A system is provided for dispersing supercooled liquid water in an icing wind tunnel. The system includes a spray bar; a spray nozzle coupled to the spray bar; a pressure control valve coupled to the spray bar; and a controller coupled to the pressure control valve and the spray nozzle. The controller is configured to receive input identifying a selected liquid water content and a selected water droplet size for dispersing the supercooled liquid water in the icing wind tunnel; configure an injector duty cycle of the spray nozzle to generate the selected liquid water content; and configure the pressure control valve to generate the selected water droplet size, wherein configuring the spray nozzle and the pressure control valve disperses the supercooled liquid water in the icing wind tunnel.
2.
ELECTRO-PNEUMATIC CABLE CUTTER ASSEMBLY FOR AIRCRAFT HOIST
A cable cutter assembly for an aircraft hoist is disclosed, and includes an actuator assembly (e.g., at least one pressurized fluid cavity, a first outlet port, and a solenoid that includes a coil and an armature). The armature is movable between closed and open positions relative to the first outlet port (e.g., via an actuation force), with the armature engaging the first outlet port for the closed position (e.g., a valve seal incorporated by the armature) and being spaced from the first outlet port for the open position. A cutter body includes a cutter body cavity that is fluidly connected with the first outlet port. A cutter is movably disposed within the cutter body cavity. Disposing the armature in the open position (e.g., via energizing the coil) fluidly connects the pressurized fluid cavity with the cutter body cavity to move the cutter in a cable cutting direction.
A landing gear actuation system is disclosed herein. The landing gear actuation system includes a trunnion sprocket coupled to a movable member, a drive motor, and a flexible drive member extending between and to the motor and the trunnion sprocket. The motor is configured to move the flexible drive member, wherein the movement of the flexible drive member moves the trunnion sprocket and the movable member. The flexible drive member may be a belt or a chain.
An inspection system is disclosed herein. The inspection system includes a control system and a hub assembly. The control system includes a base having a top surface and configured to move horizontally forward and backward, an upright member extending orthogonally from the top surface of the base and configured to move vertically up and down, the upright member having a top surface, and an elongated member extending orthogonal to the upright member having a proximal end and a distal end, the proximal end connected to the top of the upright member, wherein the elongated member is configured to rotate. The hub assembly is connected to the distal end of the elongated member. The hub assembly includes a spring-loaded arm extending orthogonally from the hub assembly and a sensor connected to a distal end of the spring-loaded arm.
5.
TEMPERATURE COMPENSATED SHOCK STRUT VISUAL HEALTH INDICATOR SYSTEMS AND METHODS
A temperature compensating shock strut health indicator system for use with a shock strut comprises a visual indicator comprising a plurality of sectors and a pointer configured to rotate with respect to the visual indicator to point to one of the plurality of sectors. The sector to which the pointer points to is dependent on the shock strut stroke (i.e., the position of the piston with respect to the cylinder). In various embodiments, the visual indicator includes various rings that correspond to a different temperature compensated ideal stroke whereby a crew member can correspond the pointer to the appropriate ring depending on ambient temperature. In various embodiments, the pointer comprises a temperature sensitive material configured to cause the pointer to rotate with respect to the visual indicator to actively compensate for temperature.
Systems and methods for operating a hoist and hook assembly may method comprising determining a clutch slip via a clutch sensor, determining an overload via a load sensor, and cutting a cable coupled to the hoist and hook assembly in response to the clutch slip determination and the overload determination.
ABSTRACT A hydraulic fluid system is disclosed herein. The hydraulic fluid system includes a hydraulic motor including an output shaft, a reduction gear box having a first side and an opposing second side, the reduction gear box being coupled to the output shaft at the first side and coupled to a reduction shaft at the second side, and a magneto-rheological fluid brake (MRF) brake coupled to the reduction shaft. Date Recue/Date Received 2023-04-12
F15B 13/00 - SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR - Details of servomotor systems
F16H 61/4157 - Control of braking, e.g. preventing pump over-speeding when motor acts as a pump
A closure assembly for a fluid port having a fluid flow channel defined along an axis, the channel ending in a port opening, the closure assembly comprising: a closure cap (301) extending in a first plane arranged to seat across, and close the port opening, in use, in a closed state, a guide arm (310) extending from the cap in a second plane substantially perpendicular to the first plane; a lifting guide (601) to accommodate and retain the guide arm for movement of the guide arm in the second plane as the cap moves axially away from the opening; and a pivot mechanism (312, 314) between the guide arm and the lifting guide about which the cap is able to pivot relative to the lifting guide to an open position.
A landing gear actuation system is disclosed herein. The landing gear actuation system includes an attachment point integral to a movable member, a flexible pull member having a first end coupled to the attachment point, and a motor configured to move the flexible pull member, wherein the movement of the flexible pull member moves the attachment point and the movable member.
An aircraft wing may comprise an airfoil having deicing zone, an anti-icing zone, and an ice runback control zone. An aircraft wing may comprise an electro- thermal ice protection system disposed in the aircraft wing. The electro-thermal ice protection system may be disposed along the deicing, anti-icing, and ice runback control zones of the airfoil to improve aerodynamic performance of the aircraft and reduce ice formation along the wings of the aircraft.
Ice may form along the leading edge of an aircraft wing or horizontal and vertical stabilizers. A pneumatic deicer system may be configured to inflate and dislodge ice along the leading edge of lift and control surfaces. The pneumatic deicer system may comprise a laser welded deicing boot attached to the leading edge. The compressed air can be directed to the deicing boot, inflating the deicing boot along inflatable tubes formed by laser welds, which can crack and dislodge the ice. A method of manufacturing a laser welded pneumatic deicer boot is also disclosed.
B64D 15/16 - De-icing or preventing icing on exterior surfaces of aircraft by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface
Ice may form along the leading edge of an aircraft wing. A pneumatic deicing system may be configured to crack and dislodge ice along the leading edge of the wing. The pneumatic deicing system may comprise a deicing boot assembly haying a deicing boot attached to the leading edge, and a gas generator fluidly coupled to the deicing boot assembly. The gas generator may comprise a propellant and may decompose the propellant, liberating a compressed gas. The compressed gas may be directed to the deicing boot assembly, inflating the deicing boot, which may crack and dislodge the ice.
B64D 15/18 - De-icing or preventing icing on exterior surfaces of aircraft by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface the surface being an aerofoil, rotor, or propeller
F23R 5/00 - Continuous combustion chambers using solid or pulverulent fuel
13.
SYSTEMS AND METHODS FOR MANUFACTURING LANDING GEAR COMPONENTS USING TITANIUM
A metallic part is disclosed. The part may comprise a functionally graded monolithic structure characterized by a variation between a first material composition of a tubular preform and a second material composition of at least one of a secondary structural element wherein each of the first material composition and the second material composition comprises at least one of a titanium metal or an alloy of titanium. The first material composition may comprise an alpha-beta titanium alloy. The second material composition may comprise a beta titanium alloy.
B22F 3/115 - Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor by spraying molten metal, i.e. spray sintering, spray casting
B22F 3/16 - Both compacting and sintering in successive or repeated steps
B23K 20/12 - Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding
A composite component may be additively manufactured by a system that mixes a fiber and matrix and extrudes a body made of the fiber and matrix toward a work piece. The extruded body may be pressed against the work piece and the workpiece and/or extruded body may be moved relative to the other. The extruded body may at least partially melt and flow, uniting with the workpiece and additively manufacturing a layer of a feature thereon. In this manner, friction stir additive manufacturing of composite components having a fiber and matrix composite may be accomplished.
B29C 64/118 - Processes of additive manufacturing using only liquids or viscous materials, e.g. depositing a continuous bead of viscous material using filamentary material being melted, e.g. fused deposition modelling [FDM]
B29C 70/12 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of short length, e.g. in the form of a mat
15.
INTEGRAL STEERING MOTOR AND COLLAR FOR LANDING GEAR
A steering apparatus may comprise a steering collar, a first linear actuator, a first drive gear, a crankshaft, and a sun gear, wherein the sun gear is disposed within the collar, wherein the first drive gear is fixed to the crankshaft and coupled to the sun gear such that the collar rotates about the sun gear in response to rotation of the crankshaft, wherein the first linear actuator is coupled between the crankshaft and the collar.
Methods, systems, and apparatuses for component manufacturing are provided. A component may be manufactured via an extrusion of loose substrate material into a unitary tubing. Features may be added to the tubing via friction stir additive manufacturing to manufacture a component. In this manner, a component may be manufactured from titanium alloys while processing challenges such as iron segregation or material loss through machining are ameliorated. Such a component may replace steel or other high strength components and further exhibits corrosion resistance.
B33Y 30/00 - ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - Details thereof or accessories therefor
B33Y 70/00 - Materials specially adapted for additive manufacturing
B22F 3/20 - Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor by extruding
B23K 20/12 - Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding
An aircraft actuation system is disclosed that includes a pair of cylinders, a piston movably disposed in each cylinder, and a roller train that extends between the pistons in the two cylinders. A portion of the roller train is disposed beyond the cylinders to engage a pinion. Movement of the pistons in the two cylinders in opposite directions produces a corresponding movement of the roller train to in turn rotate the pinion. The roller train may be maintained in compression between its two ends by fluid pressure exerted on a common face of each of the pistons in the two cylinders. The cylinders may be disposed in non-colinear relation, including in parallel relation to one another. A guide may be used to maintain rollers of the roller train in a proper orientation for entry into a space between an outer race and the pinion.
F15B 15/06 - Mechanical layout characterised by the means for converting the movement of the fluid-actuated element into movement of the finally-operated member for mechanically converting rectilinear movement into non-rectilinear movement
An aircraft landing gear actuation system which uses two separate actuation forces to retract aircraft landing gear is disclosed. One of the actuation forces may be provided by an actuator, such as a hydraulic actuator. Another of these actuation forces may be provided by a pressurized fluid that is directed into the actuator through a conduit that extends into a hollow interior of an actuator rod of the actuator. The pressurized fluid may be provided from a pressurized fluid source that contains a fixed volume of pressurized fluid. This pressurized fluid may exert a force on an actuator piston of the actuator or the actuator rod. The pressurized fluid may also be used to dampen the deployment of the landing gear.
A method is provided for producing ultra-fine-grained materials using additive manufacturing. The method includes commanding, by a controller, a laser device to produce a plurality of optical pulses to a base material to add an additive material to the base material. The method further includes commanding, by the controller, a vibration mechanism to vibrate the base material as the plurality of optical pulses are being applied to the base material forming fine equiaxed grains with random crystallographic texture in the base material.
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
B33Y 40/00 - Auxiliary operations or equipment, e.g. for material handling
B22F 10/38 - Process control to achieve specific product aspects, e.g. surface smoothness, density, porosity or hollow structures
B22F 10/50 - Treatment of workpieces or articles during build-up, e.g. treatments applied to fused layers during build-up
Disclosed is a method of manufacturing a stainless steel component, the method including texturizing a stainless steel substrate by bead blasting to provide a texturized stainless steel. The stainless steel substrate includes grade 316 austenitic stainless steel. The method also includes treating the texturized stainless steel with a passivation solution to provide a passivated stainless steel. The method further includes treating the passivated stainless steel with an oxidizing solution including sulfuric acid and hydrogen peroxide at a temperature of about 130 to about 200 degrees Fahrenheit for at least 50 minutes to provide an antimicrobial stainless steel surface that is free of a separate coating. The method includes obtaining at least 99.9% E. coli reduction as measured by JIS Z 2801:2010 test on the antimicrobial stainless steel without a separate coating.
C23F 17/00 - Multi-step processes for surface treatment of metallic material involving at least one process provided for in class and at least one process covered by subclass or or class
B05D 5/02 - Processes for applying liquids or other fluent materials to surfaces to obtain special surface effects, finishes or structures to obtain a matt or rough surface
B24C 1/10 - Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for compacting surfaces, e.g. shot-peening
C21D 7/06 - Modifying the physical properties of iron or steel by deformation by cold working of the surface by shot-peening or the like
C23C 8/58 - Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using liquids, e.g. salt baths, liquid suspensions more than one element being applied in more than one step
C23C 22/50 - Treatment of iron or alloys based thereon
21.
SELF-SUSTAINING SHIMMY DAMPER SYSTEM FOR LANDING GEAR SHOCK STRUT ASSEMBLIES
A shimmy damper assembly may comprise: a damper piston including a piston head, the piston head comprising a first permanent magnet, a shimmy cylinder including a second permanent magnet disposed on an axial surface of the shimmy cylinder, and a gland nut coupled to the shimmy cylinder, the gland nut including a third permanent magnet spaced apart axially from the second permanent magnet, the piston head disposed between the first permanent magnet and the second permanent magnet.
A rack assembly for a rack and pinion gear system may comprise: a rack housing; and a rack disposed within the rack housing, the rack and the rack housing at least partially defining a first hydraulic chamber disposed between a first side of the rack and the rack housing, a second hydraulic chamber disposed between a second side of the rack and the rack housing, a third hydraulic chamber disposed within the rack proximal the first hydraulic chamber, and a fourth hydraulic chamber disposed within the rack proximal the second hydraulic chamber.
F16H 19/04 - Gearings comprising essentially only toothed gears or friction members and not capable of conveying indefinitely-continuing rotary motion for interconverting rotary motion and reciprocating motion comprising a rack
23.
SYSTEMS AND METHODS FOR HIGH STRENGTH TITANIUM ROD ADDITIVE MANUFACTURING
A method of forming a rod feedstock for titanium stir friction welding additive manufacturing may comprise: mixing a plurality of powdered metals comprising titanium, iron, vanadium, and aluminum to produce a powder blend; at least one of die pressing the powder blend to fomi a die pressed powder or continuously powder rolling the powder blend to form a die pressed powder; and sintering the powder blend to form a rod feedstock having a cross-sectional profile.
B22F 3/16 - Both compacting and sintering in successive or repeated steps
B33Y 70/00 - Materials specially adapted for additive manufacturing
B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
B22F 5/12 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of tubes or wires
24.
SYSTEMS AND METHODS FOR HIGH STRENGTH TITANIUM ROD ADDITIVE MANUFACTURING
A method of titanium rod additive manufacturing may comprise: mixing a plurality of powdered metals comprising titanium, iron, vanadium, and aluminum to produce a powder blend; isostatic pressing the powder blend to form a billet having a cross-sectional profile; cutting the billet to form a rod feedstock having the first cross-sectional profile; loading the rod feedstock into an additive manufacturing machine configured to deposit the rod feedstock; and producing a metallic component from the rod feedstock.
B33Y 70/00 - Materials specially adapted for additive manufacturing
B33Y 80/00 - Products made by additive manufacturing
B22F 5/12 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of tubes or wires
B23K 20/12 - Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding
25.
GYROSCOPE ASSISTED HELICOPTER RESCUE LIFT SYSTEMS AND METHODS
A patient litter basket spin control assembly includes a first gyroscope and a motion sensor for sensing an angular acceleration of a patient litter basket. The first gyroscope generates a counter torque to the litter basket to slow the angular acceleration of the litter basket to provide stabilization. The first gyroscope and a second gyroscope may be configured as a pair and located at opposite ends of the litter basket.
B64D 1/00 - Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
A62B 1/00 - Devices for lowering persons from buildings or the like
B66C 13/06 - Auxiliary devices for controlling movements of suspended loads, or for preventing cable slack for minimising or preventing longitudinal or transverse swinging of loads
26.
SYSTEMS AND METHODS FOR DIRECT DEPOSITION OF THIXOTROPIC ALLOYS
A method may comprise: placing a probe in a molten metal melt comprising a thixotropic metal alloy; injecting a gas into the molten metal melt to form a saturated slurry, the saturated slurry being at a temperature above a liquidus temperature of the thixotropic metal alloy after injecting the gas; removing the probe from the molten metal melt; and depositing the molten metal melt through an extruder of an additive manufacturing system.
A torque transfer assembly comprising a drive shaft (4) and a driven shaft (10) and a dielectric insert (20) arranged to be positioned between the drive shaft and the driven shaft, the insert assembly comprising a body of dielectric material shaped to form an insulating layer and configured to engage, respectively, with a first shaped engagement feature (15) on the drive shaft and a second shaped engagement feature (16) on the driven shaft, in torque transfer engagement, the insulating layer providing a dielectric barrier between the drive shaft and the driven shaft.
F16D 3/74 - Yielding couplings, i.e. with means permitting movement between the connected parts during the drive with the coupling parts connected by one or more intermediate members with axially-spaced attachments to the coupling parts the intermediate member or members being made of rubber or other flexible material
F16K 51/00 - Other details not peculiar to particular types of valves or cut-off apparatus
A dielectric insulating assembly arranged to be positioned between a drive shaft (4) and a driven shaft (10) of a motorised drive assembly, the assembly comprising dielectric insulation (5) between the drive shaft and the driven shaft and plurality of electrically non-conductive fastener elements (6) configured to connect the drive shaft to the driven shaft and the dielectric insulation therebetween, in torque transfer engagement, the fasteners located around an outer boundary of the dielectric insulation.
F16D 3/56 - Yielding couplings, i.e. with means permitting movement between the connected parts during the drive with the coupling parts connected by one or more intermediate members comprising elastic metal lamellae, elastic rods, or the like, e.g. arranged radially or parallel to the axis, the members being shear-loaded collectively by the total load
F16D 1/033 - Couplings for rigidly connecting two coaxial shafts or other movable machine elements for connecting two abutting shafts or the like by clamping together two faces perpendicular to the axis of rotation, e.g. with bolted flanges
F16D 1/076 - Couplings for rigidly connecting two coaxial shafts or other movable machine elements for attachment of a member on a shaft or on a shaft-end by clamping together two faces perpendicular to the axis of rotation, e.g. with bolted flanges
F16K 51/00 - Other details not peculiar to particular types of valves or cut-off apparatus
A valve assembly comprising a movable valve element (3) arranged to move relative to a valve housing (30) between an open and a closed position, the valve housing including a drainage body (40) provided with drainage holes (41, 42) arranged to allow fluid to drain from the valve assembly from gaps (10, 11, 12) between the movable valve element and the housing via the drainage holes.
A clamp assembly comprising a plurality of clamps (20, 30) each comprising two clamp arms (21, 22, 31, 32) pivotal relative to each other about a hinge point (23, 33), and a common connector part (40) joining two or more of said clamps to each other at their hinge points.
F16B 2/10 - Clamps, i.e. with gripping action effected by positive means other than the inherent resistance to deformation of the material of the fastening external, i.e. with contracting action using pivoting jaws
F16L 23/036 - Flanged joints the flanges being connected by members tensioned axially characterised by the tensioning members, e.g. specially adapted bolts or C-clamps
F16M 13/02 - Other supports for positioning apparatus or articles; Means for steadying hand-held apparatus or articles for supporting on, or attaching to, an object, e.g. tree, gate, window-frame, cycle
A connector assembly comprising: a first connector part (100) and a second connector part (200), each connector part defining a fluid flow passage therethrough configured to together define a fluid flow conduit when the first and second parts are connected together, the connector assembly further comprising an extension part (500) mounted around one of the first and the second connector parts, the extension part (500) arranged to move relative to the connector part around which it is mounted to extend across an interface area between the first connector part and the second connector part and to bridge the first and second connector parts when the first and second connector parts are brought to meet each other to define the fluid conduit.
F16L 21/02 - Joints with sleeve or socket with elastic sealing rings between pipe and sleeve or between pipe and socket, e.g. with rolling or other prefabricated profiled rings
F16L 21/08 - Joints with sleeve or socket with additional locking means
32.
MECHANICAL ICE PROTECTION SYSTEM FOR AERODYNAMIC SURFACES
An ice protection system adapted to protect at least one ice-susceptible flight surface of an aircraft includes a mechanical ice protection device attached to the flight surface. A controller controls a power source that causes the mechanical ice protection device to change in shape and, thereby, change an aerodynamic characteristic of the flight surface. This change in shape happens only when the current thickness of ice on the surface exceeds a minimum thickness.
B64D 15/16 - De-icing or preventing icing on exterior surfaces of aircraft by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface
B64D 15/20 - Means for detecting icing or initiating de-icing
F25C 5/06 - Apparatus for disintegrating, removing or harvesting ice without the use of saws by deforming bodies with which the ice is in contact, e.g. using inflatable members
A ball valve assembly comprising a ball element (11) arranged to be rotated by rotation of a shaft (110) in engagement with the ball element, the ball element having first (12) and second (13) flow channels defined therethrough, a first inlet port (12a) at a first end of said first flow channel, a first outlet port (12b) at a second end of the first channel, a second inlet port (13a) at a first end of the second flow channel and a second outlet port (13b) at a second end of the second channel.
F16K 11/087 - Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves; Arrangement of valves and flow lines specially adapted for mixing fluid with all movable sealing faces moving as one unit comprising only taps or cocks with spherical plug
F16K 5/06 - Taps or cocks comprising only cut-off apparatus having at least one of the sealing faces shaped as a more or less complete surface of a solid of revolution, the opening and closing movement being predominantly rotary with plugs having spherical surfaces; Packings therefor
F16K 37/00 - Special means in or on valves or other cut-off apparatus for indicating or recording operation thereof, or for enabling an alarm to be given
34.
LASER INDUCED GRAPHENE AS PRETREATMENT TO PLATE NON-CONDUCTIVE COMPOSITES
A method of manufacture can comprise: treating a surface of a polymeric substrate with a laser induced graphene; and bonding a metallic layer to the laser induced graphene.
A cable tensioning capstan assembly comprises a capstan drum and at least a first traction flange. The capstan drum may be configured to support a cable (e.g., a cable is configured to wrap around the capstan drum), and the capstan drum may be configured to rotate about an output axis. The first traction flange may be disposed adjacent the first axial end of the capstan drum and configured to rotate about the output axis. In various embodiments, the first traction flange is independently rotatable relative to the capstan drum. A clutch assembly between an input shaft and the first traction flange may facilitate the independent rotatability of the first traction flange.
A wheel retaining assembly for a landing gear having an axle and an outer wheel bearing, the axle defining an axial direction along an axial centerline, is disclosed. In various embodiments, the wheel retaining assembly includes a first wheel spacer configured to slide over the axle and to abut the outer wheel bearing, the first wheel spacer having an axially outward portion; and a second wheel spacer configured to slide over the axle, the second wheel spacer having an axially inward portion configured to engage the axially outward portion of the first wheel spacer.
A nose-wheel steering system may comprise an actuator and a bevel gear rotationally coupled to a drive shaft of the actuator. The bevel gear may be configured to rotate about a first axis. A collar gear may be intermeshed with the bevel gear. The collar gear may be configured to rotate about a second axis that is generally perpendicular to the first axis.
A method of determining whether a landing event of an aircraft is hard may comprise: receiving, by a controller via a stroke position sensor, a stroke profile as a function of time for a shock strut; receiving, by the controller via a gas pressure sensor, a gas pressure in a gas chamber of the shock strut; receiving, by the controller via a wheel speed sensor, a wheel speed of a tire in a landing gear assembly; calculating, by the controller, multiple time dependent functions based on the stroke profile of the shock strut, based on the gas pressure, a shock strut temperature, and the wheel speed; and comparing, by the controller, the multiple time dependent functions to respective predetermined thresholds to determine whether the landing event is hard.
ABSTRACT A shock strut assembly for a landing gear may comprise a strut cylinder, a strut piston configured to telescope relative to the strut cylinder, and a locking system. The locking system may be configured to restrict rotation of the strut piston relative to the strut cylinder in response to compression of the shock strut assembly. Date Recue/Date Received 2021-11-12
A snubber assembly may comprise a snubber having a snubber body with an inner diameter surface and an outer diameter surface, the snubber including a plurality of valve receptacles disposed in the outer diameter surface, the snubber including a plurality of radial apertures disposed through the snubber body, each radial aperture in the plurality of radial apertures disposed in a respective valve receptacle in the plurality of valve receptacles; and a plurality of restrictor valves, each restrictor valve in the plurality of restrictor valves disposed in a respective valve receptacle in the plurality of valve receptacles, each restrictor valve in the plurality of restrictor valves including an orifice disposed through a blade.
F16F 9/512 - Means responsive to load action on the damper or fluid pressure in the damper
F16F 9/516 - Special means providing automatic damping adjustment resulting in the damping effects during contraction being different from the damping effects during extension
A shaft assembly includes a composite tube and an impact shield. The composite tube has a longitudinal centerline axis and the impact shield may be disposed around the composite tube and may extend along a length of the composite tube. A gap may be defined between the composite tube and the impact shield. Generally, shaft assembly is configured to inhibit impact damage to the composite tube and/or facilitate visual detection of damage from impacts. The shaft assembly may further include a shock absorbing sleeve disposed in the gap between the composite tube and the impact shield.
A system may comprise a main host device; a first splitter having a first input port, a first output port, and a second output port, the first input port configured for electronic communication with the main host device; a first local display monitor configured for electronic communication with the first output port of the first splitter; a first video capture device configured for electronic communication with the second output port of the first splitter; a multi-cam switch having a plurality of input ports and an outlet port; a second splitter having a second input port, a third output port, and a fourth output port, the outlet port of the multi-cam switch configured for electronic communication with the second input port; and a second video capture device configured for electronic communication with the third output port.
An uplock system includes a cam plate comprising a cam channel, a hook configured to rotate with respect to the cam plate, a follower rotatably coupled to the hook, wherein a portion of the follower moves within the cam channel in response to rotation of the hook, a stopper configured to engage the follower, and a first biasing member configured to bias the stopper towards the follower to stop the follower from moving within the cam channel, thereby locking the hook in a locked position.
A damping mechanism may comprise a housing, a shaft, a spring arm assembly including a first spring arm, wherein the spring arm assembly is coupled to the shaft and configured to rotate in response to a rotation of the shaft, wherein the first spring arm extends relatively radially outward of the spring arm assembly toward the housing in response to the rotation of the shaft, and wherein the rotation of the shaft is damped in response to extending the first spring arm.
F16F 15/121 - Suppression of vibrations in rotating systems by making use of members moving with the system using elastic members or friction-damping members, e.g. between a rotating shaft and a gyratory mass mounted thereon using springs as elastic members, e.g. metallic springs
A shock strut is disclosed. The shock strut may include a shock strut cylinder, a shock strut piston that is slidably disposed within the shock strut cylinder, a metering pin, and a percolation seal configured to restrict a flow of liquid between the shock strut cylinder and the shock strut piston.
A system and various methods for determining a center of mass of an aircraft with a plurality of shock strut assemblies is illustrated. Multiple sensors, including a gas pressure sensor, and/or a position sensor, may be used to gather data and determine the center of mass of the aircraft. Various methods illustrated herein may evaluate the center of mass relative to a wheelbase axis and a wheel tread axis based on the gathered data.
A dual-sleeve, locking adjustment arrangement includes a position-sensitive component comprising an aperture, an outer eccentric sleeve disposed in the aperture, and an inner eccentric sleeve disposed in the outer sleeve. Rotation of the outer sleeve with respect to the position-sensitive component and the inner sleeve drives rotation of the position-sensitive component to adjust an angular position of the component.
A system for use with a tripod landing gear assembly of an aircraft may comprise: a tension strut assembly having a tension strut extending from an upper end to a lower end; a drag brace assembly having an upper brace and a lower brace, the upper brace pivotably coupled to the lower brace at a center point, the lower brace rotatably coupled to the lower end of the tension strut; and a jury linkage pivotally coupled to the drag brace assembly at the center point rotatably coupled to a middle portion of the tension strut, the middle portion between the upper end and the lower end
A system for servicing a shock strut may comprise a system controller and a tangible, non-transitory memory configured to communicate with the system controller. The tangible, non-transitory memory may have instructions stored thereon that, in response to execution by the system controller, cause the system controller to perform operations, which may comprise: receiving, by the system controller, a hydraulic fluid volume difference or a pressurized gas volume difference from a ground support controller; determining, by the system controller, a desired fluid flow rate based on the hydraulic fluid volume difference or the pressurized gas volume difference; and outputting, by the system controller, a desired fluid flow rate signal corresponding to the desired fluid flow rate to at least one of a hydraulic fluid flow controller or a pressurized gas flow controller.
F16F 9/06 - Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium using both gas and liquid
F16F 9/43 - Filling arrangements, e.g. for supply of gas
50.
CONTINUOUS STACKED DUAL WRAP TUBE END CLOSURE FOR ANTI-ICING SYSTEMS
An anti-icing system may comprise a deicing boot of an elastomeric material comprising a plurality of tubes, wherein the deicing boot comprises a first set of tubes and a second set of tubes, wherein each of the first set of tubes and the second set of tubes have a corresponding end, and wherein the corresponding end is coupled to a continuous dual wrap end closure.
B64D 15/16 - De-icing or preventing icing on exterior surfaces of aircraft by mechanical means, e.g. pulsating mats or shoes attached to, or built into, surface
B64D 15/20 - Means for detecting icing or initiating de-icing
ABSTRACT A shimmy damper for centering a landing gear includes a cap and a housing. The shimmy damper further includes a damper shaft extending from the cap to the housing. The shimmy damper further includes a plurality of magnets configured to exert an opposing force on the cap and the housing via the damper shaft, providing a centering mechanism of the damper shaft within the housing. This centering action in turn provides for the centering of the landing gear during flight. 14 Date Recue/Date Received 2021-03-17
A system for controlling landing gear subsystems may comprise a controller and a first motor drive unit in operable communication with the controller. A first electric motor and a second electric motor may be in operable communication with the first motor drive unit. A second motor drive unit may be in operable communication with the controller. A third electric motor and a fourth electric motor may be in operable communication with the second motor drive unit. An AC/DC converter may be electrically coupled to the first drive unit and the second motor drive unit.
A nose-wheel steering system is disclosed. In various embodiments, the system includes an actuator; a strut; and a gearing mechanism operably coupling the actuator to the strut, the gearing mechanism including a steering collar attached to the strut, and idler gear engaged with the actuator and a pinion having a first gear engaged with the idler gear and a second gear engaged with the steering collar.
A landing gear system for an aircraft is disclosed. In various embodiments, the system includes a truss frame pivotally connected to a frame of the aircraft and configured to rotate about an axis; a retraction actuator configured to rotate the truss frame about the axis; a first truss link pivotally connected to the truss frame; a second truss link pivotally connected to the first truss link; a truss locking link pivotally connected to the truss frame and to the second truss link; and an articulation actuator configured to pivot the first truss link with respect to the truss frame.
- 9 - ABSTRACT ICE DETECTION ARRANGEMENT An ice detection system for an aircraft surface, comprising a sensor assembly (10) comprising a plurality of temperature sensitive elements configured to be arranged at respective points on the aircraft surface, a control unit (20) arranged to receive signals indicative of a temperature sensed by each of the temperature sensitive elements, a signal conducting bus (50) to transmit the signals from the temperature sensitive elements to the control unit, and means for providing power to the sensor assembly, wherein the sensor assembly further comprises a multiplexer (40) arranged to multiplex the signals from the plurality of temperature sensitive elements into a single signal for transmission on the signal conducting bus to the control unit. [FIG. 2] Date Recue/Date Received 2021-01-15
AB STRACT A carbon allotrope element includes a carbon allotrope layer formed from a carbon allotrope material impregnated with a dielectric resin and haying a first surface. The carbon allotrope element further includes a first bus bar in communication with the first surface, and a second bus bar in communication with the first surface and non-adjacent to the first bus bar. The first surface includes a layer of the dielectric resin and a plurality of abraded regions, and each of the first and second bus bars is in communication with one of the plurality of abraded regions of the first surface. 13 Date Recue/Date Received 2020-11-10
H01B 1/04 - Conductors or conductive bodies characterised by the conductive materials; Selection of materials as conductors mainly consisting of carbon-silicon compounds, carbon, or silicon
B82Y 30/00 - Nanotechnology for materials or surface science, e.g. nanocomposites
C08L 101/12 - Compositions of unspecified macromolecular compounds characterised by physical features, e.g. anisotropy, viscosity or electrical conductivity
H05B 3/14 - Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material the material being non-metallic
ABSTRACT A heating element and conductive element system may include a heater conductive element and a heating element. The heater conductive element and the heating element may be integral components. The heater conductive element and the heating element may be discrete components. The heater conductive element may be configured for enhanced mechanical fatigue compared to typical conductive element. 19 Date Recue/Date Received 2021-01-11
H05B 3/06 - Heater elements structurally combined with coupling elements or with holders
B82Y 30/00 - Nanotechnology for materials or surface science, e.g. nanocomposites
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
H05B 3/14 - Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material the material being non-metallic
ABSTRACT A steering system may include a gear assembly and a collar. The gear assembly may include a planet carrier, a planet gear, an internal ring gear, and a sun gear. The planet gear may be disposed between the internal ring gear and the sun gear. The gear assembly may provide a mechanical advantage to the steering system, which may result in a greater powered steering range, a shorter rack assembly, and/or increased design space relative to typical steering systems. Date Recue/Date Received 2021-01-06
ABSTRACT A damping actor selector may be configured to transition a multi-actor damping system from a first damping actor configuration to a second damping actor configuration. The multi- actor damping system may be used in a shock strut assembly to alter a damping curve of the shuck strut assembly. The damping actor selector may be coupled to a metering pin of a shock strut assembly. The damping actor selector may be configured to rotate the metering pin to transition the multi-actor damping system from a first damping actor configuration to a second damping actor configuration. The first damping actor configuration may correspond to a first damping curve. The second damping actor configuration may correspond to a second damping curve. The first damping curve being different than the second damping curve. 41 Date Recue/Date Received 2021-01-11
F16F 9/44 - Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium - Details such means combined with temperature correction
ABSTRACT A main orifice plate assembly may be configured to transition a multi-actor damping system from a first damping actor configuration to a second damping actor configuration. The multi-actor damping system may be used in a shock strut assembly to alter a damping curve of the shuck strut assembly. The main orifice plate assembly may be a part of a main orifice assembly including an orbital cam. The main orifice plate may include a flow restrictor. The flow restrictor may be configured to retract or deploy in response to main orifice plate rotating about the orbital cam. The first damping actor configuration may correspond to a first damping curve. The second damping actor configuration may correspond to a second damping curve. The first damping curve being different than the second damping curve. 42 Date Recue/Date Received 2021-01-11
F16F 9/44 - Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium - Details such means combined with temperature correction
ABSTRACT A metering pin for use in a multi-actor damping system is disclosed herein. The multi-actor damping system may be used in a shock strut assembly to alter a damping curve of the shuck strut assembly. The metering pin may be configured to transition the multi-actor damping system from a first damping actor configuration to a second damping actor configuration. The first damping actor configuration may correspond to a first damping curve. The second damping actor configuration may correspond to a second damping curve. The first damping curve being different than the second damping curve. 42 Date Recue/Date Received 2021-01-11
F16F 9/44 - Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium - Details such means combined with temperature correction
62.
SYSTEMS FOR HARVESTING ROTATIONAL WHEEL ENERGY FOR LANDING GEAR RETRACTION
AB STRACT A system for extracting energy for landing gear retraction may comprise a wheel pump rotationally coupled to a wheel via a pinion gear. A landing gear control valve assembly may be fluidly coupled to an output of the wheel pump. A secondary pump may be fluidly coupled to the landing gear control valve assembly, and an electric motor may be operationally coupled to the secondary pump. Date Recue/Date Received 2020-1 2-2 1
F03G 7/08 - Mechanical-power-producing mechanisms, not otherwise provided for or using energy sources not otherwise provided for recovering energy derived from swinging, rolling, pitching, or like movements, e.g. from the vibrations of a machine
63.
CONDUCTIVE INK WITH ENHANCED MECHANICAL FATIGUE RESISTANCE
ABSTRACT A conductive ink may comprise a high temperature thermoplastic polyurethane (TPU) and a plurality of conductive particles disposed in the high temperature TPU. The plurality of conductive particles may comprise between 60% and 95% of the conductive ink by weight. The high temperature TPU may include a melting point between 120 C and 200 C. The conductive ink may be used for external heated composite structures, such as rotor blades, fixed wings, faring, engine lip electrothermal ice protection, or the like. The conductive ink may have enhanced mechanical fatigue resistance. 18 Date Recue/Date Received 2020-11-27
B82Y 30/00 - Nanotechnology for materials or surface science, e.g. nanocomposites
H05B 3/12 - Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material
ABSTRACT An ice protection system may include a rotary blade, an electrothermal heater, and a low ice adhesion surface. The low ice adhesion surface may include an adhesion strength below 100 kPa. The rotary blade may be disposed between the electrothermal heater and the low ice adhesion surface. The electrothermal heater may be disposed between the low ice adhesion surface and the rotary blade. The low ice adhesion surface may include a coating or a surface treatment. 16 Date Recue/Date Received 2020-10-30
ABSTRACT A system for use with a landing gear of an aircraft includes a drag brace assembly having an upper end configured to be rotatably coupled to the aircraft and a lower end configured to be rotatably coupled to a shock strut of the landing gear. The system further includes a jury linkage having a brace portion configured to be pivotally coupled to the drag brace assembly and a strut portion pivotally coupled to the brace portion and configured to be rotatably coupled to the shock strut. 19 Date Recue/Date Received 2020-10-30
AB STRACT A lock system for a landing gear assembly may comprise a housing and a hook configured to rotate relative to the housing. A lock pin may be configured to translate into a rotational path of the hook. An electromechanical actuator may be configured to translate the lock pin. 37 CA 3065253 2019-12-13
A nose landing gear system is disclosed. In various embodiments, the nose landing gear system includes an electro-hydraulic actuator configured to raise and lower a nose shock strut assembly; a first electro-mechanical actuator configured to steer the nose shock strut assembly; and a second electro-mechanical actuator configured to open and close a fairing door.
A method of manufacturing a cured vessel is disclosed herein. The method comprises wrapping a first bladder in a first composite laminate, wrapping a second bladder in a second composite laminate. The method further comprises joining the first composite laminate and the second composite laminate by wrapping them both in a third composite laminate to form an uncured vessel. The un-cured vessel is cured by heating the uncured vessel and pressurizing the bladder while the uncured vessel is in a vessel mold.
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
B65D 1/40 - Rigid or semi-rigid containers having bodies formed in one piece, e.g. by casting metallic material, by moulding plastics, by blowing vitreous material, by throwing ceramic material, by moulding pulped fibrous material or by deep-drawing operations p - Details of walls
A system for shrinking landing gear includes a shock strut having a cylinder and a piston to be received by the cylinder. The system further includes a collar coupled to a brace linkage and the piston, a torque arm configured to resist rotation between the collar and the piston, and a shrink linkage coupled between the torque arm and the cylinder. The collar rotates relative to the cylinder in response to retraction of the landing gear. Rotation of the collar rotates the piston and the torque arm relative to the cylinder. The rotation of the collar relative to the cylinder forces, via the shrink linkage, the piston towards the aircraft attachment within the cylinder.
An apparatus for forming a composite shaft may comprise an axial fiber strip dispensing assembly and a hoop fiber strip dispensing assembly. The axial fiber strip dispensing assembly may include a plurality of fiber strip guides located circumferentially about a center axis. The plurality of fiber strip guides may be configured to dispense a plurality of circumferentially adjacent first fiber strips with the plurality of circumferentially adjacent first fiber strips extending in a generally axial direction. The hoop fiber strip dispensing assembly may be configured to dispense a second fiber strip circumferentially about the center axis.
B29C 70/24 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in at least three directions forming a three dimensional structure
An auxiliary brake assembly for use in a hoist, is disclosed. The auxiliary brake assembly comprises a pinion, a fastener, and a clutch assembly. The pinion may comprise a mesh gear disposed proximate a respective mesh gear of a rotor gear. The clutch assembly may be disposed between the fastener and the mesh gear. The fastener may be configured to compress the clutch assembly in the event a cable drum of the hoist is free spinning. The compression of the clutch may lock the pinion and the rotor gear and stop the cable drum from spinning freely.
A nut locking assembly may comprise a pin, a nut, and a lock ring. The pin may include an outer diameter threaded surface and a plurality of radially inward extending grooves formed between the outer diameter threaded surface and an end of the pin. The nut may include an inner diameter threaded surface and a plurality of radially outward extending grooves formed between the inner diameter threaded surface and an axial end of the nut. The lock ring may include a plurality of outer diameter protrusions and a plurality of inner diameter protrusions.
F16B 39/10 - Locking of screws, bolts, or nuts in which the locking takes place after screwing down by a plate or ring immovable with regard to the bolt or object
An electrical harness includes an electrical cable, an inner tubing, an outer tubing, and a braid tubing disposed between the inner tubing and the outer tubing. The braid tubing is physically contacting the inner tubing and the outer tubing to react against twisting of the electrical harness.
A tube arrangement includes a composite tube defining a centerline axis, wherein the composite tube comprises a proximal surface and a distal surface, and an end fitting comprising a first end disposed within the composite tube and a second end extending from the composite tube, wherein an outer surface of the end fitting defines a flared portion defining a terminus of the first end, a lobe portion disposed axially from the flared portion, and a terminating portion disposed axially from the lobe portion, the proximal surface conforms to a geometry of the outer surface of the end fitting, the lobe portion and the flared portion mechanically lock the end fitting to the composite tube to mitigate movement of the end fitting relative to the composite tube.
Systems and methods for operating a potable water system in an aircraft are provided. Aspects include determining, by a controller, flight data associated with a flight for the aircraft, determining passenger data associated with the flight, determining an estimated water consumption for the potable water system associated with the aircraft based on the passenger data, determining a water quantity value for the flight based at least in part on the flight data and the estimated water consumption, and transmitting, by the controller, a request for the water quantity value for the potable water system for the flight to a water fulfillment system.
A clutch having two stages for applying varied torque between an input shaft and an output shaft includes a clutchpack having input friction plates and output friction plates. The clutch further includes a first spring configured to apply a first pressure to the clutchpack to compress the clutchpack. The clutch further includes a second spring configured to apply a second pressure to the clutchpack to compress the clutchpack. The clutch further includes an engagement nut configured to move in response to rotation of the output shaft relative to the input shaft to compress the second spring in order to increase an amount of the second pressure applied to the clutchpack.
B66D 1/58 - Safety gear responsive to excess of load
B64D 1/00 - Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
B66D 1/14 - Power transmissions between power sources and drums or barrels
B66D 1/60 - Rope, cable, or chain winding mechanisms; Capstans adapted for special purposes
F16D 13/56 - Clutches with multiple lamellae with means for increasing the effective force between the actuating sleeve or equivalent member and the pressure member in which the clutching pressure is produced by springs only
78.
DUAL BUS AND HARDWARE ARCHITECTURE FOR HIGH RELIABILITY CONTROL OF HELICOPTER HOIST
A control system for a component of a rescue hoist attached to an aircraft is disclosed. In various embodiments, the control system includes a first bus extending between a control module of the rescue hoist and a control input device; a second bus extending between the control module of the rescue hoist and the control input device; and a hardwire extending between the control module of the rescue hoist and the control input device.
A control system for a rescue hoist attached to an aircraft is disclosed. In various embodiments, the control system includes a first bus extending between a control module of the rescue hoist and a control input device; and a second bus extending between the control module of the rescue hoist and the control input device. The first bus is configured to transmit a first signal from the control input device to the control module and the second bus is configured to transmit a second signal from the control input device to the control module, both the first signal and the second signal being generated by the control input device in response to a manipulation of the control input device.
A system for shrinking landing gear includes a shock strut having a cylinder and a piston to be received by the cylinder. The system further includes an upper cam fastened to the piston and a lower cam fastened to the cylinder. The system further includes a brace configured to be coupled to the shock strut to lock the landing gear in a deployed position, and to fold towards the shock strut during retraction of the landing gear. The system further includes a collar coupled to the brace and the piston and configured to rotate relative to the cylinder in response to folding of the brace such that rotation of the collar rotates the piston and the upper cam relative to the lower cam, the rotation of the upper cam relative to the lower cam forcing the piston towards the aircraft attachment within the cylinder.
A bracket manifold for a landing gear assembly is disclosed. In various embodiments, the bracket manifold includes a mounting plate having a central portion and a first wing portion extending from the central portion; and a first manifold section integrated monolithically into at least one of the central portion and the first wing portion of the mounting plate.
F16L 3/01 - Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets for supporting or guiding the pipes, cables or protective tubing, between relatively movable points, e.g. movable channels
A veneer panel includes a face layer formed from a carbon fiber sheet. The veneer panel further includes a backing layer. The veneer panel further includes a thermoset dry film adhesive located between the face layer and the backing layer and attaching the face layer to the backing layer.
A panel assembly for use in an aircraft includes a surface. The panel assembly further includes a body portion including a honeycomb material having multiple body volumes oriented perpendicular to the surface. The panel assembly further includes an edge portion extending around an edge of the panel assembly and including the honeycomb material having multiple edge volumes oriented parallel to the surface in order to increase edge strength of the panel assembly.
B32B 3/02 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by features of form at particular places, e.g. in edge regions
A47B 96/20 - Furniture panels or like furniture elements
B32B 3/12 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure
B64D 11/00 - Passenger or crew accommodation; Flight-deck installations not otherwise provided for
84.
BONDED STRUCTURAL RIB FOR HEATED AIRCRAFT LEADING EDGE
An aircraft may include a fuselage and a wing extending away from the fuselage to a wing tip. The wing may have a leading edge portion, a suction side portion, and a pressure side portion. A thermoelectric element may be coupled to an inner surface of the wing. A chemical adhesive may be disposed on a thermoelectric inner surface. A structural rib may be adhesively bonded to the thermoelectric element by curing the chemical adhesive. The structural rib may be mechanically fastened to a suction side of the wing and to a pressure side of the wing.
Disclosed is a sensor system for retrofitting a water supply of an airplane to detect leakage. The system includes a housing having a first band with an inner diameter sized to receive a necked portion of a valve for consumer access to the water supply. The system includes a first transducer disposed on the first band operable to provide a position measurement corresponding to a relative position between a head of the valve and the necked portion. The system includes a second transducer operable to provide a pressure measurement corresponding to a pressure of a compressed gas in a water tank of the water supply. The system includes a controller having input channels operable to receive the position measurement and the pressure measurement. The controller is operable to indicate a leak condition.
G01M 3/26 - Investigating fluid tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors
B64F 5/60 - Testing or inspecting aircraft components or systems
A method for monitoring a dual-stage shock strut may include measuring a first primary chamber pressure when the dual-stage shock strut is in a first state, measuring a first secondary chamber pressure when the dual-stage shock strut is in the first state, measuring a shock strut stroke when the dual-stage shock strut is in the first state, measuring a first temperature, measuring a second temperature, measuring a second primary chamber pressure when the dual-stage shock strut is in a second state, measuring a second secondary chamber pressure when the dual-stage shock strut is in the second state, and determining a servicing condition of the shock strut based upon at least the first primary chamber pressure, the first secondary chamber pressure, the shock strut stroke, the first temperature, the second temperature, the second primary chamber pressure, and the second secondary chamber pressure.
F16F 9/06 - Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium using both gas and liquid
F16F 9/32 - Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium - Details
A cable rotation blocking system (CRBS) (300) is described herein. The CRBS extends along an axis X between a first end (305) and a second end (303), and comprises a first section provided at the first end (305), the first section being configured to be connectable to a cable (100). The CRBS further comprises a second section provided at the second end (303), the second section being configured to be attachable to a load. With the CRBS described herein, when no load, or a load up to an upper load threshold is attached to the second section, the second section is rotatable about the axis X, relative to the first section, however, when a load higher than the upper load threshold is attached to the second section, the second section is prevented from rotation about the axis relative to the first section.
A self-adjusting automatic load brake for a hoist is disclosed. In various embodiments, the load brake includes a first shaft defining an annular hollow portion; a second shaft defining an engagement portion, the engagement portion configured for sliding disposition within the annular hollow portion; a first reaction plate coupled to the first shaft; a second reaction plate coupled to the second shaft; and a plurality of friction discs, with at least one of the plurality of friction discs coupled to a cup and disposed between the first reaction plate and the second reaction plate, the annular hollow portion of the first shaft and the engagement portion of the second shaft being sized and configured to accommodate thinning of the plurality of friction discs.
B66D 5/14 - Crane, lift, hoist, or winch brakes operating on drums, barrels, or ropes with axial effect embodying discs
A62B 1/10 - Devices for lowering persons from buildings or the like by making use of rope-lowering devices with brake mechanisms for the winches or pulleys mechanically operated
B64D 1/00 - Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
B66D 1/60 - Rope, cable, or chain winding mechanisms; Capstans adapted for special purposes
F16D 65/52 - Slack adjusters mechanical self-acting in one direction for adjusting excessive play
89.
AUTOMATIC LOAD BRAKE HAVING WEAR-INDUCED LOCKING MECHANISM
An automatic load brake having a wear-induced locking mechanism for a hoist is disclosed. In various embodiments, the load brake includes a first shaft defining an annular hollow portion and a radially outer surface; a second shaft defining an engagement portion and a radially inner surface, the radially inner surface configured to engage the radially outer surface; a first reaction plate coupled to the first shaft; a second reaction plate coupled to the second shaft; and a plurality of friction discs, with at least one of the plurality of friction discs coupled to a cup and disposed between the first reaction plate and the second reaction plate, the annular hollow portion of the first shaft being configured to lock to the engagement portion of the second shaft upon thinning of the plurality of friction discs.
B66D 5/14 - Crane, lift, hoist, or winch brakes operating on drums, barrels, or ropes with axial effect embodying discs
A62B 1/10 - Devices for lowering persons from buildings or the like by making use of rope-lowering devices with brake mechanisms for the winches or pulleys mechanically operated
B64D 1/00 - Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
B66D 1/60 - Rope, cable, or chain winding mechanisms; Capstans adapted for special purposes
F16D 65/52 - Slack adjusters mechanical self-acting in one direction for adjusting excessive play
A clutch assembly for a hoist may comprise a first epicyclic gear train and a first set of friction disks rotationally coupled to the first epicyclic gear train. A second set of friction disks may be in operable communication with the first set of friction disks. Torque may be transferred between the first set of friction disks and the second set of friction disks by means of a friction coupling between the first set of friction disks and the second set of friction disks. A pinion may be rotationally coupled to the second set of friction disks. A splined portion of the pinion may form an output of the clutch assembly.
B64D 1/00 - Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
B66D 1/58 - Safety gear responsive to excess of load
F16D 13/76 - Friction clutches specially adapted to incorporate with other transmission parts, i.e. at least one of the clutch parts also having another function, e.g. being the disc of a pulley
An armrest for a seat may comprise paneling and an easy hook assembly. The easy hook assembly may include a flange and a keyhole protrusion. The flange and the keyhole protrusion may each extending beyond an exterior surface of the paneling. The flange and the keyhole protrusion may allow the armrest to be installed after the paneling is attached.
A method for monitoring a shock strut may comprise measuring a first shock strut pressure, measuring an ambient temperature, measuring a shock strut stroke, measuring a second shock strut pressure, and determining a servicing condition of the shock strut based upon the first shock strut pressure, the ambient temperature, the shock strut stroke, and the second shock strut pressure, wherein the servicing condition indicates whether it is desirable for the shock strut to be serviced with at least one of a liquid and a gas. The first shock strut pressure and the shock strut stroke may be measured before the takeoff event with a weight of an aircraft supported by the shock strut.
F16F 9/06 - Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium using both gas and liquid
F16F 9/32 - Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium - Details
A vehicle including a housing, and a vehicle seat disposed in the housing. The vehicle further includes at least one radial slit disc energy attenuation assembly having an upper end coupled to the vehicle seat and a lower end coupled the housing. The radial slit disc energy attenuation assembly includes a slit disc stack having a plurality of deflectable discs configured to deflect in response to realizing a force applied by the vehicle seat.
B60N 2/42 - Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles for particular purposes or particular vehicles the seat constructed to protect the occupant from the effect of abnormal g-forces, e.g. crash or safety seats
B60N 2/427 - Seats or parts thereof displaced during a crash
A method of making a multi-section tank with composite material includes pre- tensioning the composite material, wrapping a soluble tool in the composite material, and curing the composite material around the soluble tool. The composite material is pre- tensioned with force to align fibers in the composite material.
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29C 33/52 - SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING - Details thereof or accessories therefor with means for, or specially constructed to facilitate, the removal of articles, e.g. of undercut articles soluble or fusible
B29C 70/40 - Shaping or impregnating by compression
A method of making a blind hole in a wall of a multi-section tank during manufacture includes inserting a thin, flexible composite spacer ring in a hole in a composite material between mating parts of a soluble tool. The composite spacer ring is cured to the composite material during curing and maintains the hole between sections of the tank once completed.
Provided are embodiments for a system and method for performing real-time performance and health monitoring of an ice detector system. Embodiments include sensing, by a current sensor, a current parameter of a drive coil of an ice detector circuit, and monitoring a performance and health of the ice detector circuit based at least in part on the current parameter, where the drive coil is coupled to a feedback coil that is configured to provide a feedback signal to a driver circuit to control the drive coil. Embodiments also include comparing the performance of the ice detector circuit and expected performance of the ice detector circuit, and providing a report based at least in part on the comparison.
Disclosed is a multilayer structure, comprising: a first heater layer comprising a CNT heater, wherein the CNT heater comprises a composite of carbon nanotubes and silicone; and a second heater layer comprising a PTC heater, wherein the PTC heater comprises a composite of carbon black and polymer; wherein the first heater layer and the second heater layer are first and second respectively in an electrical series; wherein the first heater layer has a negative temperature coefficient with respect to electrical resistivity; and wherein the second heater layer has a positive temperature coefficient with respect to electrical resistivity. Also disclosed is an aircraft component comprising the multilayer structure.
H05B 3/12 - Heating elements characterised by the composition or nature of the materials or by the arrangement of the conductor characterised by the composition or nature of the conductive material
B82Y 30/00 - Nanotechnology for materials or surface science, e.g. nanocomposites
A water tank includes a compression molded tank shell. The tank shell includes a back panel and a side panel extending from the back panel. The side panel defines an outer perimeter of the water tank. A compression molded front panel is secured to the side panel to enclose an interior of the water tank. A method of forming a potable water tank includes forming a tank shell via a compression molding process, the tank shell including a back panel and a side panel extending from the back panel, the side panel defining an outer perimeter of the water tank. A front panel is separately formed by compression molding, and the front panel is secured to the side panel thereby enclosing an interior of the water tank.
B65D 1/00 - Rigid or semi-rigid containers having bodies formed in one piece, e.g. by casting metallic material, by moulding plastics, by blowing vitreous material, by throwing ceramic material, by moulding pulped fibrous material or by deep-drawing operations p
B29C 39/02 - Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressure; Apparatus therefor for making articles of definite length, i.e. discrete articles
B65D 1/42 - Reinforcing or strengthening parts or members
A clutch assembly includes a first gear, a second gear, a first proximity sensor configured to determine a first number of teeth of the first gear that pass by the first proximity sensor within a period of time, and a second proximity sensor configured to determine a second number of teeth of the second gear that pass by the second proximity sensor within the period of time.
A passive anti-icing and/or deicing device can include an icephobic outer layer configured to prevent ice from forming and/or building up on the outer layer by preventing ice from adhering to the outer layer. The device can include a backer film attached to an underside of the icephobic outer layer, and an adhesive attached to the backer film on an opposite side of the backer film relative to the icephobic outer layer.
B64D 15/00 - De-icing or preventing icing on exterior surfaces of aircraft
C09K 3/18 - Materials not provided for elsewhere for application to surface to minimize adherence of ice, mist or water thereto; Thawing or antifreeze materials for application to surfaces