting sheath.

Abstract: A device is provided for protecting a structure, such as an aircraft structure. The device includes, but is not limited to a skin made of a material comprising a multitude of alternating aluminium and glass-fibre reinforced plastic layers (e.g., GLARE), each being a few tenths of a millimetre in thickness. The skin is attachable to the structure so that a space is created between the structure and the skin, into which space the skin deforms when a force acts on it, so as to absorb the force acting on the skin, thereby minimizing and preferably preventing damage to the structure.

Abstract: An inexpensive, efficient and lightweight integrated small decoy system towed behind an aircraft to power an intense IR emitter for drawing in a missile with an IR sensitive guidance system away from vulnerable parts of a defended aircraft is combined with a system for simultaneously cloaking the aircraft with spectral bands of atmospherically scattered UV solar radiation reflected, and radiated from UV radiant sources mounted on the aircraft to defend against advanced MANPADS missiles with guidance systems sensitive to UV shadows cast by an aircraft in a background sky radiance of atmospherically scattered solar UV. Both the reflected and direct cloaking UV emittance may be spatially and/or temporally modulated to confuse an incoming missile. The UV aspect of this invention may also be combined with other C-MANPADS missiles, such as DIRCM, to provide additional defensive capability.

Abstract: A container, such as a standard aircraft unit load device, a truck trailer, a ship's cargo compartment, or the like, is fitted with a blast mitigating material located within the container. The blast mitigating material can be fitted to the container during manufacture, or an existing container can be retrofitted.

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: When a fire breaks out, air flows that promote the spread of fire may occur in the region between the load bay and the skin of the aircraft. According to one embodiment of the present invention, a fire barrier is disclosed that allows rapid decompression of the passenger cabin in the normal operating mode of the aircraft and prevents flashovers in case of a fire. In this case, the fire barrier may be arranged at different positions in the intermediate wall space of the aircraft.

Abstract: The invention is a thermal insulation tile for providing thermal protection of the external surface of a vehicle. In detail, the tile includes a rigid ceramic core having top and bottom surfaces, side surfaces and parallel front and rear surfaces at a 15 to 45 degree angle to said top surface. A cover completely surrounds the core and is bonded thereto. A plurality of rigid rods extends through the core and the cover and are bonded thereto. The rods are at an angle of between 10 and 30 degrees to the top surface of the core, with the angle thereof in an angular direction opposite to the front and rear surfaces of the core.

Abstract: A folding, retractable dome for protecting a feature, such as a docking mechanism, a hatch or other equipment at an exterior surface of a space vehicle, includes a plurality of arcuate ribs, each having opposite ends respectively pinioned at opposite sides of the feature at the surface of the vehicle for rotational movement about an axis of rotation extending through the opposite ends and through an arcuate path of revolution extending over the feature, and a flexible cover attached to each of the ribs such that, in a deployed configuration of the dome, in which adjacent ribs are rotated apart from each other at a maximum relative angle therebetween, the cover is stretched generally tangentially between the adjacent ribs to form a generally arcuate shield over the feature, and in a retracted position of the dome, in which adjacent ribs are rotated together at a minimum relative angle therebetween, the cover is collapsed to define folded pleats between the adjacent ribs.

Abstract: Disclosed is a system for shielding the interior of an aircraft cockpit. The system utilizes a number of individual shades that can be deployed over the various windshields that make up the canopy of an aircraft cockpit. Each shade has both a substantially flat, deployed configuration and a folded, stowed configuration. In the deployed configuration, the edges of the shade can be secured within the edges surrounding an associated canopy windshield. In this manner the shade is retained adjacent the windshield and is used to reflect sunlight and otherwise protect the internal components of the cockpit from direct sunlight. The shade can be deployed over a windshield in any orientation due to a resilient wire loop that is positioned within a peripheral edge of the shade. In the stowed configuration, the shade is folded over onto itself for storage and transport. The various details of the present invention, and the manner in which they inter-relate, and are described in greater detail hereinafter.

Abstract: An aircraft wing (12) comprising a structural casing (14) defining a leading edge, a fuel cell (16) within the structural casing (14), a deicer (18) having electrical lines which receive a supply of electrical power from an onboard power source, and a trip line (20). The trip line (20) is positioned to receive early contact upon impact of the wing by a bird or other foreign object and disruption of the trip line triggers termination of the supply of electrical power to the deicer (18).

Abstract: A window for a subsonic passenger aircraft that provide maximum optical visibility while minimizing the amount of exterior acoustic noise transmitted through the windows to the passenger cabin during flight of the aircraft includes at least one substantially transparent window pane having the shape of an ellipse. The ellipse has a major axis and a minor axis, and the major axis is about twice as long as the minor axis and is disposed generally perpendicular to the direction of flight of the aircraft. In one exemplary embodiment, the window has a height of about 20 inches and a transparent area of about 141 square inches, and includes a pair of substantially similar window panes disposed in a parallel, spaced-apart relationship circumscribed by a mounting bezel. A plurality of the windows are each mounted with the bezels in spaced-apart rows in each of the opposite sidewalls of the aircraft fuselage.

Abstract: A nose cover (10) for a dome (12) through which radiation can pass, for a missile, the nose cover having an outer structure (22) through which radiation can pass and which is aerodynamically better than a spherical shape, and having correction optics (24) through which radiation can pass and which can be placed in front of the dome (12). The nose cover (10) makes it possible to retrofit older missiles such that they have a greater range without this necessitating any modification of the existing structure of the missile.

Abstract: A mount for an aircraft secures insulation material to a structure of the aircraft in which a plate-shaped element and a connecting element that are implemented from a very heat-resistant material are provided. The remainder of the hanger may be implemented from plastic. Under the effect of strong heat, the plastic may melt. An insulation mat is nonetheless secured against falling down/detaching by the plate-shaped element, which is supported using the connecting element.

Abstract: A pressurized bulkhead or panel for an aircraft includes an energy absorbing skin that deforms in response to an object strike that imparts at least a threshold amount of impact energy to the skin. The skin may be configured as a dome or a lofted panel that is essentially free of rigid stiffeners and non-deformable reinforcement members that would otherwise hinder the flexible characteristics of the skin. The skin may be formed from a monolithic one-piece material, such as metal of composites, and may include various integrally formed reinforcing features.

Abstract: A composite panel structure for an aircraft includes a plurality of annular, hat-shaped frames disposed coaxially along a long axis of the aircraft in a spaced, parallel relationship, an inner skin having an inner surface bonded to an outer surface of the hat frames, a plurality of elongated, hat-shaped stringers disposed in a longitudinal direction along an outer surface of the inner skin in a spaced, parallel relationship, a solid or rigid foam offset bonded to an outer surface of each of the stringers, and an outer skin having an inner surface bonded to an upper surface of each of the offsets. The inner skin carries the loads of the structure and the outer skin defines an aerodynamic surface of the aircraft and provides impact and lighting protection. The frames, inner skin and stringers are formed on a single forming tool and cured and bonded with each other simultaneously.

Abstract: A partition for an aircraft is designed to separate a cargo part from a cockpit or a passenger compartment of this aircraft. The partition includes a cellular central structure in contact with a first external wall and a second external wall of this partition. The partition also includes several stiffener elements added onto at least one of the first and second external walls. The invention also relates to an aircraft including at least one such partition.

Abstract: Described herein is a computer design-aided shield for exposed surfaces on aircraft, a method for manufacture, and kits derived from collections of shields, each kit appropriate for use on a single aircraft type. The shield is contemplated for first use on general and corporate aviation aircraft. The kits are designed for convenient distribution to private pilots, and easy use by them on their aircraft. The shields can be transparent, or can bear lettering or insignia.

Abstract: A wire-strike system (1) including: a wire cutter including at least one pair of electrodes (5, 6), electrically insulated from each other and mountable upon an outer surface of an aircraft (2), said electrodes (5, 6) being connectable to a power source (11) capable of generating an electrical potential difference between the electrodes (5, 6) and in the event of a wire-strike, supplying a short circuit current flow through a portion of said wire connecting both electrodes (5, 6).

Abstract: Temperature and pressure sensors are protected from ice buildup by a in heat exchange relationship with a probe surrounding the sensors.

Abstract: An optically clear structural laminate includes a thermosetting resin, a silane coupling agent and a filler. The laminate has a high weight to strength ratio and is capable of optical transmission over a wide range of temperatures. The laminate has increased tensile strength and is capable of being easily formed into complex shaped components. The structural properties of the laminate make it useful as aircraft canopies and windows.

Abstract: An apparatus and method for thermal protection is provided. A thermal protection apparatus includes a porous layer attached to an inner structural member requiring thermal protection. The porous layer serves as both a cooling air plenum and a transpiring medium. The porous layer may include a low strength ceramic foam layer. Thermal protection may be achieved by flowing cooling air the length of the porous layer. The voids in the porous layer may be sized to less than 50 ?m, producing uniquely efficient thermal protection due to micro-fluidic effects in the air flowing through the layer. A semi-permeable layer may be attached to the outer surface of the porous layer. The semi-permeable layer may prevent erosion of the porous layer and may transform the porous layer into a plenum by making the majority of the cooling air flow the length of the porous layer before exiting through small holes drilled or punched through the semi-permeable layer.

Abstract: An aircraft includes a partition designed to separate a cargo part from a cockpit or a passenger compartment. The partition includes a corrugated structure, defining several corrugations with an approximately omega section extending along the direction of the height of the partition. The partition also includes one or several stiffener elements.

Abstract: A perforated heat shield (20) is formed of a single layer and is implemented to be positioned between an aircraft brake assembly (34) and wheel assembly (28) in order to effectively protect the wheel assembly (28) and adjacent components from excessive thermal energy generated by an operation of the brake assembly (34) and to promote the cooling of the brake assembly (34) by allowing a partial amount of the thermal energy to radiate to the wheel assembly (28) through apertures (22) provided in the heat shield (20).

Abstract: Provided is a method for providing fire shield protection to an aircraft auxiliary power unit, or portion thereof, or to other aircraft systems.

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: The invention relates to a method for improving the thermal comfort in passenger planes by means of a heat-reflecting coating with a low thermal emission coefficient, and airplanes and airplane parts bearing this coating. According to the invention, the coating is applied to the existing interior surfaces of the airplane cabin wall such that a passenger of the airplane may be in direct radiation exchange with this coating.

Abstract: A fire protection apparatus for an oil cooler in an aircraft auxiliary power unit compartment adapted to at least partially cover the oil cooler to thereby at least partially block flames from directly impinging the oil cooler in the event of a fire in the compartment. An associated means and method are also disclosed.

Abstract: A guided missile having a longitudinally extending airframe with a tip, a seeker head arranged in the tip and a window located in front of the seeker head for closing the airframe at the tip so as to protect the seeker head. A jettisonable protective cap consisting of at least two separable parts is attached to the airframe in front of the window for protection of the window.

Abstract: Modularized insulation blanket for thermal and/or acoustical insulation. The modularized insulation blanket has a cover formed of a distal layer and proximal layer in sealed mated relationship. The distal and proximal layers are sealed along longitudinal and latitudinal heat-sealed seams that define a plurality of modules. The heat-sealed seam may be creased so as to be foldable and/or perforated to provide a tear line. Within the modules are batting blocks. The blankets may be attached to surface structures such as the interior skin surface of an aircraft fuselage, pipes or other structures with retention systems. The blankets may be formed in an apparatus including a platen, heat seal rollers or heating sealing mechanisms, and edge sealers.