| Entries |
| Document | Title | Date |
|---|
| 20080230650 | Aircraft landing gear - The invention relates to an aircraft landing gear comprising a landing gear leg, wherein the landing gear leg or one or more parts of the landing gear leg consists partly or completely of a fiber composite material. | 09-25-2008 |
| 20080251637 | System for Maneuvering an Aircraft Landing Gear and Aircraft Comprising Same - The invention concerns a system for maneuvering an aircraft landing gear mounted in a landing gear box closed by a set of hatches, comprising: a general control unit of the landing gear box to trigger the different maneuvers, a control channel for the hatches ( | 10-16-2008 |
| 20080251638 | LANDING GEAR LEGS AND METHOD OF MAKING - An airplane gear leg that is strong, stiff, and capable of storing large amounts of energy and formed of a composite material that has first and second fiber materials. The first fiber material is very strong and flexible, allowing it to store a great deal of energy in a hard landing, and its fibers are oriented essentially parallel to the axis of the gear leg. The second fiber material is very stiff, providing the torsional rigidity necessary to avoid flutter, and its stiff fibers are laid at a large angle relative to the axis of the gear leg so their elastic limit is not exceeded during a hard landing. | 10-16-2008 |
| 20090008501 | LANDING GEAR - An aircraft landing gear door assembly includes a door, which is moveable to an open position, in which an aperture is exposed, the landing gear being able to be deployed through said aperture, and moveable to a closed position, in which the door is closed across the aperture. The door is arranged for rotational movement of a first type, in which the door rotates about an axis that is substantially parallel to the length of the aircraft, between the closed position and the open position. The door is also arranged for movement of a second type, different from the first type, in which the door rotates, about an axis that is substantially transverse to the length of the aircraft, to a position in which it acts as a fairing to reduce the noise caused by the landing gear or a part thereof. In one embodiment, the second type of movement is rotational movement about an axis that is substantially parallel to the door when in the closed position and the door forms a ramp type fairing. In another embodiment, the second type of movement is rotational movement about an axis that is substantially transverse to the door when in the closed position and the door forms a V-shaped fairing (when viewed from above) with an opposite door. | 01-08-2009 |
| 20090026312 | Landing Gear Assembly - A landing gear assembly comprises a wheel support housing rotatably connected to a support member, the wheel support housing containing an electrically powered motor operable to adjust the angular position of the wheel support housing relative to the support member. | 01-29-2009 |
| 20090026313 | Aircraft landing gear load sensor - An aircraft landing gear comprising a fibre optic load sensor for monitoring load in a component of the landing gear, such as an axle. The fibre optic cable is mounted on an inner surface of the component of the landing gear. Typically the fibre optic load sensor comprises one or more Bragg Grating sensors. | 01-29-2009 |
| 20090272844 | Method and Device for Supporting the Take-Off Rotation of an Aircraft - A method and a device for supporting the take-off rotation of an aircraft, which aircraft comprises on each side of the aircraft at least two main landing gear units, arranged one behind the other, which main landing gear units comprising wheels. For supporting the take-off rotation, in at least one rear pair of the main landing gear units the distance between the wheels of these rear main landing gear units, which wheels roll on the ground, and the fuselage, may actively be reduced. | 11-05-2009 |
| 20100006698 | Hybrid strut having metal and composite portions | 01-14-2010 |
| 20100252678 | GROUND SENSING SYSTEM - A ground sensing system for an aircraft attaches to the aircraft's landing gear to provide a ground touch indication. The ground sensing system includes a bracket, an upper arm, a lower arm, a roller and a sensor. The bracket is mounted to the landing gear while the upper arm is pivotally and biasly coupled to the bracket. The lower arm is pivotally and biasly coupled to the upper arm. The roller mounts to the lower arm and extends just slightly beneath a lowermost surface of the tire when the aircraft is airborne. The sensor is triggered once a portion of the upper arm has sufficiently entered the sensor's field of view, which occurs when the roller is urged upward by the ground during landing. | 10-07-2010 |
| 20100320317 | NEAR-BETA TITANIUM ALLOY FOR HIGH STRENGTH APPLICATIONS AND METHODS FOR MANUFACTURING THE SAME - A high strength near-beta titanium alloy including, in weight %, 5.3 to 5.7% aluminum, 4.8 to 5.2% vanadium, 0.7 to 0.9% iron, 4.6 to 5.3% molybdenum, 2.0 to 2.5% chromium, and 0.12 to 0.16% oxygen with balance titanium and incidental impurities is provided. An aviation system component comprising the high strength near-beta titanium alloy, and a method for the manufacture of a titanium alloy for use in high strength, deep hardenability, and excellent ductility applications are also provided. | 12-23-2010 |
| 20110163201 | Landing Gear for Spacecraft - A pivotal connection and a substantially rigid yet disruptable mechanical connection mount a respective foot pad on a distal end of each one of plural landing legs of a lander spacecraft. The mechanical connection includes at least one predetermined rated breaking point designed to break when the foot pad makes contact with a landing ground surface. At least two sensor elements, preferably electrical conductors or switches, are incorporated in the mechanical connection(s) of one or more foot pads. When the foot pad makes ground contact, the mechanical connection breaks at the rated breaking point(s), which also disrupts or actuates the sensor element(s), which thus provides a signal to an evaluating unit, which triggers the shut-down of at least one braking retrorocket or retrothruster. | 07-07-2011 |
| 20110174923 | PROTECTION PANEL AND LANDING GEAR MODULE COMPRISING IT - The invention relates to a protection panel ( | 07-21-2011 |
| 20110215196 | ENGINE DEBRIS GUARD - 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. | 09-08-2011 |
| 20110303787 | Load Indicator - An overload detecting assembly comprising a lateral probe ( | 12-15-2011 |
| 20110309192 | TORQUE LINK WITH SHIMMY DAMPER - A torque link includes a spring-damper system structurally incorporated into the design and functionality of the torque link. The spring portion may take the form of a structurally rigid beam while the damping portion may take the form of a damping mechanism or assembly. The damping mechanism is configured to damp out deformations in the beam and also configured to bottom out and become a structural tension/compression member when the load through the torque link exceeds a threshold load. The method damping may take a number of forms, such as, but not limited to, solid media damping, fluid damping with or without an orifice, a hydraulic or magnetic circuit, coulomb damping, etc. | 12-22-2011 |
| 20110309193 | AERO-ACOUSTIC OPTIMISATION METHOD FOR COMPLEX-SECTION MECHANICAL PARTS AND CORRESPONDING MECHANICAL PART AND LANDING GEAR - The invention is intended to reduce the drag caused by a complex-section part in an airflow, for example the landing gear of an aircraft, making it possible to optimise the lift/drag ratio and to reduce the aerodynamic noise by reducing the local noise source combined with a global optimisation of the aeroplane related to the reduction in drag. To do so, the invention provides for the shaping of the complex part, masking its form with a special casing. | 12-22-2011 |
| 20120012699 | SENSOR FOR MEASURING LARGE MECHANICAL STRAINS IN SHEAR OR LATERAL TRANSLATION - A capacitive strain sensor for sensing strain of a structure. The sensor includes a first section attached to the structure at a first location and a second section attached to the structure at a second location. The first section includes a capacitor plate electrically isolated from the structure and the second section includes two electrically isolated capacitive plates, both of the plates being electrically isolated from the structure. A flexible connector connects the first section to the second section. The capacitor plate of the first section is separated from the two capacitive plates of the second section by at least one capacitive gap. When strain is experienced by the structure, a change occurs in the capacitive gap due to relative motion between the first and second sections. The first section includes a core and the second section includes a ring that receives the core. | 01-19-2012 |
| 20120012700 | SYSTEMS AND METHODS FOR MEASURING ANGULAR MOTION - A system for monitoring landing gear position. An example rotation position sensor includes a hub mount that locks within a shaft of a joint, a first sensor attached to the hub mount, and a second sensor attached to the rotatably attached part that does not rotate. The hub mount includes a nut that has a partially tapered surface and a threaded cavity. The nut is secured within the shaft. The hub mount also includes a mounting unit that has a partially tapered surface that is in opposition to the partially tapered surface of the nut. A fastener secures the hub mount to the nut. In one example, the first sensor includes a magnetometer and the second sensor includes magnet(s). In another example, the first sensor includes inductor sensor(s) and the second sensor includes device(s) that causes a change in an inductance value of the inductor sensor(s) as the joint rotates. | 01-19-2012 |
| 20120012701 | SENSOR FOR MEASURING LARGE MECHANICAL STRAINS WITH FINE ADJUSTMENT DEVICE - A capacitive strain sensor for sensing strain of a structure. The sensor includes a first section attached to the structure at a first location and a second section attached to the structure at a second location. The first section includes a capacitor plate electrically isolated from the structure and the second section includes two electrically isolated capacitive plates, both of the plates being electrically isolated from the structure. A flexible connector connects the first section to the second section. The capacitor plate of the first section is separated from the two capacitive plates of the second section by at least one capacitive gap. When strain is experienced by the structure, a change occurs in the capacitive gap due to relative motion between the first and second sections. | 01-19-2012 |
| 20120043417 | CAPACITIVE SENSORS FOR MONITORING LOADS - A sensor for monitoring loads in a landing gear torque linkage includes a main pin having an axial interior bore defined therein. The main pin is configured and adapted to engage a torque link to a strut lug of a landing gear strut. A core pin is mounted axially within an interior bore of the main pin and is spaced radially inwardly from the interior bore for relative displacement with respect to the main pin. A capacitor is included having an inner capacitor plate mounted to the core pin. An outer capacitor plate is mounted to the main pin. Relative displacement of the core pin and the main pin due to loads acting on the torque link and strut lug results in relative displacement of the inner and outer capacitor plates. Signals can thereby be produced indicative of the loads acting on the torque link. | 02-23-2012 |
| 20120097792 | HYDRAULIC CIRCUIT FOR ACTUATING AN UNDERCARRIAGE, AND METHODS OF DEPLOYING AND RAISING AN UNDERCARRIAGE USING SUCH A CIRCUIT - A hydraulic circuit for actuating an undercarriage, the circuit comprising: a feed line for feeding fluid and a return line; at least one door selector connected to the feed and return lines, the selector feeding door service lines, including an opening line and a closing line for opening and closing the doors; at least one undercarriage selector connected to the feed and return lines, feeding undercarriage service lines including a deployment line and a raising line for deploying and raising the undercarriage; and a door unhooking line and an undercarriage unhooking line. The door unhooking line is connected to at least one undercarriage service line while the undercarriage unhooking line is connected to at least one door service line, the circuit also including means for connecting the door service lines together during a door opening stage, and means for connecting the undercarriage service lines together during an undercarriage deployment stage. | 04-26-2012 |
| 20120111998 | BEARING ASSEMBLY - A bearing assembly ( | 05-10-2012 |
| 20120132742 | QUICK RELEASE ASSEMBLY FOR AIRCRAFT LANDING GEAR - A torque link member for aircraft landing gear includes a first end for connecting to a lower portion or an upper portion of the aircraft landing gear and a second end for connecting to another torque link member. A locking pin is disposed on one of the upper portion, the lower portion, the first end or the second end. The locking pin is axially movable between an engaged position wherein the pin protrudes for interengagement with a cooperating aperture on the first end, the second end, the upper portion, the lower portion, or the second end of the other torque link member, and a disengaged position. The locking pin is biased toward the engaged position and movable against the biasing to the disengaged position. | 05-31-2012 |
| 20120153077 | LANDING SYSTEM FOR A BODY AND SPACE PROBE PROVIDED WITH SUCH A SYSTEM - A landing system of a body and a space probe provided with such a system for landing on a bearing ground. The landing system includes landing legs ( | 06-21-2012 |
| 20120181385 | NEAR-BETA TITANIUM ALLOY FOR HIGH STRENGTH APPLICATIONS AND METHODS FOR MANUFACTURING THE SAME - A high strength near-beta titanium alloy including, in weight %, 5.3 to 5.7% aluminum, 4.8 to 5.2% vanadium, 0.7 to 0.9% iron, 4.6 to 5.3% molybdenum, 2.0 to 2.5% chromium, and 0.12 to 0.16% oxygen with balance titanium and incidental impurities is provided. An aviation system component comprising the high strength near-beta titanium alloy, and a method for the manufacture of a titanium alloy for use in high strength, deep hardenability, and excellent ductility applications are also provided. | 07-19-2012 |
| 20120211600 | AIR-GROUND DETECTION SYSTEM FOR SEMI-LEVERED LANDING GEAR - A method and apparatus for air-ground detection. A truck beam of a semi-levered landing gear is mounted on a pivot pin. The truck beam is configured to rotate about the pivot pin between a toes down position and a toes up position. A positioning mechanism is connected to a locking mechanism that secures an angle of the truck beam in the toes up position. The locking mechanism is secured in a steady state and configured to change from the steady state to a locked state in response to an initial ground contact. A sensor is connected to the locking mechanism. The sensor is configured to detect a change from the steady state to the locked state. | 08-23-2012 |
| 20120241557 | HEAT SHIELD INSTALLATION FOR AIRCRAFT WHEEL TO IMPROVE CONVECTIVE COOLING OF AIRCRAFT BRAKE - Improved chin rings are disclosed, wherein a chin ring may comprise a substantially circular chin ring having an outer surface and a slot, a first radially spaced aperture in the chin ring on a first side of the slot, a second radially spaced aperture in the chin ring on a second side of the slot, a first louver disposed at least partially over the first radially spaced aperture, the first louver disposed at a first angle relative to the outer surface and a second louver disposed at least partially over the second radially spaced aperture. | 09-27-2012 |
| 20120241558 | Aircraft Landing Gear - Aircraft landing gear including at least one load bearing longitudinal structural element wherein said longitudinal structural element is hollow and is arranged to have at least one non-structural element located inside. | 09-27-2012 |
| 20120256050 | BOGIE STOP BLOCK - An aircraft landing gear assembly including a bogie beam, a landing gear strut having a first end arranged to be pivotally coupled to an aircraft and a second end pivotally coupled to the bogie beam, and a stop arranged to limit pivotal movement of the bogie beam relative to the landing gear strut, wherein the stop comprises at least one elongate member arranged to be deflectable in bending when the bogie beam reaches a pivotal limit. | 10-11-2012 |
| 20120292442 | Aircraft Landing Gear Including a Fairing - An aircraft landing gear including a fairing ( | 11-22-2012 |
| 20120298796 | VARIABLE SURFACE LANDING PLATFORM (VARSLAP) - In one embodiment, a variable surface landing platform (VARSLAP) includes a base for contacting a landing surface; at least 3 adjustable struts interconnected with the base, wherein each strut is bisected by a strut actuator-housing, and wherein the at least 3 adjustable struts are interconnected to a main body aerospace craft (MAC); a sensor array on the base; and an attitude determination and control system (ADCS). | 11-29-2012 |
| 20130009003 | TORQUE LINK WITH SHIMMY DAMPER - A torque link includes a spring-damper system structurally incorporated into the design and functionality of the torque link. The spring portion may take the form of a structurally rigid beam while the damping portion may take the form of a damping mechanism or assembly. The damping mechanism is configured to damp out deformations in the beam and also configured to bottom out and become a structural tension/compression member when the load through the torque link exceeds a threshold load. The method damping may take a number of forms, such as, but not limited to, solid media damping, fluid damping with or without an orifice, a hydraulic or magnetic circuit, coulomb damping, etc. | 01-10-2013 |
| 20130026289 | ENERGY ABSORPTION STRUCTURE - An object of the invention is to provide an energy absorption structure that can suppress the fall of an energy absorption member when a load is applied to the energy absorption structure. According to the energy absorption structure of the invention, when a load is applied to the energy absorption structure, the relative displacement between a first member and an energy absorption member is suppressed by a displacement suppressing member that connect the first member with the energy absorption member. Accordingly, the fall of the energy absorption member can be suppressed. | 01-31-2013 |
| 20130099052 | METHOD FOR ADJUSTING THE DOORS OF A LANDING GEAR BAY, AND ASSOCIATED DOOR - The aim of the invention is to allow the set of doors to be adjusted without increasing the number of landing gear retraction/extension manoeuvres, by incorporating a specific entrance in the fairing ( | 04-25-2013 |
| 20130119196 | Hydraulic Strut Assembly for Semi-Levered Landing Gear - A hydraulic strut assembly, for use in a semi-levered landing gear in an aircraft, comprising an actuator and a manifold associated with the actuator. The actuator comprises a housing, a first piston, a second piston, and a third piston. The first piston is positioned between outer and inner cylindrical structures of the housing. The outer and inner cylindrical structures and first piston form an outer chamber that receives a first fluid. The inner cylindrical structure, the first piston, and the second piston, which is nested within the first piston, form an inner chamber, which holds a second fluid comprising a gas. A volume of the inner chamber changes when at least one of the first and second pistons moves. The third piston is positioned between the outer cylindrical structure and the first piston. The first, second, and third pistons move in a direction parallel to an axis through the housing. | 05-16-2013 |
| 20130181090 | SHOCK ABSORBERS - Adjusting device ( | 07-18-2013 |
| 20130264417 | Aircraft Landing Gear Stop Pad - A stop pad ( | 10-10-2013 |
| 20130327889 | Landing Gear Bogie Beam With Jacking Dome - An aircraft landing gear assembly comprising a bogie beam ( | 12-12-2013 |
| 20140021296 | Attachment Bracket for Landing Gear - Attachment brackets are disclosed which are configured to be removably mounted on aircraft landing gear, e.g., by bolting the bracket to the landing gear. The attachment brackets may be used to secure skis, pontoons, or other landing equipment to the landing gear of the aircraft. In preferred implementations, the brackets are bolted on using existing factory drilled holes in the landing gear. | 01-23-2014 |
| 20140027570 | WRAPAROUND STRAIN GAGE ASSEMBLY FOR BRAKE ROD - An apparatus comprises a brake rod and a flexible dielectric membrane wrapped around the brake rod. The membrane has a plurality of substrate cutouts at precise locations for strain gage substrates. | 01-30-2014 |
| 20140084108 | AIRCRAFT LANDING GEAR - Aircraft landing gear including: a bogie beam coupled to a main strut; a first and second axles mounted on the bogie beam, each axle having a respective brake assembly and wheel assembly; and first and second stabilising arms mechanically coupling the first and second brake assemblies to respective first and second anchor points on the landing gear so as to react respective first and second brake torques generated as respective brake assembly applies a braking force to the respective wheel assembly. The first and second stabilising arms couple the respective first and second brake assemblies to the respective first and second anchor points such that the first and second brake torques result in both stabilising arms experiencing a tensile force or both stabilising arms experiencing a compressive force. | 03-27-2014 |
| 20140097293 | Airplane Shock Absorbing Suspension - A landing gear strut incorporating an oleo-pneumatic shock absorber with a bungee return spring. An oleo-pneumatic shock absorber is a device engineered for slowing down a moving mass. The shock absorber converts the kinetic energy of the impact into heat due to the friction of oil being driven through narrow orifices. The shock then recovers using air and or spring pressure. The recovery is governed by the flow rate of the fluid to the original reservoir. In the case of an aircraft this results in less bounce, shorter stop time, smoother overall ride, and safer landings. | 04-10-2014 |
| 20140131514 | NOSE LANDING GEAR ARRANGEMENT FOR AIRCRAFT AND METHOD OF ASSEMBLY - A nose landing gear arrangement for an aircraft and a method of assembling the nose landing gear arrangement are disclosed herein. The nose landing gear arrangement includes, but is not limited to, a wheel assembly, a shock strut extending upwards from the wheel assembly towards a fuselage of the aircraft, and a torque arm assembly coupled to the wheel assembly and to the shock strut. The torque arm assembly is configured to transmit torque to the wheel assembly. The torque arm assembly is disposed forward of the shock strut with respect to a direction of travel of the aircraft. | 05-15-2014 |
| 20140151499 | METHOD OF POSITIONING LANDING GEAR - A method of positioning landing gear of an airplane is provided that includes providing the landing gear including a shock strut, a truck beam operatively pivotally connected to the shock strut, first and second interconnected links operatively connected to the truck beam and a third link extending between the shock strut and the first and second links with the third link pivotally connected to the second link at a third pivot. When the landing gear is commanded to a lowered position, the third pivot is positioned in a first position to support a taxi mode, a take-off mode and a landing mode if the landing gear is operational and in a second position to support an alternate landing mode if the landing gear is not fully operational. When the landing gear is commanded to a raised position, the third pivot is in the second position to support a stow mode. | 06-05-2014 |
| 20140197274 | AIRCRAFT FUSELAGE - A fuselage for an airplane including a frame comprising an upper truss and a lower truss extending from a front end of the fuselage towards the rear end of the fuselage, wherein the lower truss comprises one or more forward box beams, a plurality of support rings attached to the upper truss and lower truss, a front bulkhead connected to a first end of the upper truss and lower truss, a main bulkhead connected to the upper truss and lower truss, a pressure vessel adapted to fit within the frame between the front bulkhead and main bulkhead, and a skin adapted to fit over the frame. | 07-17-2014 |
| 20140231584 | ANTI-LOFTING DEFLECTOR FOR AIRCRAFT LANDING GEAR - An anti-lofting deflector for landing gear having two wheels on an axle, the deflector comprising: | 08-21-2014 |
| 20140312171 | GAUGE - A gauge for indicating whether the oil level in an oleo-pneumatic shock absorber requires modification. The gauge comprises a substrate for positioning relative to the oleo-pneumatic shock absorber. The substrate has a first region arranged to encompass a range of possible oil levels within the shock absorber, a second region corresponding to a range of possible extension states of the shock absorber and a third region comprising one or more traces. Each trace corresponds to a temperature value and is indicative of an optimum relationship between the oil levels and the range of extension states at the respective temperature value associated with the trace. | 10-23-2014 |
| 20140346272 | AIRCRAFT LANDING GEAR STRUT - A landing gear rod ( | 11-27-2014 |
| 20140367513 | WEIGHT REDUCING LANDING GEAR FEATURES - Aircraft landing gear is provided comprising a trunnion arm having a centering portion and a first stress relieving portion and an outer cylinder coupled to the trunnion arm is disclosed. The first stress relieving portion may relieve stress spreading from the centering portion to the outer cylinder. In addition, the first stress relieving portion may be disposed adjacent the centering portion, and may relieve stress spreading from the centering portion to at least one trunnion arm portion. In various embodiments, the aircraft landing gear disclosed herein may further comprise a cross bolt portion formed in a portion of the trunnion arm and a second stress relieving portion disposed adjacent the cross bolt portion. The second stress relieving portion may relieve stress spreading from the cross bolt portion to at least one trunnion arm portion. | 12-18-2014 |
| 20150034762 | ROUTINGS FOR ARTICULATED LANDING GEAR - An articulated landing gear may include electrical lines and/or hydraulic lines located within the articulated landing gear. The articulated landing gear may have a hollow structural post and a hollow trailing arm coupled by a pivot joint. The electrical lines and/or hydraulic lines may be routed through an interior of the hollow structural post and through an interior of the hollow trailing arm. A bulkhead within the hollow structural post or the hollow trailing arms may include guide holes. The electrical lines and/or hydraulic lines may be supported by the bulkhead by passing through the guide holes. The electrical lines and/or hydraulic lines may be flexible around the pivot joint. | 02-05-2015 |
| 20150041585 | BOGIE BEAM ANGLE SENSOR - A bogie beam sensor may include a bracket and a target arm pivotably coupled to the bracket. The bracket may be coupled to a bogie beam. A sensor may be coupled to the bracket, and a target may be coupled to the target arm. A drive link may be coupled to the target arm and a piston. In response to the bogie beam pivoting with respect to the piston, the drive link may cause the target arm to rotate with respect to the bogie beam. The sensor may detect movement of the target on the target arm, and an angular position of the bogie beam may be determined based on the position of the target. | 02-12-2015 |
| 20150041586 | LANDING GEAR STORAGE COMPARTMENT OF AIRCRAFT, AND AIRCRAFT - To provide a landing gear storage compartment of an aircraft which can protect accessories installed around a landing gear by blocking jet blast and dust etc. while suppressing the weight and the cost. A landing gear storage compartment | 02-12-2015 |
| 20150090837 | ATTACHMENT OF A LANDING GEAR - A bracket ( | 04-02-2015 |
| 20160009423 | METHOD OF DETECTING A LEAK PAST A DYNAMIC SEAL IN AIRCRAFT LANDING GEAR | 01-14-2016 |
| 20160089721 | AEROSPACE COMPONENT AND METHOD FOR PRODUCING AN AEROSPACE COMPONENT - A method of forming an aerospace component, the method including: forming a first subcomponent by an additive layer manufacturing (ALM) process, the first subcomponent having an inner surface defining an inner space; performing a non-ALM machining process to modify a portion of the inner surface of the first subcomponent; and forming a second subcomponent by an ALM process, the second subcomponent being arranged to close the inner space to complete the component. | 03-31-2016 |
| 20160090172 | LANDING GEAR COMPONENTS HAVING IMPROVED JOINTS - The present disclosure includes landing gear components, such as an outer cylinder of a shock strut assembly. The outer cylinder includes one or more structural attachment pins configured to engage with other components of the landing gear including pintle frames, drag braces, and torque links. The pins include a cobalt alloy mated to a cobalt containing coating for improved wear resistance, which may eliminate the need for a bushing between the pin and the receptacle of the corresponding landing gear component. | 03-31-2016 |
| 20160167774 | ACTUATOR | 06-16-2016 |
| 20160178064 | AN APPARATUS COMPRISING A SEALING ELEMENT | 06-23-2016 |
| 20160185453 | AIRCRAFT LANDING GEAR ASSEMBLY - An aircraft landing gear includes an axle on which wheel and brake assemblies are mounted. An adaptor member is mounted on the axle and arranged to define a brake rod connection point that is distinct from a conventional brake rod connection point defined by the brake assembly. The adaptor member is coupled to the brake assembly via an adaptor linkage that is arranged to react brake torque but arranged to permit relative movement between the adaptor member and the brake assembly in degrees of freedom which are not required to react brake torque. | 06-30-2016 |
| 20100001128 | Retracting Air Cushioned Landing System for Air Vehicles - A hybrid air vehicle is disclosed in which a cover is provided for a plurality of air cushioned landing pads to reduce drag when airborne. The pad is inflatable to provide an air cushioned during touchdown and deflatable during flight of the air vehicle. The cover can include a first cover portion and a second cover portion. A first cover roller of the first cover portion and a matching second cover roller of the second cover portion abut to cover the corresponding pad. The first cover roller and the second cover roller, which are separate and free from a physical linkage there between, are separable in an eyelid fashion to expose the corresponding pad. A separation gap between the first cover roller and the second cover roller is increased or decreased by roller straps to cover or expose the corresponding pad. | 01-07-2010 |
| 20100181421 | TWO-STAGE AIRBAG INFLATION SYSTEM WITH PYROTECHNIC DELAY - A two-stage pyrotechnic gas generator for inflating an airbag has a housing with first and second chambers each having gas release apertures. The chambers are separated by a partition having an opening. Running through the gas generator is an essentially contiguous train of combustible material including a train of fast burning material passing through the first chamber to the opening, a pyrotechnic delay element associated with the opening, and a train of fast burning material within the second chamber. The first and second chambers each include a quantity of propellant deployed to be ignited by the corresponding train of fast burning material. An initiator, associated with the first chamber, is configured to initiate combustion of the essentially contiguous train of combustible material. As a result, the second quantity of propellant is ignited at a predefined delay relative to ignition of the first quantity of propellant to achieve precisely timed two-phase inflation with a single electronic initiator. | 07-22-2010 |
| 20100206983 | Crash Attenuation System for Aircraft - A crash attenuation system for an aircraft, the system having an airbag carried by the aircraft and inflatable generally adjacent an exterior of the aircraft. The airbag has at least one vent for releasing gas from the interior of the airbag. A gas source is in fluid communication with the interior of the airbag for inflating the airbag with gas generated provided by the first gas source. A vent valve is provided for controlling a flow of gas through each vent, each vent valve being selectively configurable between an open state, in which gas can pass through the associated vent from the interior of the airbag, any number of intermediate states, in which the vent is partially open, and a closed state, in which gas is retained within the interior of the airbag. | 08-19-2010 |
| 20110011973 | AIRBAG SYSTEM WITH IMPROVED PERFORMANCE FOR A WIDE RANGE OF LOADS - An airbag system according to any one individual feature or combination of features as described herein. | 01-20-2011 |
| 20110204181 | Aircraft Occupant Protection System - A crash attenuation system for an aircraft includes an airbag carried by the aircraft that is inflatable generally adjacent an exterior of the aircraft. The airbag is in fluid communication with at least one vent passage for channeling gas from within the interior of the airbag to a region external to the airbag that allows the gas to escape without being obstructed by the airbag. A gas source is in fluid communication with the interior of the airbag for inflating the airbag. A vent valve is provided within the vent passage for controlling a flow of gas through the vent passage, thereby controlling deflation of the airbag. The vent valve is continuously adjustable to and between an open state, a closed state, and any number of partially open states. | 08-25-2011 |
| 20110226898 | Crash Attenuation System for Aircraft - A crash attenuation system for an aircraft, the system having an airbag carried by the aircraft and inflatable generally adjacent an exterior of the aircraft. The airbag has at least one vent for releasing gas from the interior of the airbag. A gas source is in fluid communication with the interior of the airbag for inflating the airbag with gas generated provided by the gas source. A vent valve is provided for controlling a flow of gas through each vent, each vent valve being selectively configurable between an open state, in which gas can pass through the associated vent from the interior of the airbag, and a closed state, in which gas is retained within the interior of the airbag. The gas source is provided for at least partially re-inflating the airbag after venting of gas through the at least one vent. | 09-22-2011 |
| 20110272523 | SHOCK ABSORPTION SYSTEM - An air bag | 11-10-2011 |
| 20110297785 | AIRFRAME POSITION ADJUSTING STRUCTURE - Provided is an airframe position adjusting structure capable of adjusting the position of an airframe (A) inclined in the left-and-right direction. In the airframe position adjusting structure ( | 12-08-2011 |
| 20120043416 | RETRACTING AIR CUSHIONED LANDING SYSTEM FOR AIR VEHICLES - An air vehicle includes a bag skirt extendable along a portion of a hull of the air vehicle. The bag skirt is inflatable to provide an air cushion during touchdown and deflatable during flight of the air vehicle. The air vehicle also includes a cover roller adjacent the bag skirt, and a cover portion coupled to the cover roller. The cover roller is operable between exposed position and unexposed positions to expose and hide the bag skirt with the cover portion. The cover roller includes an extensible shaft and a pad securely wrapped around the extensible shaft. The extensible shaft is capable of being rotated along a shaft axis. One end of the extensible shaft is pivotally coupled to the hull by an anchor. A circumference of the cover roller is configured as a function of a distance between the exposed and the unexposed positions. | 02-23-2012 |
| 20120132741 | METHOD OF CONTROLLING A BUOYANCY SYSTEM FOR AN AIRCRAFT, A BUOYANCY SYSTEM IMPLEMENTING SAID METHOD, AND AN AIRCRAFT - A buoyancy system ( | 05-31-2012 |
| 20130032665 | Active Vent and Re-Inflation System for a Crash Attenuation Airbag - A crash attenuation system has an airbag inflatable generally adjacent to an exterior of the aircraft. The system includes a gas generator in fluid communication with an interior of the airbag. The system also includes a vent system having a vent passage supported by the aircraft, the vent passage being configured to allow gas to escape from within the airbag during an impact. The vent system also includes an actuator door for sealing the vent passage, thereby preventing gas from leaving the airbag. The actuator door is actuated by an actuator, the actuator being in fluid communication with the gas generator through an actuator duct. The system operates such that deployment of gas from the gas generator causes the actuator to inflate, thereby causing the actuator door to seal the vent passage. The gas generator is configured to re-inflate the airbag after the actuator door seals the vent passage. | 02-07-2013 |
| 20130062465 | High Efficiency External Airbag for Crash Attenuation - An external airbag for an aircraft includes an inflatable bladder having a top portion and a bottom portion, the top portion being generally adjacent to an exterior of the aircraft. A widthwise panel divides the inflatable bladder into a first cylindrical portion and a second cylindrical portion. The widthwise panel acts to restrict outward bulging of the inflatable bladder. An aperture in the widthwise panel may be used for allowing gas communication between the first cylindrical portion and a second cylindrical portion. | 03-14-2013 |
| 20130068883 | CONSTANT AREA VENT FOR EXTERNAL CRASH ATTENUATION AIRBAG - The external crash attenuation airbag includes an inflatable bladder which is inflatable to an exterior of an aircraft, so that the inflatable bladder is generally located between the aircraft and a crash surface when inflated. The airbag includes a vent configured to burst at a predefined burst pressure, the vent being located a side portion of the inflatable bladder. The airbag also includes a vent support located approximate the vent, the vent support being configured to prevent deformation and therefore maintain the effectiveness of a venting area of the vent. | 03-21-2013 |
| 20140124620 | METHOD AND SYSTEM FOR EMERGENCY LANDING OF A VEHICLE - A method for emergency landing of a vehicle, such as a helicopter or like, is described. The vehicle has at least one airbag provided with a respective opening valve for allowing the outflow of the gas therein contained. The airbag is suitable to cushion the impact of the vehicle with ground, and is inflated for an emergency landing. The method checks the conditions for the emergency landing of the vehicle, detects the maximum or impact speed of the vehicle, and opens the opening valve after the detection of an activation speed of the vehicle, so as to deflate the airbag. A system for controlling airbags of a vehicle, such as a helicopter or like, is also described. | 05-08-2014 |
| 20140332627 | CONTROL AND SAFETY SYSTEM FOR AN AIRPLANE - A Safety and Control System for an airplane that allows a pilot to adjust the direction of an airplane and protect the plane in emergency situations. The engine of the plane can create thrust in more than one direction for improved maneuverability. A plurality of parachutes and landing pads can be deployed to protect the plane, along with the people in it. | 11-13-2014 |
| 20150041584 | ACTIVE VENT AND RE-INFLATION SYSTEM FOR A CRASH ATTENTUATION AIRBAG - A crash attenuation system has an airbag inflatable generally adjacent to an exterior of the aircraft. The system includes a gas generator in fluid communication with an interior of the airbag. The system also includes a vent system having a vent passage supported by the aircraft, the vent passage being configured to allow gas to escape from within the airbag during an impact to a second set of airbags for flotation. The vent system also includes an actuator door for sealing the vent passage, thereby preventing gas from leaving the airbag. The actuator door is actuated by an actuator, the actuator being in fluid communication with the gas generator through an actuator duct. The system operates such that deployment of gas from the gas generator causes the actuator to inflate, thereby causing the actuator door to seal the vent passage. The gas generator is configured to re-inflate the airbag after the actuator door seals the vent passage. | 02-12-2015 |
| 20150083856 | LANDING SYSTEMS FOR AIR VEHICLES - An air cushioned landing system for an air vehicle comprises an inflatable and deflatable skirt ( | 03-26-2015 |
| 20160001893 | IMPACT PROTECTION APPARATUS - An impact protection apparatus is provided, comprising a gas container configured to hold a compressed gas and an inflatable member configured to be inflated by the gas and function as an airbag of a movable object, such as an aerial vehicle. A valve controls flow of gas from the container to the inflatable member in response to a signal from a valve controller. The valve and valve controller are powered by an independent power source than one or more other systems of the movable object. A safety mechanism may also be provided that, unless deactivated, prevents inflation of the inflatable member. | 01-07-2016 |
| 20160075447 | IMPACT PROTECTION APPARATUS - An impact protection apparatus is provided, comprising a gas container configured to hold a compressed gas and an inflatable member configured to be inflated by the gas and function as an airbag of a movable object, such as an aerial vehicle. A valve controls flow of gas from the container to the inflatable member in response to a signal from a valve controller. The valve and valve controller are powered by an independent power source than one or more other systems of the movable object. A safety mechanism may also be provided that, unless deactivated, prevents inflation of the inflatable member. | 03-17-2016 |
| 20180022310 | AIRBAG SYSTEM FOR USE WITH UNMANNED AERIAL VEHICLES | 01-25-2018 |
