Class / Patent application number | Description | Number of patent applications / Date published |
244121000 | Shields and other protective devices | 65 |
20090050741 | FIRE BARRIER FOR AN AIRCRAFT FUSELAGE - 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. | 02-26-2009 |
20090127392 | PROTECTION DEVICE - 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. | 05-21-2009 |
20090140097 | FLEXIBLE COMPOSITE MULTIPLE LAYER FIRE-RESISTANT INSULATION STRUCTURE - 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. | 06-04-2009 |
20090140098 | COMPONENT WITH CARBON NANOTUBES - 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. | 06-04-2009 |
20090189018 | Method for isolating a cabin wall of an aircraft or for cooling or heating of cabin air and a cabin wall suitable therefore - The present invention relates to a method for insulating an aircraft cabin | 07-30-2009 |
20090206202 | Energy absorbing structure for aircraft - 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. | 08-20-2009 |
20090212159 | Restraint System - 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. | 08-27-2009 |
20090242701 | PRESSURE BULKHEAD FOR AIRCRAFT - 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. | 10-01-2009 |
20090294588 | FUSELAGE STRUCTURE INCLUDING AN INTEGRATED FUSELAGE STANCHION - 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. | 12-03-2009 |
20100025533 | Electrically conductive protective liner and method of manufacture - 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. | 02-04-2010 |
20100059627 | Aircraft with a Rear Fuselage Protection Shield - The invention relates to an aircraft with a protection shield for the rear composite material, fuselage | 03-11-2010 |
20100090061 | FUSELAGE OF AN AIRCRAFT OR SPACECRAFT OF CRP/METAL HYBRID CONSTRUCTION WITH A METAL FRAMEWORK - 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. | 04-15-2010 |
20100096501 | Primary structure for aircraft of composite material with improved crash resistance and associated energy-absorbing structural element - 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. | 04-22-2010 |
20100148006 | IMPACT RESISTANT AIRCRAFT LEADING EDGE STRUCTURES AND AIRCRAFT INCLUDING THE SAME - Aircraft empennage structures have impact resistance satisfying transport aircraft certification requirements (for example, FAR part 25 and/or other international certification requirements). The structures may be specifically embodied in leading edge structures that are preferably in the form of one-piece components formed from fiber-reinforced composite materials (e.g., reinforcement fibers such as glass fibers, aramid fibers and/or carbon fibers embedded in a polymeric matrix such as an epoxy resin). The leading edge structures will most preferably include an arcuate skin and longitudinally extending internal reinforcement which is generally Y-shaped and includes a planar rib element and a pair of planar divergent reinforcement arms. The rib element may be positioned so as to be coplanar with a longitudinal bisecting plane of the leading edge structure. A forward end of the rib element may thus be integrally attached aft of an apical end of the skin, whereas an aft end of the rib may be integrally attached to each of the reinforcement arms. According to certain embodiments, rigidity and thus impact resistance may be facilitated by providing the apical end of the skin with a greater cross-sectional thickness as compared to the attachment ends of the skin. | 06-17-2010 |
20100155533 | COMPOSITE FORWARD PRESSURE BULKHEAD - A forward pressure bulkhead for aircraft includes an energy dissipating material layer, a metallic or nonmetallic inboard skin with a porous filler material positioned within said layers. The energy and load distribution layer redistributes and disperses energy of impacts and penetrations. The porous filler material is a material having ligaments that collapse resulting in a densification of the porous filler material in response to impact loading or a compression force sufficient to cause failure of the combined assembly. | 06-24-2010 |
20100155534 | Aircraft Baffle Seal - Aircraft systems having baffle seals with low coefficients of friction and methods of assembling aircraft systems are disclosed herein. In one embodiment, an aircraft system includes: (a) an aircraft baffle; (b) an aircraft cowl separated from the aircraft baffle by a gap, the aircraft cowl having a contact surface; and (c) a flexible aircraft baffle seal extending from the aircraft baffle to the aircraft cowl to seal the gap, the aircraft baffle seal having a contact side for contacting the contact surface of the aircraft cowl, the contact side having a kinetic coefficient of friction that is not more than 0.4, the aircraft baffle seal comprising an elastomer sheet and a laminate, the laminate being the contact side. | 06-24-2010 |
20100206987 | Fire Protection Space for Aircraft Passengers Provided with the Aid of Fuselage Skin of Fibre-Metal Laminates - 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-fibre reinforced aluminium laminate to form a safety zone for passengers in the event of a fire. | 08-19-2010 |
20100243807 | AIRCRAFT INSULATION SYSTEMS AND METHODS - In one of the embodiments of the disclosure, there is provided an aircraft insulation system and method for providing fire penetration resistance and/or thermal and acoustic protection. The aircraft insulation system comprises one or more insulation blankets, each having an inboard side and an outboard side. The aircraft insulation system further comprises a fire penetration resistant cover material having a heat seal adhesive, wherein the fire penetration resistant cover material covers the outboard side of the one or more insulation blankets. The aircraft insulation system further comprises an insulation cover film having a heat seal adhesive, wherein the insulation cover film covers the inboard side of the one or more insulation blankets. The aircraft insulation system further comprises a thermal heat seal that joins the fire penetration resistant cover material and the insulation cover film together to form a continuous insulation blanket assembly. | 09-30-2010 |
20100258673 | PRESSURE BULKHEAD MADE OF COMPOSITE MATERIAL FOR AN AIRCRAFT - The present invention relates to a curved rear pressure bulkhead ( | 10-14-2010 |
20100270430 | DEVICE AND METHOD FOR PROVIDING RADIATION OCCLUSION AND AERO-THERMAL PROTECTION - An extendable device for providing radiation occlusion and/or aero-thermal protection is disclosed. In various representative aspects, the present invention generally includes an extendable collar and a flexure configured to provide elastic properties (e.g., to facilitate stowage and/or deployment with respect to conformational disposition of the flexure). The flexure is coupled to a collar and is also coupled to the housing of an optical device. | 10-28-2010 |
20100276539 | Fire protection device for an aircraft or spacecraft - Provided is a fire protection device for an aircraft or spacecraft. The fire protection device is provided with a fireproof bulkhead and an adjusting device, by means of which the fireproof bulkhead can be adjusted from a ventilating position I into a screening position II. This may prevent a stream of smoke and heat from penetrating into the cabin when there is a fire underneath the fuselage. | 11-04-2010 |
20100276540 | AIRBAG SYSTEM FOR AIRCRAFT - The invention relates to an airbag system for aircraft, intended to protect crew and passengers. The system comprises: inflatable cushions; a supply of air from individual tanks, communal tanks and the aircraft APU; a connection to the landing gear and the altimeter; a manual switch; an approach and contact sensor enabling automatic activation; electric lines, electrovalves and air ducts. The system also includes a second version which is activated using electrochemical batteries which operate on the basis of sharp deceleration. | 11-04-2010 |
20100301165 | Structural Wing-Fuselage Component For Connecting Two Wings To A Fuselage Section Of An Aircraft - A structural wing-fuselage component for connecting two aerofoils to a fuselage section of an aircraft includes: a first wing shell component for the first wing and a second wing shell component for the second wing, with each component being made in a single piece and comprising a shell component on the wing side and a shell component on the fuselage side, where each shell component on the fuselage side comprises coupling parts and recesses in each case situated between the coupling parts, where in the installed state the coupling parts and the recesses of the shell component on the fuselage side for the first wing and of the shell component on the fuselage side for the second wing interlock, and where at least two coupling parts at their ends pointing away from the shell component on the wing side each comprises an extension part, a partially cylindrical fuselage shell component whose supporting rims include recesses which are engaged by the extension parts of the first wing shell components. | 12-02-2010 |
20110001009 | Transport aircraft, ballistic resistant and explosive containment system - Invention includes the concept and design necessary to protect transport aircraft from catastrophic failure as the result of an on board explosive or ballistic event. Concept is to protect the flight operation personnel and flight control systems from inoperable damage resulting from an on-board event defined by the FAA NPRM Docket Number 2006-26722, Notice Number 06-09 and subsequent FAA NPRM filings. | 01-06-2011 |
20110042513 | ENERGY-ABSORBING STRUCTURAL ELEMENT MADE OF A COMPOSITE MATERIAL AND AIRCRAFT FUSELAGE HAVING SAID ABSORBER - An aircraft fuselage has at least one reinforcement frame ( | 02-24-2011 |
20110049295 | REUSABLE ROTORCRAFT BUMPER, AND A ROTORCRAFT HAVING SUCH A BUMPER - A reusable bumper ( | 03-03-2011 |
20110095131 | ENERGY ABSORBING IMPACT BAND - An energy absorbing system may include a structure formed of an inner face sheet and an outer face sheet and having a core positioned therebetween. The structure may have a leading edge. An impact member formed of a plastically deformable material may be positioned with the inner face sheet within an area of the leading edge. The impact member may absorb energy from an impact of a projectile with the leading edge and redistributing the energy of the impact to the structure. | 04-28-2011 |
20110101164 | COMPLIANT CROWN PANEL FOR AN AIRCRAFT - An aircraft forward pressure bulkhead and an aircraft crown panel are described herein. The forward pressure bulkhead includes a malleable and deformable dome that is configured to “catch” foreign objects, such as birds. The dome is intentionally designed to deform in response to a foreign object strike that imparts at least a threshold amount of impact energy to the bulkhead. The dome is free of rigid stiffeners and non-deformable reinforcement members that would otherwise hinder the flexible characteristic of the dome. Practical embodiments of the bulkhead utilize fewer parts, are less heavy, and are less expensive than traditional bulkheads that utilize rigid stiffeners. The crown panel has similar compliant characteristics. The crown panel is designed to simultaneously deform and deflect in response to foreign object impacts such as birds and hail. The crown panel is formed from a monolithic one-piece material, such as aluminum, and various reinforcing features are integrally formed in the material. | 05-05-2011 |
20110121135 | GUARD FOR PROTECTING AN AIRCRAFT CARGO DOOR - This disclosure relates to a guard for protecting an aircraft cargo door during loading and unloading of cargo is provided, comprising a panel member adapted for covering at least a portion of an external skin of the cargo door, and one or more attachments for holding the panel member adjacent to the cargo door in use. Advantageously, the panel member is adapted to protect at least a portion of the external skin of the cargo door from being damaged during loading and unloading of cargo. In this respect, the panel member may be adapted to cover the portion of the external skin of the cargo door most prone to being damaged. | 05-26-2011 |
20110139931 | FIREPROOF BIDIRECTIONAL DECOMPRESSION PANEL - A fireproof, bi-directional decompression panel includes a frame member and a pressure relief panel member that is releasably retained to the frame member to removably cover a decompression vent opening of an aircraft partition, such as a sidewall of an aircraft cargo compartment. During a decompression event, the pressure relief panel member is released bi-directionally in either of two opposing directions from the frame member when a predetermined pressure differential exists across the partition. The decompression panel assembly is fire resistant, and has reduced weight and fewer parts than prior conventional decompression panel assemblies. | 06-16-2011 |
20110204184 | ELECTRICAL CONNECTOR - An aircraft pressure bulkhead electrical connector comprising a first connection terminal proximate at least one side of the electrical connector and a pressure seal arranged to maintain an applied air pressure differential across the electrical connector in use. | 08-25-2011 |
20110253839 | DOOR ENTRY HEAD GUARD - A method of protecting individuals entering or exiting an aircraft is provided. The method includes prior to the individuals entering or exiting the aircraft, removably attaching an entryway head guard to a frame of an entryway of the aircraft to protect the individuals entering or exiting the aircraft, the entryway head guard comprising a main body made of a protective material, wherein the main body has a contour that complements the frame of the aircraft passenger entryway such that the entryway head guard is configured to fit against the frame. The method further provides that after the individuals enter or exit the aircraft, removing the entryway head guard from the door of the aircraft. | 10-20-2011 |
20110290940 | PRESSURE BULKHEAD FOR PURPOSES OF ARRANGEMENT IN AN AIRCRAFT FUSELAGE - A pressure bulkhead for a fuselage of an aircraft is configured for bounding a fuselage interior relative to an external environment. The pressure bulkhead includes a flat skin configured to span a cross-section of the fuselage and having a cavity disposed at a core region of the skin. The core region is radially bounded by a ring element. A plurality of radial stiffeners extend on the skin and provide stabilization of the skin. Each radial stiffener is fixed at an end to the ring element. A reinforcement element extends over the ring element. | 12-01-2011 |
20120068015 | METHOD OF ACTIVATING PROTECTION MEANS FOR PROTECTING AN OCCUPANT OF AN AIRCRAFT, AND AN AIRCRAFT IMPLEMENTING SAID METHOD - A method of activating protection means ( | 03-22-2012 |
20120074261 | FUSELAGE ARRANGEMENT, AIRCRAFT OR SPACECRAFT AND METHOD - The present invention provides a fuselage arrangement for an aircraft or spacecraft, comprising: a skin portion which consists substantially of fibre composite material and/or of a fibre-composite/metal mixed material; a metal floor structure which is mounted on the skin portion; and a plurality of electrical system components which are interconnected in an electrically conductive manner by means of the floor structure. | 03-29-2012 |
20120228427 | PRESSURE FUSELAGE OF AN AIRCRAFT WITH DOME-SHAPED PRESSURE BULKHEAD - 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. | 09-13-2012 |
20130009009 | AIRBAG IN PRIVACY WALL - Embodiments of the present invention provide an airbag system designed to deploy from a privacy wall in a diagonal manner. | 01-10-2013 |
20130075525 | LOCKING MECHANISM FOR USE IN A DECOMPRESSION ARRANGEMENT - A locking mechanism, in particular suitable for use in a decompression arrangement, includes a pressure chamber surrounded by a delimiting wall, wherein at least a section of the pressure chamber delimiting wall is formed by an actuating element which is in a rest position when the pressure in the interior of the pressure chamber corresponds to the ambient pressure and moves into a differential pressure position when the pressure in the interior of the pressure chamber exceeds the ambient pressure by a predetermined differential value. The locking mechanism further includes a locking bar which is kept in a locked position when the actuating element is in its rest position and is movable into an unlocked position when the actuating element is in its differential pressure position. | 03-28-2013 |
20130087657 | COMPLIANT CROWN PANEL FOR AN AIRCRAFT - An aircraft forward pressure bulkhead and an aircraft crown panel are described herein. The forward pressure bulkhead includes a malleable and deformable dome that is configured to “catch” foreign objects, such as birds. The dome is intentionally designed to deform in response to a foreign object strike that imparts at least a threshold amount of impact energy to the bulkhead. The dome is free of rigid stiffeners and non-deformable reinforcement members that would otherwise hinder the flexible characteristic of the dome. Practical embodiments of the bulkhead utilize fewer parts, are less heavy, and are less expensive than traditional bulkheads that utilize rigid stiffeners. The crown panel has similar compliant characteristics. The crown panel is designed to simultaneously deform and deflect in response to foreign object impacts such as birds and hail. The crown panel is formed from a monolithic one-piece material, such as aluminum, and various reinforcing features are integrally formed in the material. | 04-11-2013 |
20130099057 | IMPACT RESISTANT AND DAMAGE TOLERANT AIRCRAFT FUSELAGE - Aircraft fuselage section ( | 04-25-2013 |
20130126674 | AIRCRAFT FUSELAGE STRUCTURE COMPRISING AN ENERGY ABSORBING DEVICE - An aircraft fuselage structure, includes a circumferential reinforcing frame ( | 05-23-2013 |
20130187002 | PROTECTIVE SHIELD AGAINST ICE IMPACTS ON AIRCRAFT - Protective shield against ice impacts on aircraft, wherein the shield comprises plies of composite material ( | 07-25-2013 |
20130206908 | Rotorcraft Front Windshield - According to one embodiment, a rotorcraft front windshield comprises a translucent material extending continuously between a point located twenty degrees above and forty degrees to the side of a design reference point and a point located thirty degrees below and forty degrees to the same side of the design reference point as the first point. | 08-15-2013 |
20130206909 | DECOMPRESSION UNIT - A decompression unit is suitable for use in a decompression opening of a wall element of an aircraft. The unit includes a panel which can be mounted via a frame in or over the decompression opening. The panel can be moved out of the frame at a predetermined differential pressure Δp in order to open the decompression opening. In order to form a decompression unit of as simple a design as possible and with an optimum response behavior, the panel is formed by at least one hardened prepreg layer with at least one separating joint that is filled with cured resin as a predetermined breaking point. The separating joint breaks when the predetermined differential pressure is exceeded. | 08-15-2013 |
20130214093 | RELEASABLE RADOME COVER - A protective cover ( | 08-22-2013 |
20130264423 | AIR VEHICLE WITH A SLIP PROTECTING AND GAS SEALING COMPOSITE FLOOR - An air vehicle with a slip protecting and gas sealing composite floor ( | 10-10-2013 |
20140001312 | PRIMARY FUSELAGE STRUCTURE FOR AIRCRAFT INCLUDING STRUTS CAPABLE OF EARLY FAILURE TO INCREASE THE ABSORPTION OF ENERGY IN THE EVENT OF A CRASH | 01-02-2014 |
20140027574 | AIRCRAFT AIRBAG SYSTEM - An airbag system assembly configured to be positioned in the interior of a vehicle that includes an aft wall configured to be positioned forward of a passenger seat and an airbag system. The aft wall includes front and aft surfaces and the aft wall includes a first flap that is formed by a plurality of weakness lines in at least the front surface thereof. The airbag system includes at least a first airbag module having a first airbag support plate with front and aft surfaces. The first airbag support plate is secured to the front surface of the aft wall, and the first airbag support plate includes a first airbag that is configured to deploy in the event of a crash condition and that is disposed on the aft surface of the first airbag support plate. The first airbag is positioned adjacent the first flap. | 01-30-2014 |
20140054419 | PRESSURIZED AIRPLANE FUSELAGE, COMPRISING A PRESSURE BULKHEAD - A pressurized aircraft fuselage includes a pressure bulkhead installed on a fuselage structure, which forms a barrier between an internal pressurized cabin area and an outside area, wherein the edge of the pressure bulkhead is circumferentially attached to the fuselage structure by fastening means, wherein the fastening means include a pair of ring-shaped attachment frames made of an open or hollow profile, which are disposed at each side of the pressure bulkhead respectively, in order to form a clamping connection for the pressure bulkhead towards the fuselage structure. | 02-27-2014 |
20140138484 | DOOR ENTRY HEAD GUARD - A method of protecting individuals entering or exiting an aircraft is provided. The method includes prior to the individuals entering or exiting the aircraft, removably attaching an entryway head guard to a frame of an entryway of the aircraft to protect the individuals entering or exiting the aircraft, the entryway head guard comprising a main body made of a protective material, wherein the main body has a contour that complements the frame of the aircraft passenger entryway such that the entryway head guard is configured to fit against the frame. The method further provides that after the individuals enter or exit the aircraft, removing the entryway head guard from the door of the aircraft. | 05-22-2014 |
20140158827 | Glare Shield Equipped With An Emergency Vision Apparatus - A glare shield equipped with an emergency vision apparatus comprises a glare shield in a cockpit and a compartment recessed into the glare shield. A blower is disposed within the compartment. An inflatable first enclosure made of airtight material and having an expanded form when deployed and a deflated form when not in use is connected to the blower with a tubular air passageway. The first enclosure when in the deflated form is stored within the compartment. First and second clear members are disposed at respective first and second ends of the enclosure to enable a user to see through the first enclosure when expanded and observe a source of information at a distal end of the first enclosure while smoke or other particulate matter is in the environment. A switch operably is associated with the blower to activate the blower and thereby inflate the first enclosure when deployed. | 06-12-2014 |
20140166809 | Improved Aircraft Windshield Assembly - An aircraft windshield assembly includes at least one window pane, a frame against which the pane bears, at least one flange for clamping the pane against the frame, and at least one cavity delimited between the pane, the frame and the flange. A member of profiled cross-section substantially fills the cavity and over at least part of its periphery has formations in relief in the form of flutes which with a facing surface define seal-forming baffles. | 06-19-2014 |
20140203143 | Front aircraft sealed bottom comprising recesses for housing cockpit equipment - A leaktight nose cone backplate for an aircraft having a first side oriented towards a radome zone intended to house a mobile antenna, and a second side opposite the first side and oriented towards a cockpit of the aircraft. The second side has at least one recess intended to receive at least one piece of cockpit equipment, each recess being partly delimited by a backplate structure forming a protrusion on the first side. | 07-24-2014 |
20140252170 | DEVICE FOR PROTECTING A ROTORCRAFT AGAINST A PYRAMID-SHAPED STRUCTURE FOR CARRYING A LOAD - A protection device ( | 09-11-2014 |
20140299712 | Thermal Barrier Coated RF Radomes - 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. | 10-09-2014 |
20150083862 | PRESSURIZED FUSELAGE OF AN AIRCRAFT, WITH A FUSELAGE STRUCTURE AND A PRESSURE BULKHEAD SPECIALLY MOUNTED THEREIN - 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. | 03-26-2015 |
20150336654 | AIRCRAFT BODY MOUNTED ENERGY ABSORBING RUB STRIP - An energy absorbing rub strip having a core material and a fairing positioned over the core material. The core material may be configured to buckle under the application of a predetermined amount of force and the fairing may be configured to be attached to a fuselage of an aircraft. The fairing may be made out of an abrasive-resistant material such as titanium or a nickel-based metal. The core material may be comprised of an aluminum honeycomb. The core material may be comprised of a dual density material. The length of the rub strip may extend beyond potential contact points on the fuselage during landing and takeoff. Upon a ground contact event, the thickness of deformed/buckled core material may be measured to determine if the ground contact event may have caused structural damage to the aircraft. | 11-26-2015 |
20150375844 | PANEL ASSEMBLY WITH CRUSH SECTION - A panel assembly that includes a front skin having a front surface, a back surface and at least one crush section portion, a core assembly that includes first, second, third, fourth and fifth layers laminated together, and at least a first crush section. The first, second, third, fourth and fifth layers each include a front surface, a back surface and at least one crush section portion. The front surface of the first layer of the core assembly includes a plurality of scores defined therein. The second layer includes a plurality of elongated voids defined therein and the fourth layer includes a plurality of elongated voids defined therein. | 12-31-2015 |
20160001735 | TUBULAR AIRBAG - Embodiments of the present invention provide an airbag system formed of a plurality of tubular structures. | 01-07-2016 |
20160052616 | AIRCRAFT WINDSHIELD AND METHOD FOR SUSPENDING AIRCRAFT WINDSHIELD - A row formed by a plurality of windshield fasteners, which fasten an outboard retainer, a panel, and an inboard retainer of a windshield of an aircraft, along a peripheral edge part of the windshield panel includes a first fastener, which is disposed at a predetermined position, and a pair of second fasteners, which is disposed in alignment with the row, one on each side of the first fastener. A plate, which is fastened along with the windshield panel by the first fastener and the pair of second fasteners, is disposed on the inboard retainer on the inside of the aircraft. The first fastener can be attached to or detached from a fixing nut, which is fixed on the plate, from the outside of the aircraft, and can be replaced with a suspension fastener on which a wire to be mounted on the windshield can be fitted. | 02-25-2016 |
20160052636 | AIRBAG ASSEMBLY FOR LEG FLAIL PROTECTION AND ASSOCIATED SYSTEMS AND METHODS - An airbag assembly for leg flail protection and associated systems and methods are described herein. An airbag system configured in accordance with an embodiment of the present technology can include, for example, a housing having a cavity and an opening in communication with the cavity, an airbag stowed within the cavity, and an inflator operably coupled to the airbag. The airbag can be configured to deploy through the opening of the housing during a crash or other significant dynamic event. The airbag can deploy outwardly from the side-facing seat to reduce occupant leg rotation during the crash or other significant dynamic event. The airbag can be pushed out of the housing before it is fully inflated. The airbag can be stowed and include folded first and second opposing side portions such that when the airbag is deployed, the portion nearest the occupant unfurls toward the occupant prior to the other portion farthest from the occupant unfurling in a direction away from the occupant. | 02-25-2016 |
20160059969 | GLARE SHIELD EQUIPPED WITH AN EMERGENCY VISION APPARATUS - A glare shield equipped with an emergency vision apparatus comprises a blower disposed within the glare shield; an inflatable first enclosure made of airtight material and having an expanded form when deployed and a deflated form when not in use; first and second clear members disposed at respective first and second ends of the inflatable first enclosure to enable a user to see through the inflatable first enclosure when expanded and observe a source of information at a distal end of the inflatable first enclosure while smoke or other particulate matter is in the environment; a switch operably associated with the blower to activate the blower and thereby inflate the inflatable first enclosure to the expanded form when the inflatable first enclosure is to be deployed; and a tubular passageway connecting the blower and the first enclosure. | 03-03-2016 |
20160096627 | ACTIVE POSITIONING AIRBAG ASSEMBLY AND ASSOCIATED SYSTEMS AND METHODS - Airbag assemblies and associated systems and methods for use in aircraft and other vehicles are described herein that can provide crash protection for occupants seated in an upright position while not injuring or striking occupants in the brace position. An airbag system configured in accordance with an embodiment of the present technology can include an airbag configured to deploy through an opening of a housing during a crash event. The housing can be affixed to a seat or other interior portion (e.g., a fixed portion) of an aircraft forward of a passenger seat. The airbag can initially deploy in a direction away from an occupant in the seat and then move into position between a potential strike hazard and the occupant such that the airbag system can be used to protect occupants seated in an upright position while not injuring occupants in the brace position. | 04-07-2016 |
20160167793 | AIRBAG PROTECTION SYSTEM | 06-16-2016 |
20190144327 | TRANSPARENT ARTICLES AND METHODS OF MAKING TRANSPARENT ARTICLES | 05-16-2019 |