Abstract: The present disclosure relates to the active initiation of incident energy-dissipating material from a structure surface coating as a counter measure response for the protection of a structure surface. The active initiation is triggered at a predetermined area or areas on a targeted structure surface in response to incident directed energy sensed on a target surface.

Abstract: A deployable shroud provides an aerodynamically smooth surface to minimize the drag otherwise experienced by blunt nose projectiles. The shroud comprises multiple petals mounted at the nose of the projectile that are released at a set time during flight. The deployment mechanism assembly of the shroud provides deployment of the petals without the generation of shock waves into the projectile and comprises a fusible link powered by a thermal source. The shroud assembly is self-powered and does not require energy input from the projectile.

Abstract: A window for a vehicle includes at least one transparent pane suspendable within a frame. The transparent pane comprises a deformable material. The transparent pane defines a first surface position h1 when not subjected to a pressure differential thereacross and a second surface position h2 when subject to the differential pressure thereacross. The first and second surface positions are defined with reference to an outside mold line. The first surface position h1 defines a reverse curvature with respect to the outside mold line. In response to the differential pressure ?P, the second surface position h2 includes bulging of the transparent pane by a predetermined distance ?h. The frame is constructed to be positioned within the vehicle such that the transparent pane presents a surface, when subjected to the pressure differential ?P, that is substantially consistent with the outside mold line of the vehicle.

Abstract: Methods and apparatus are provided for a blast attenuator having a container with an outer wall that defines a cavity in which a particulate media is disposed, and a stirring element disposed in and moveable relative to the container. At least a portion of the stirring element extends into the particulate media, wherein, in use, the particulate media provides resistance against movement of the stirring element relative to particulate media so as to attenuate the energy of a blast.

Abstract: Fabrics that have been treated to create superhydrophobic, oleophobic and/or ice-phobic performance are manufactured or assembled in specific conforming shapes so they can be positioned on or pulled over and around certain objects for the purpose of making those objects superhydrophobic, oleophobic and/or ice-phobic so they are self-cleaning, water proof, ice-resistant, oil-resistant, corrosion barriers, etc.

Abstract: An airbag module for protecting an occupant of a vehicle seat. The module includes an inflatable cushion and an inflator for providing inflation gas for the cushion. The cushion includes at least a first inflatable chamber and a second inflatable chamber. The inflatable cushion is configured so that the first inflatable chamber fully inflates prior to the second inflatable chamber becoming fully inflated. The second inflatable chamber is positioned to absorb energy resulting from movement of the head of the occupant, and the loft of the second inflatable chamber is greater than the loft of the first inflatable chamber.

Abstract: A stretchable mesh material extends across the opening of a cavity of the landing gear of an aircraft when the landing gear is in the deployed position. The mesh material alters the flow of air across the opening of the landing gear cavity and significantly reduces the amount of noise produced by the wheel well at low-to-mid frequencies.

Abstract: A turret airbag system is provided including a plurality of airbags disposed within the turret to protect an occupant of the turret from injury and/or ejection from the turret. Turret airbags may be configured in padding around a turret access opening, and/or as substantially cylindrical airbags that deploy between the occupant of the turret and a wall or exterior opening of the turret. In some examples, the turret airbag(s) may be integrated with a countermeasure system that deploys explosion countermeasures and activates the turret airbags based on sensor data and multiple thresholds that indicate a collision event, a rollover event and/or an explosion event.

Abstract: Blast absorbing structures and system for use in absorbing blast forces exerted on a floor of a personnel cabin of a vehicle, are disclosed. The blast absorbing flexing structure comprises a bottom section forming a floor of the cabin, a first side section and opposing second side section, each side section extending from the bottom section and including a plurality of steps along a length of the second side section. The steps flex in response to a blast force. In another embodiment, the blast absorbing expanding structure comprises a force abatement device forming a floor of the cabin, a cover plate having a plurality of slots arranged around a perimeter of the plate. The cover plate is movable between a neutral position and a blast force position to diminish the blast forces prior to the blast forces to reaching an occupant of the cabin.

Abstract: Structure mounted airbag assemblies and associated systems and methods are described herein. An airbag system configured in accordance with an embodiment of the present disclosure can include, for example, a housing having a cavity and an opening in communication with the cavity, an airbag assembly within the cavity, and an inflator operably coupled to the airbag assembly. The airbag assembly can include an airbag configured to deploy through the opening of the housing during a crash event. The airbag system can further include a door removably positioned across the opening and configured to move away from the opening during airbag deployment. The housing can be affixed to an interior portion of an aircraft, forward of and offset from an aircraft seat.

Abstract: A composite laminate for use on an external part of an aerospace vehicle has improved ultraviolet resistance and resistance to microcracking from thermal cycling. The laminate comprises a nanoreinforcement film, a support veil, and a composite layer. The laminate also can have a lightning strike protection layer and an external paint and primer. The nanoreinforcement film can comprise carbon nanomaterial and a polymer resin, and the composite layer has one or more layers of a reinforcement and a polymer resin. The carbon nanomaterial can be carbon nanofibers, and the nanoreinforcement film can have an areal weight of less than about 100 g/m2. The carbon nanomaterial can also comprise carbon nanofibers and carbon nanotubes.

Abstract: A fully differential microelectromechanical system (MEMS) accelerometer configured to measure Z-axis acceleration is disclosed. This may avoid some of the disadvantages in traditional capacitive sensing architectures—for example, less sensitivity, low noise suppression, and low SNR, due to Brownian noise. In one embodiment, the accelerometer comprises three silicon wafers, fabricated with electrodes forming capacitors in a fully differential capacitive architecture. These electrodes may be isolated on a layer of silicon dioxide. In some embodiments, the accelerometer also includes silicon dioxide layers, piezoelectric structures, getter layers, bonding pads, bonding spacers, and force feedback electrodes, which may apply a force to the proof mass region. Fully differential MEMS accelerometers may be used in geophysical surveys, e.g., for seismic sensing or acoustic positioning.

Abstract: A mounting system for a fire detection system for a turbofan engine propulsion system is provided to mount fire detection sensors on the inner fixed structure (IFS) of the nacelle. The mounting system mounts to an inner, engine facing surface of the IFS. Two IFS halves cooperate to form a substantially enclosed space around an engine core. The mounting system includes part of a fastening system mounted to the IFS, and an orientation clip mounted to a thermal blanket. Brackets for mounting the fire detection system sensing wires are positioned on the orientation clip, and the fastening system fixes the bracket to the IFS and traps the thermal blanket therebetween.

Abstract: An aircraft nose structure comprising frames (2, 4, 6), a lower windshield frame member (12) and an upper windshield frame member (14) which are adapted to receive a windshield. The lower windshield frame member (12) has an arcuate shape with two branches which are connected together by a tie-rod (26).

Abstract: A method for providing dynamic security hardening of selected aircraft functions includes: a) monitoring sequences of real-time security events for at least one aircraft function; b) accessing a database storing a plurality of sequences of attack events indicative of an attack of the at least one aircraft function; c) probabilistically inferring, by at least one processor, the location and progression of an attack represented within the database by utilizing the sequences of real-time security events; and d) activating at least one countermeasure in response to an inferred location and progression of an attack.

Abstract: In order to provide a firewall that is capable of preventing flame passage through a through-hole without any sealant in a connecting part of a component in which a fastener through-hole is formed, a firewall 50 is provided which can prevent a flame from leaking out of the connecting part which connects a first member 51 to a second member 55, particularly through the fastener through-hole TH defined therein. In the firewall 50, the connecting part is a part of a fire-protection chamber 52. As sealing pieces 51d and 51e which also constitute a part of the fire-protection chamber 52 are in contact with each other, the flame is unable to enter into a closed space CA. Thus, the flame would not reach the connecting part, thereby preventing the flame from leaking out of the firewall 50 to the outside of a nacelle 23.

Abstract: A glazing unit is provided in which a two part bush is provided such that relative movement between a fastener, a glazing component and a wing skin is permitted, thus avoiding stress concentrations and lowering risk of damage in use.

Abstract: Nanostructured photonic materials and associated components for use in devices and systems operating at ultraviolet (UV), extreme ultraviolet (EUV), and/or soft Xray wavelengths are described. Such a material may be fabricated with nanoscale features tailored for a selected wavelength range, such as at particular UV, EUV, or soft Xray wavelengths or wavelength ranges. Such a material may be used to make components such as mirrors, lenses or other optics, panels, lightsources, masks, photoresists, or other components for use in applications such as lithography, wafer patterning, biomedical applications, or other applications.

Abstract: The different advantageous embodiments comprise an apparatus comprising an airbag. The airbag is configured to inflate into a configuration that covers a region around a seat in which a top of a head, a front of a head, upper body region, knees, and shins of a passenger in the seat is expected to be located when an event occurs in which the airbag is deployed.

Abstract: The present invention provides a fireproof bulkhead, having a highly porous structure with an intumescent coating, the highly porous structure being formed as a reticulated foam or as a highly porous pimple or nub structure.

Abstract: A primary fuselage structure for an aircraft, including circumferential frames, a floor structure having lateral ends connected to the circumferential frames, at least one strut supporting the floor structure and including a lower end fixed on a circumferential frame and an upper end fixed on the floor structure, and at least one failure-initiating element associated with the strut, including a first arrangement for fastening the strut to a circumferential frame, at a distance from the lower end of the strut, as well as a second arrangement for attaching the circumferential frame to the strut, away from the ends of the strut. A fuselage segment and aircraft, such as an airplane, including the primary fuselage structure are also provided.

Abstract: A sealing assembly is provided in an airframe of aircraft. The sealing assembly includes, but is not limited to a resilient and yet stiff enough bellows body that is attachable to the fuselage of the aircraft and is further attachable to a center wing box of the aircraft. The sealing assembly seals off a gap between the fuselage and the center wing box so as to allow maintaining pressure in the fuselage if the fuselage is pressurized. The bellows body is a composite and is designed to sustain exposure to tear and wear and exposure to a high and low temperatures as well as exposure to chemicals used during operation of the aircraft.

Abstract: A protected firing platform protection system protects personnel from contact with the protected firing platform. In an embodiment, the protected firing platform protection system is adapted for use with a protected firing platform of a military vehicle. The protected firing platform protection system includes a blanket. The blanket has a carrier and a protective insert. The carrier has an interior. The protective insert is disposed in the interior. The blanket is attached to the protected firing platform.

Abstract: The reusable energy absorbing lab seat 10 includes a seat bucket for holding an anthropomorphic test device, a seat support structure, an energy absorbing system, a false floor structure, and a fail-safe system. The seat support structure is for securing the seat bucket to a sled that corresponds to a horizontal accelerator. The energy absorbing system is for absorbing energy imposed by the horizontal accelerator on the seat bucket and the anthropomorphic test device. The false floor structure is for simulating a real floor of a vehicle or aircraft. The fail-safe system is for reducing damage to the reusable energy absorbing seat, the anthropomorphic test device, and lab facilities in case the energy absorbing system fails.

Abstract: A device for creating an individually delimited zone of a passenger cabin in a mode of transport for at least one passenger seat includes a modular cabin element that has been attached in a positionally variable manner to stationary guide rails of the passenger seat by way of quick-release fasteners. Associated with this cabin element is an extendable and affixable privacy screen roller blind that forms a flexible dividing element, which privacy screen roller blind extends from the underside of the hatrack or the PSU panel or the ceiling arrangement, and in the lateral region in addition the sidewall lining of the passenger cabin, to the modular cabin element, and by way of which privacy screen roller blind an individually delimited zone can be implemented.

Abstract: A rocket is provided and includes booster stages at a rear of the nose cone, the booster stages being configured for propelling the nose cone in a propulsion direction and a divert control system housed entirely in the nose cone for controlling an orientation of the propulsion direction.

Abstract: The invention relates to an aircraft protection device for protecting potentially exposed aircraft structures from direct impacts and a method of protecting an exposed edge of an aircraft component. The method includes the steps of winding filament around a foam core to create an impact protection device. A portion of the filament winding and foam core is removed from the impact protection device to create a receiving section whereby the receiving section is configured to correspond to and receive the exposed edge of the aircraft component. The impact protection device is secured to the exposed edge of the aircraft component such that the exposed edge is received in the receiving portion of the impact protection device.

Abstract: A pressurized fuselage of an aircraft includes a fuselage structure and a pressure bulkhead mounted therein for forming a fuselage-internal pressure region. The pressure bulkhead is attached on the edge region, by way of mounting means, to the inside of the fuselage structure. The mounting means comprise at least one pivoting socket arrangement, arranged on the edge side of the pressure bulkhead, which edge side faces away from the pressure region, and interacts with the fuselage structure, as well as a supporting frame element, arranged on the opposite edge side and supporting itself on the fuselage structure.

Abstract: A method for covering an end of a housing for an engine. A cover is positioned relative to the end of the housing for the engine. The cover comprises a structure, a flange comprised of a deformable material extending from the structure around a circumference of the structure, and a retaining feature configured to extend from a middle portion of the structure such that the retaining feature and the flange form a channel configured to receive the end of the housing. The cover is moved in a direction towards the end of the housing for the engine such that the retaining feature extends into an inlet of the engine through an opening of the housing to form an interference fit between the retaining feature and a portion of an interior surface of the housing.

Abstract: A pressure fuselage of an aircraft, which fuselage in longitudinal direction comprises several fuselage sections, wherein at least one rear dome-shaped pressure bulkhead is provided to form an aircraft-internal pressurized region, with a ring-shaped frame element profile being provided for radially outward attachment of said dome-shaped pressure bulkhead to at least one fuselage section, wherein the frame element profile on the side of the dome-shaped pressure bulkhead comprises a U-shaped profile section whose first end-side limb is attached towards the back on the dome-shaped pressure bulkhead by way of connecting means, and whose elongated radially outward extending second limb establishes a connection to the at least one fuselage section in such a manner that it is possible for the connecting means to be installed solely from the aircraft-internal pressurized region.

Abstract: A protective cover (10) for an instrument dome (12) extending from a body (20) of a vehicle, such as a missile. The cover (10) includes multiple segments (14 and 16) having trailing ends (18) connectable to the body (20) at joints (22) that allow for rotational movement. The cover (10) further includes a releasable holder (26) that includes a retention device (28) that holds leading ends (24) of the segments (14 and 16) together, and a release mechanism (30) for causing the retention device (28) to release the leading ends (24). The joints (22) hold the trailing ends (18) of the segments (14 and 16) to the body (20) through a predetermined range of motion beyond which the segments (14 and 16) will be released to separate from the body (20) when the segments (14 and 16) rotate beyond the predetermined range.

Abstract: A safety device to separate personnel from landing gear tires which incorporates a clamping collar configured to wrap around a landing gear post. A support frame extends outward from the clamping collar and defines a perimeter around the landing gear. A mesh skirt extends downward from the support frame.

Abstract: The present invention provides poly(ureaurethane)s including a reaction product of components comprising: (a) at least one isocyanate functional ureaurethane prepolymer comprising the reaction product of: (1) at least one isocyanate functional urethane prepolymer comprising the reaction product of: (i) a first amount of at least one polyisocyanate; and (ii) a first amount of at least one branched polyol; and (2) water, to form an isocyanate functional ureaurethane prepolymer; and (b) a second amount of at least one polyisocyanate and a second amount of at least one branched polyol; compositions, coatings and articles made therefrom and methods of making the same.

Abstract: A pressure bulkhead may include a bulkhead wall having a radially inner disk and a radially outer compression ring, the outer compression ring being reinforced to balance meridional and hoop stresses sustained by the bulkhead wall in response to a pressure differential across the pressure bulkhead; and the radially inner disk being unitary with the outer compression ring and being made of the same material as the outer compression ring.

Abstract: This invention provides a fuselage of an aircraft or space vehicle with a fuselage section having an outer skin, wherein at least the outer skin of the fuselage section consists of a glass-fiber reinforced aluminum laminate to form a safety zone for passengers in the event of a fire.

Abstract: An engine debris guard for preventing tyre propelled debris striking an aircraft engine, the debris guard comprising a guard bar pivotably connected to an aircraft main landing gear having at least one wheel and tyre assembly, the guard bar being arranged to be movable between a first position and a second position wherein in the first position the guard bar extends laterally across the wheel and tyre assembly to intersect the possible trajectories between the wheel and tyre assembly and an engine of the aircraft of any tyre propelled debris.

Abstract: A low cost, lightweight frangible wing slot seal can be applied to a guidance wing slot of a folding fin aerial rocket or missile, providing a barrier against exposure of internal missile components to external contaminants, while allowing unhindered deployment of missile guidance wings simply by bursting through the seals. The simple design is nearly foolproof, and has no impact the likelihood of weapon failure. The seal is a flexible sheet which is sufficiently thin so as not to exceed the required volume envelope of the missile. The sheet includes a burst seam, which is breached when impacted by the leading edge of a deploying wing. No additional wing deployment force is required, and after deployment the seal has minimal impact on the aerodynamic performance of the wing.

Abstract: An emergency vision apparatus for providing an operator in a station visual access to information during a vision-obscuring emergency, comprises an expandable first enclosure filled with clear air, the first enclosure having front and rear transparent panels to allow an operator visual access through the first enclosure to a first source of information disposed in front of the front panel; an expandable second enclosure filled with clear air, the second enclosure having a rear panel and a transparent front panel for being disposed in proximity to a second source of information; a first camera disposed at the rear panel of the second enclosure, the camera being directed toward the front panel to image the second source of information through the second enclosure front panel; and a first display operably connected to the camera, the display being operably associated with the first enclosure to be visible to the operator through the first enclosure rear panel.

Abstract: The present invention relates to an aircraft (1) provided with at least one rotary element (10) provided with blades (11) liable to come into contact with a liquid surface (100) on ditching, said aircraft including a buoyancy system. The aircraft includes a fairing (15) surrounding at least part of said rotary element (10), the fairing (15) including an inflatable emergency float (20) of the buoyancy system for preventing said blades (11) from coming into contact with the liquid surface when in an inflated position.

Abstract: A vibration isolator includes a base plate having a first attachment feature that enables attachment of the isolator to a first surface, the isolator further including a second attachment feature permitting attachment to a second surface. A spring section disposed between the base plate and the second attachment feature has a first radiused section and a second radiused section, each of the first and second radiused sections being formed in opposing directions on a continuous spring portion intermediate to the base plate and second attachment feature and in which the spring section provides noise attenuation and isolation between the first and second surfaces.

Abstract: An insulation package is provided for insulating a cabin of a vehicle that includes, but is not limited to at least one wrapping foil and at least one core layer of an insulation material. The wrapping foil envelopes the core layer at least in some regions and includes, but is not limited to at least one opening for feeding-through a holding element. On the wrapping foil a fastening element is arranged that is designed to establish a mechanical connection with the holding element fed through the opening. This can be a positive-locking or a non-positive-locking connection. By integrating the fastening element in the insulation package, the expenditure for separate fasteners can be saved so that the installation time and the different components can be reduced.

Abstract: An acoustic barrier structure can include a support structure that defines a plurality of cells, a weight attached to the support structure, and at least one resonant membrane covering one of the plurality of cells. The at least one resonant membrane can comprise at least one weight. The at least one resonant membrane can have an anti-resonant frequency and the support structure with the weight can provide wide frequency band gaps between odd resonance modes while suppressing structure-membrane coupled modes to enable the anti-resonance of the at least one resonant membrane.

Abstract: A structural component includes a fiber composite material structure having an outer surface and an electrically conductive metal profile disposed on the outer surface of the fiber composite material structure. The metal profile provides provide improved electrical conductivity of the structural component and component protection.

Abstract: A thermal protection system for a vehicle may include a substantially rigid, relatively thin outer aeroshell, a relatively low density insulation layer, and a resiliently compressible conformal layer. The vehicle may include a substructure. The aeroshell may be configured to be fastened to the substructure. The insulation layer may be disposed against the aeroshell. The conformal layer may be disposable against the insulation layer. The conformal layer may be compressively preloaded against the substructure when the aeroshell is fastened to the substructure.

Abstract: The present invention provides polyurethanes including a reaction product of components including: (a) an isocyanate functional urethane prepolymer comprising a reaction product of components including: (i) about 1 equivalent of at least one polyisocyanate; and (ii) about 0.1 to about 0.5 equivalents of at least one diol having 2 to 18 carbon atoms; and (b) about 0.05 to about 0.9 equivalents of at least one branched polyol having 4 to 18 carbon atoms and at least 3 hydroxyl groups; and (c) up to about 0.9 equivalents of at least one polyol different from branched polyol (b) and having 2 to 18 carbon atoms, wherein the reaction product components are essentially free of polyester polyol and polyether polyol; compositions, coatings and articles made therefrom and methods of making the same.

Abstract: An insulation device for an aircraft, comprising a blanket comprising a layer of insulation filling enclosed in a cover and having provision areas for the passage of aircraft components, these areas being devoid of insulation filling and being formed by a surface junction of two opposite faces of the cover inducing a recess in at least one face. The insulation device comprises an associated detachable complementary assembly to cover at least one of the provision areas, the assembly comprising a portion of insulation filling shaped to fit into the corresponding recess, and a retention arrangement for retaining this portion of filling. The retention arrangement is provided with a detachable arrangement for fixing the detachable complementary assembly on at least one face of the cover.

Abstract: A thermal barrier coated radio frequency (RF) radome is provided having a radio frequency (RF) radome with an exterior surface, an interior surface, a tip, and a base, wherein the RF radome is designed to transmit RF signals. A thermal barrier coating is applied to an exterior surface of the radome, wherein the thermal barrier coating has a dielectric constant of less than about 2.0, and further wherein the thermal barrier coating reduces a structure temperature of the RF radome by greater than 300 degrees Fahrenheit to enhance thermo-mechanical properties and performance of the RF radome.

Abstract: The present invention provides polyurethanes including a reaction product of components including: (a) an isocyanate functional urethane prepolymer comprising a reaction product of components including: (i) about 1 equivalent of at least one polyisocyanate; and (ii) about 0.1 to about 0.5 equivalents of at least one diol having 2 to 18 carbon atoms; and (b) about 0.05 to about 0.9 equivalents of at least one branched polyol having 4 to 18 carbon atoms and at least 3 hydroxyl groups; and (c) up to about 0.9 equivalents of at least one polyol different from branched polyol (b) and having 2 to 18 carbon atoms, wherein the reaction product components are essentially free of polyester polyol and polyether polyol; compositions, coatings and articles made therefrom and methods of making the same.

Abstract: A protection device (20) for protecting a fuselage (2) of a rotorcraft (1) against a pyramid-shaped structure (10) for carrying a load, which structure has a frame having a quadrilateral shape together with a first pair of two arms (12) and a second pair of two arms (14), each arm extending in elevation from the frame up towards an apex (16). The protection device includes a protective plate (21), a blade (30) secured to said protective plate (21) for exerting a force on said two arms of the first pair, and a chevron (40) provided with two branches connected to said protective plate (21) in order to tend to move the arms of said second pair transversely apart from each other.

Abstract: Polymerizable liquid compositions of the polyurethane type, consisting of two components (A) and (B), wherein component (A) contains at least one cyclo-aliphatic diisocyanate monomer or a mixture of one cyclo-aliphatic diisocyanate monomer and a pre-polymer obtained by reaction, in the presence of an acid phosphate ester catalyst, between said cyclo-aliphatic diisocyanate monomer and one or more polyols having two or more hydroxy 1 groups per molecule and a molecular weight ranging from 50 to 2,000 g/mole; the second component (B) contains one or more polyols having a molecular weight ranging from 50 to 2,000 g/mole and a functionality between 2 and 5; in the absence of polyalkoxylated tertiary diamines and organometallic catalysts, said components (A) and (B) being present in a weight ratio which varies from 1:1 to 2:1 and the process for the production of organic glass starting from polymerizable liquid compositions of the polyurethane type.