Methods and systems for automated placement of composite material on a surface of a component, the composite material including unidirectional fibers, is provided. A set of fiber paths along the surface is established, the set of fiber paths comprising at least one ply, each ply comprising a respective plurality of fiber paths being substantially aligned with a respective direction. An isotropy factor for the component is determined based on the set of fiber paths, the isotropy factor being indicative of a distribution of the plurality of fiber paths on the surface. When the isotropy factor exceeds a predetermined threshold, a respective layer of composite material is applied to the surface of the component using an automated fiber placement machine and for each of the at least one ply, wherein the unidirectional fibers of the composite material are applied along the set of fiber paths.
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers
B32B 37/00 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
B32B 41/00 - Arrangements for controlling or monitoring lamination processes; Safety arrangements
A radial inlet plenum a forward panel, an aft panel, and a cowling extending therebetween. The forward and aft panels are coupled between the cowling and an engine. The forward and aft panels include flexible sections to allow the engine to translate radially and axially, as well as rotate, relative to the cowling.
A cyclic stick for transmitting control commands to blades of a rotorcraft via at least one transmission member, including a grip configured for engagement with a pilot's hand, a control arm and at least one locking mechanism. The control arm has a bottom end configured for connection to the transmission member(s) and for rotational connection to a base support structure, and a top end pivotally connected to the grip. The control arm includes first and second arm portions pivotally connected to each other, the first arm portion defining the bottom end, the second arm portion defining the top end. The locking mechanism(s) selectively prevent a relative pivoting motion between the first and second arm portions and a relative pivoting motion between the second arm portion and the grip. A method of adjusting a position of a grip of a cyclic stick in a rotorcraft cabin is also discussed.
A cyclic stick for transmitting control commands to blades of a rotorcraft via at least one transmission member, including a grip configured for engagement with a pilot's hand, a control arm and at least one locking mechanism. The control arm has a bottom end configured for connection to the transmission member(s) and for rotational connection to a base support structure, and a top end pivotally connected to the grip. The control arm includes first and second arm portions pivotally connected to each other, the first arm portion defining the bottom end, the second arm portion defining the top end. The locking mechanism(s) selectively prevent a relative pivoting motion between the first and second arm portions and a relative pivoting motion between the second arm portion and the grip. A method of adjusting a position of a grip of a cyclic stick in a rotorcraft cabin is also discussed.
A method of operating an automated fiber placement machine including determining an effective length and a steering radius of a localized curved portion of a path and obtaining data including combinations of effective length and steering radius reference values each associated with a corresponding one of maximum speed values. A predetermined defect is avoided when the tape is laid along a curved path characterized by any of the combinations of effective length and steering radius reference values and laid at the corresponding maximum speed value. The method further includes determining a maximum speed based on the maximum speed values of the data in function of a correspondence between the effective length and the steering radius of the curved path and the combinations of effective length and steering radius reference values, selecting a speed for laying the tape being at most the maximum speed, and laying the tape on the surface.
A navigation system for vehicles, such as rotorcraft, includes a directional gyroscope having a magnetic heading correction mode, a nonmagnetic manual heading correction mode and a nonmagnetic automatic heading correction mode. A magnetic field sensor is operably coupled to the directional gyroscope and is operable to generate magnetic north-based signals. A heading correction input is operably coupled to the directional gyroscope and is operable to generate manual signals upon actuation thereof. A global positioning system sensor is operably coupled to the directional gyroscope and is operable to generate track-based signals. In the magnetic heading correction mode, the directional gyroscope receives the magnetic north- based signals for heading corrections. In the nonmagnetic manual heading correction mode, the directional gyroscope receives the manual signals for heading corrections. In the nonmagnetic automatic heading correction mode, the directional gyroscope periodically receives the track-based signals for heading corrections.
In one embodiment, a method may comprise heating a composite material into a viscous form, wherein the composite material comprises a thermoplastic and a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is randomly arranged within the thermoplastic. The method may further comprise extruding a plurality of strands of the composite material, wherein extruding the plurality of strands causes the plurality of reinforcement fibers within each strand to align. The method may further comprise arranging the plurality of strands of the composite material to form a mold tool, wherein the mold tool is configured to mold a composite structure at a heated temperature, and wherein the mold tool comprises an anisotropic thermal expansion property, wherein the anisotropic thermal expansion property is based on an orientation of the plurality of reinforcement fibers within the mold tool.
B29C 70/20 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length oriented in a single direction, e.g. roving or other parallel fibres
8.
PLANET GEAR HAVING FAILURE MODE OPTIMIZED FOR CONTINUED PLANETARY GEAR SYSTEM OPERATION
A method of optimizing a planetary gear system for continued operation after failure of a planet gear includes providing a planetary gear system and reducing a backup ratio of a planet gear of the planetary gear system by reducing a rim thickness of the planet gear.
A method of avoiding gear tooth interference in a planetary gear system includes designing and building a planetary gear system comprising a selected base pitch and tooth length for planet gears, breaking a rim of one of the planet gears, and verifying whether tooth tip interference occurs during operation of the planetary gear system.
An apparatus includes a shaft comprising a spiral spline along a length of the shaft. A rotor comprising a blade extending from the rotor and a tubular hole extending into the rotor. The tubular hole comprises a spiral groove configured to mate with the spiral spline on the shaft. Relative rotation between the spiral spline and the spiral groove causes the rotor to linearly move along the shaft. A cam surface comprises a recession. The blade nesting in the recession constrains rotation of the rotor about the shaft in a first rotational direction, and allows linear movement of the rotor along the shaft in a second rotational direction.
B64C 27/30 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with provision for reducing drag of inoperative rotor
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64C 27/50 - Blades foldable to facilitate stowage of aircraft
11.
METHOD AND APPARATUS TO IMPROVE LIFT TO DRAG RATIO OF A ROTOR BLADE
A rotor blade includes a blade member having a top side, a bottom side, a leading edge, and a trailing edge. inner surfaces of the top and bottom sides of the leading extension member adhesively are connected to the top side and the bottom side of the leading edge of the blade member. The leading edge extension member is comprised of plies of at least one of a fabric and a tape with a cured resin. The leading edge extension member is configured to extend a chord length of at least a portion of the rotor blade. The curved portion of the leading edge extension member and the leading edge of the blade member define a hollow interior portion therebetween. A method of improving a lift to drag ratio of a rotor blade is also disclosed.
The present invention includes a first barrier layer configured to cover a leading edge of the blade or wing; one or more electrical bus bars disposed on the first barrier layer proximate to and substantially parallel with the leading edge; a ground bus bar disposed on the first barrier layer proximate to and substantially parallel with the leading edge; a second barrier layer disposed over the one or more electrical bus bars and the ground bus bar; one or more heating elements disposed on the second barrier layer, and each heating element electrically connected to one of the electrical bus bars and to the ground bus bar; and a third barrier layer disposed over the one or more heating elements.
H05B 3/20 - Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater
H05B 3/28 - Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater non-flexible heating conductor embedded in insulating material
13.
ROTOR BRAKE EFFECT BY USING ELECTRIC DISTRIBUTED ANTI-TORQUE GENERATORS AND OPPOSING ELECTRIC MOTOR THRUST TO SLOW A MAIN ROTOR
The present invention includes a system and method for slowing the rotation of a rotor using, for example, rotor brake system for a rotorcraft comprising: one or more generators connected to a main rotor gearbox; an electric distributed anti-torque system mounted on a tail boom of the rotorcraft comprising two or more electric motors connected to the one or more generators, wherein the two or more electric motors are connected to one or more blades; and wherein a rotation of the rotor is slowed by placing a drive load on the main rotor gearbox with the one or more generators to bleed the mechanical power from rotor into electrical power via the two or more electric motors, wherein the electric distributed anti-torque system generates thrust in opposing directions.
B64C 27/82 - Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft
The present invention includes an apparatus for preventing aircraft rollover upon a water landing comprising: a deployable first and/or second boom affixed by a first end to the aircraft and capable of deployment substantially perpendicular to a longitudinal axis of the aircraft; and a first and/or second air bladder attached to a second end of the first and/or second boom, wherein the first and/or second air bladders are configured to inflate when an aircraft lands in the water, wherein deployment of the first and second boom and air bladder prevents aircraft rollover upon water landing; or a deployable keel affixed by a first end to the aircraft and capable of deployment substantially perpendicular to a longitudinal axis and opposite a rotor of the aircraft upon a water landing, wherein the keel is sized to prevent aircraft rollover upon deployment; or both.
B63B 43/04 - Improving safety of vessels, e.g. damage control, not otherwise provided for reducing risk of capsizing or sinking by improving stability
B63B 43/14 - Improving safety of vessels, e.g. damage control, not otherwise provided for reducing risk of capsizing or sinking by improving buoyancy using outboard floating members
The present invention includes a first frame attached to an aerial vehicle or a mounting plate attached to the aerial vehicle, and a second frame attached to an aimable device moveably connected to the aerial vehicle or the mounting plate. The first frame and the second frame are configured to collectively provide a hard stop that prevents the aimable device from pointing at the aerial vehicle.
B64D 7/06 - Arrangement of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft the armaments being firearms movably mounted
A helicopter includes a full authority digital engine controlled (FADEC) engine, a first two-position throttle switch disposed on a first collective control stick, the first two- position throttle switch being movable between a Fly position and an Idle position, and a second two-position throttle switch disposed on a second collective control stick, the second two-position throttle switch being movable between a Fly position and an Idle position.
An aircraft including a nacelle disposed at a fixed location relative a wing member; a proprotor housing coupled to the nacelle, the proprotor housing configured to selectively rotate between a horizontal orientation and a non-horizontal orientation; a door pivotably coupled to the proprotor housing; and a linkage to connect the door and the nacelle, the linkage configured to move with the door from a closed position when the proprotor housing is in a horizontal orientation to an open position when the proprotor housing is in a non-horizontal orientation. In some embodiments, there can be a hinge member for hingedly coupling the door to the proprotor and/or nacelle. In other embodiments, the door includes a flexure portion. In some embodiments, the nacelle includes a plurality of doors. In other embediments, proprotor includes a forward portion and a stationary aft portion; wherein the forward portion is configured to selectively pivot.
B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
B64D 29/02 - Power-plant nacelles, fairings, or cowlings associated with wings
18.
HYBRID PROPULSION DRIVE TRAIN SYSTEM FOR TILTROTOR AIRCRAFT
The present invention includes a hybrid propulsion system for an aircraft comprising: one or more turboshaft engines that provide shaft power and are capable of providing thrust; at least one of: one or more electrical generators or one or more hydraulic pumps connected to a shaft of the one or more turboshaft engines; and at least two rotatable nacelles, each nacelle housing at least one of: one or more electric motors or one or more hydraulic motors each connected to a proprotor, wherein the electric motor is electrically connected to the electric generator, or the hydraulic motor is connected to the hydraulic pump, respectively, wherein the proprotors provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight, and provide thrust whenever the aircraft is in forward flight.
B64D 27/00 - Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
19.
SYSTEM AND METHOD FOR FLAPERON AND/OR AILERON CONTROL
A roll control system controls roll control surfaces of an aircraft that are capable of causing the aircraft to perform a roll maneuver by respectively deflecting in upward and downward directions. The roll control system includes deflection limiter units for respectively limiting angles of deflection of the roll control surfaces, and further includes deflection rate limiter units for respectively limiting rates of deflection of the roll control surfaces. The deflection limiter unit limits the roll control surfaces to deflection distances and deflection rates based at least in part on the deflection direction of the roll control surfaces. For a given set of flight conditions, such as airspeed, if a roll control surface is deflecting upwardly, it is less limited by the roll control system in terms of deflection distance and deflection rate than if the roll control surface Is deflecting downwardly.
An aircraft rotor assembly includes a central hub, and rotor blades coupled to the hub for rotation with the hub about an axis. Each blade has a Lock number of approximately 5 or greater. A discrete hinge for each blade allows for out-of-plane motion. A lead-lag pivot for each blade formed by a flexure couples the associated blade to the hub. Each pivot is a radial distance from the axis and allows for in-plane lead-lag motion of the associated blade relative to the hub. Each pivot allows for in-plane motion from a neutral position of at least 1 degree in each of the lead and lag directions. Elastic deformation of the flexure produces a biasing force for biasing the associated blade toward the neutral position. The biasing force is selected to achieve a first in-plane frequency of greater than 1/rev for each blade.
In accordance with one embodiment of the present disclosure, a method for manufacturing a honeycomb core sandwich panel includes placing a thermoset facesheet in contact with a thermoplastic honeycomb core without using a separate adhesive and attaching the thermoset facesheet to the thermoplastic honeycomb core by using a curing profile comprising a temperature that is lower than a gel point temperature of the thermoset facesheet and higher than a softening point temperature of the thermoplastic honeycomb core.
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
B32B 27/08 - Layered products essentially comprising synthetic resin as the main or only constituent of a layer next to another layer of a specific substance of synthetic resin of a different kind
B32B 37/04 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the partial melting of at least one layer
22.
CROWNING OF A SPLINE IN A DIRECTION PERPENDICULAR TO A SPLINE TOOTH FACE
A drive shaft includes a plurality of external crowned spline teeth configured for transmitting torque in a drive system such that contact stress can remain substantially even as misalignments occur. The drive shaft can be manufactured by forming a groove in a drive shaft blank in a direction perpendicular to the side faces of the spline teeth being formed. The resulting spline teeth can have crowned side-wall surfaces that have equal crown drops along the height of the side walls of the spline teeth.
The present invention includes a rotor hub system, comprising: a teetering rotor hub disposed about a mast, the teetering rotor hub comprising: a first and a second yoke; each connected to a set of rotor blades, wherein the second set of rotor blades and the first set of rotor blades are disposed in a common plane, but the first and the second yoke do not come in contact.
B64C 27/82 - Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft
An engine cooling system for a rotorcraft includes an engine having an engine cooling circuit, a hydraulic pump powered by the engine to pump hydraulic fluid, and a hydraulic circuit in fluid communication with the hydraulic pump and the engine cooling circuit, the hydraulic circuit including at least one hydraulic-powered component. The hydraulic pump is adapted to pump the hydraulic fluid through both the hydraulic circuit and the engine cooling circuit, thereby cooling the engine.
A method for determining a shear property of a sample includes supporting the sample at three or more separate support locations about a periphery of a first surface of the sample in a testing fixture. The sample includes a second surface separated from the first surface by a thickness. The method includes supporting the sample with three or more clamps at the three or more separate support locations about the periphery. Each clamp includes a lower clamp member having a first chamfered surface and an upper clamp member having a second chamfered surface. A load is applied on the second surface of the sample with a load applicator in a direction orthogonal to the second surface. The method includes measuring shear testing data of the sample in response to applying the load, and determining, with a controller, a shear property of the sample from the measured shear testing data.
A soft-in-plane proprotor system for a tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system comprises a hub, and proprotor blades coupled to the hub to independently flap relative to the hub, and independently change pitch. A plurality of loop yokes coupling one of the proprotor blades with the hub and including first and second longitudinal sections extending between inboard and outboard arcuate sections. A bearing assembly disposed between the inboard and outboard arcuate sections of each loop yoke. Each bearing assembly includes a flapping bearing disposed generally within the inboard arcuate section and coupled to the hub, a lead-lag damper coupled to the hub, a centrifugal force bearing disposed generally within the outboard arcuate section, and a blade anchor positioned between the lead-lag damper and the centrifugal force bearing. The blade anchor is coupled to the respective proprotor blade inboard of the centrifugal force bearing.
B64C 11/06 - Blade mountings for variable-pitch blades
B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
A rotor hub assembly for a rotorcraft includes a yoke forming a bearing bore. The yoke has a teetering axis extending through the bearing bore. The rotor hub assembly includes a flapping bearing disposed in the bearing bore. The flapping bearing is operable to regulate teetering of the yoke about the teetering axis. The rotor hub assembly includes an axial spring abutting the flapping, thereby reducing movement of the flapping bearing along the teetering axis.
B64C 27/82 - Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft
F16F 1/40 - Springs made of material having high internal friction consisting of a stack of similar elements separated by non-elastic intermediate layers
28.
ROTORCRAFT FALL RESTRAINT PROTECTION ATTACH POINTS AND MECHANISM SYSTEMS
The present invention includes a safety apparatus and method for protecting users during maintenance operations for a rotorcraft comprising: at least one permanent, semi-permanent, or detachable safety bar, strap, fastener, hook, or loop that is attached or attachable to a rotorcraft, wherein the safety bar, strap, fastener, hook, or loop is positioned in an area or surface between a windshield of the rotorcraft and a tail boom of the rotorcraft and is connectable to a user safety device to provide fall protection from the area or surface.
A62B 35/00 - Safety belts or body harnesses; Similar equipment for limiting displacement of the human body, especially in case of sudden changes of motion
A method of manufacturing a door skin and a fuselage wall having a doorway and a member extending into the doorway for abutting the door includes placing a first sheet of uncured composite material on a mold plate to define the door and fuselage skin, disposing an insert over the first sheet overlapping a desired periphery of the door, placing a second sheet of uncured composite material on a peripheral portion of the insert and over the first sheet adjacent the peripheral portion of the insert to form the member, curing the sheets and bonding the sheets together adjacent the insert during the cure, removing the insert from between the sheets after cure, and separating the door skin from the wall skin after cure by moving a cutting tool through the first sheet and without penetrating the second sheet around the desired periphery of the door. An assembly for manufacturing the door skin and a fuselage wall is also discussed.
B29C 70/18 - Fibrous reinforcements only characterised by the structure of fibrous reinforcements using fibres of substantial or continuous length in the form of a mat, e.g. sheet moulding compound [SMC]
Wing stowage systems are typically associated with military aircraft having a large footprint and an extended, large tail section. Some aircraft have anhedral tail wings, however, problems with landing and ground clearance remain. The embodiments described herein provide an improved aircraft including a fuselage having a longitudinal axis extending through the fuselage front end and the fuselage rear end; a foldable wing located on the fuselage and being movable between a flight position wherein the wing is generally perpendicular to the longitudinal axis, and a stowed position wherein the wing is generally parallel to the longitudinal axis; and a pair of stabilizing wings having an anhedral orientation disposed on the fuselage.
A pylon assembly for a tiltrotor aircraft includes a rotor assembly operable to rotate between a generally vertical orientation, in a VTOL flight mode, and a generally horizontal orientation, in a forward flight mode, and having an intermediate orientation therebetween, in a conversion flight mode. The rotor assembly includes a proprotor operable to produce a slipstream. A wing extension, positioned outboard of the rotor assembly, has a minimal dimension and an outboard end. A winglet is coupled to the outboard end of the wing extension and has a minimal dimension. The wing extension and the winglet are operable to rotate generally with the rotor assembly such that the minimal dimensions of the wing extension and the winglet remain in the slipstream of the proprotor.
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
32.
TILTING DUCTED FAN AIRCRAFT GENERATING A PITCH CONTROL MOMENT
In some embodiments, an aircraft includes a fuselage having a forward portion and an aft portion. First and second ducted fans are supported by the forward portion of the fuselage. The first and second ducted fans are tiltable relative to the fuselage between a generally horizontal orientation, in a vertical takeoff and landing mode, and a generally vertical orientation, in a forward flight mode. A tailboom having an aft station extends from the aft portion of the fuselage. A cross-flow fan is disposed in the aft station of the tailboom and is operable to generate a pitch control moment.
B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
B64C 15/00 - Attitude, flight direction or altitude control by jet reaction
B64C 39/06 - Aircraft not otherwise provided for having disc- or ring-shaped wings
B64D 27/00 - Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
The present invention includes an air flow bypass for a tiltrotor engine comprising: a ram air inlet comprising bypass door(s) capable of at least partially or fully blocking a ram air flow through the ram air inlet; a barrier filter inlet positioned in a side, a bottom, and/or a top of a tiltrotor engine nacelle; a filter plenum; a selector duct comprising one or more openings; and one or more selector duct doors or covers over the one or more openings; wherein the barrier filter inlet, the filter plenum, the one or more openings in the selector duct, the selector duct, and an engine are in fluid communication and the bypass door(s) in the ram inlet are closed and the barrier filter inlet provides filtered air flow to the engine when the aircraft is in hover operations.
B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
B64D 29/00 - Power-plant nacelles, fairings, or cowlings
F02C 7/05 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
34.
AIRCRAFT WITH SELECTIVELY ATTACHABLE PASSENGER POD ASSEMBLY
In some embodiments, an aircraft includes a flying frame having an airframe, a propulsion system attached to the airframe and a flight control system operably associated with the propulsion system wherein, the flying frame has a vertical takeoff and landing mode and a forward flight mode. A pod assembly is selectively attachable to the flying frame such that the flying frame is rotatable about the pod assembly wherein, the pod assembly remains in a generally horizontal attitude during vertical takeoff and landing, forward flight and transitions there between.
B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64C 27/30 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with provision for reducing drag of inoperative rotor
B64D 1/22 - Taking-up articles from earth's surface
B64D 5/00 - Aircraft transported by aircraft, e.g. for release or reberthing during flight
An aircraft haying a vertical takeoff and landing fight mode and a forward flight mode. The aircraft includes an airframe and a versatile propulsion system attached to the airframe. The versatile propulsion system includes a plurality of propulsion assemblies. A flight control system is operable to independently control the propulsion assemblies. The propulsion assemblies are interchangeably attachable to the airframe such that the aircraft has a liquid fuel flight mode and an electric flight mode. In the liquid fuel flight mode, energy is provided to each of the propulsion assemblies from a liquid fuel. In the electric flight mode, energy is provided to each of the propulsion assemblies from an electric power source.
B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
Systems and methods are provided for statistically equivalent level of safety modeling. One method includes identifying sub-fleets within a fleet based upon usage profiles, determining a sub-fleet reliability value for each sub-fleet, determining a baseline fleet reliability for the fleet by combining the sub-fleet reliability values on a weighted basis, applying at least one credit to at least one sub-fleet, determining a post-credit sub-fleet reliability value for each sub-fleet based upon the at least one credit, determining a post-credit fleet reliability for the fleet by combining the post-credit sub-fleet reliability values on a weighted basis, comparing the baseline fleet reliability with the post-credit fleet reliability to identify a change in fleet reliability and determining whether the change in fleet reliability is within a predetermined threshold to validate the at least one credit.
The present invention includes an electric distributed propulsion for anti- torque modules for a helicopter and methods of use comprising: two or more generators connected to a main gearbox transmission; at least a first and a second plurality of variable speed motors connected to one or more fixed pitch blades to provide anti-torque thrust connected to the two or more generators, and at least a first and a second yaw control computer independently connected to each of the at least first and second plurality of variable speed motors, wherein each of the first and second yaw control computer serves as a primary and a backup yaw control computer to provide redundant control to both the first and second plurality of variable speed motors.
B64C 27/82 - Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft
B64C 11/46 - Arrangements of, or constructional features peculiar to, multiple propellers
38.
VARIABLE DIRECTIONAL THRUST FOR HELICOPTER TAIL ANTI-TORQUE SYSTEM
The present invention includes an anti-torque assembly for a helicopter comprising a plurality of fixed blade pitch motors mounted on one or more pivots on the tail boom of the helicopter, wherein the plurality of fixed blade pitch motors on the one or more pivots are adapted to be oriented substantially in-plane with a tail boom of a helicopter during a first mode of operation that comprises a hover mode and wherein the fixed blade pitch motors are adapted to be oriented substantially off-plane from the tail boom of the helicopter during a second mode of helicopter operation that is different from the first mode.
B64C 27/82 - Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft
B64C 11/46 - Arrangements of, or constructional features peculiar to, multiple propellers
39.
ANTI-TORQUE CONTROL USING MATRIX OF FIXED BLADE PITCH MOTOR MODULES
The present invention includes an a plurality of first variable speed motors arranged in a first matrix pattern and mounted on a tail boom of the helicopter; one or more fixed pitch blades attached to each of the plurality of first variable speed motors; and wherein a speed of one or more of the plurality of first variable speed motors is varied to provide an anti-torque thrust.
B64C 27/82 - Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft
B64C 11/46 - Arrangements of, or constructional features peculiar to, multiple propellers
A tiltrotor aircraft includes a fuselage, a wing member extending from the fuselage, an engine disposed relative to the wing member and a proprotor mechanically coupled to the engine. The proprotor includes a plurality of proprotor blade assemblies each including a spar and a sheath extending spanwise along the spar forming the leading edge of the proprotor blade assembly. The spar has a root section, a main section and a tip section. The spar has a generally oval cross section at radial stations along the main section and a first edge having a structural bias relative to a generally oppositely disposed second edge at the radial stations along the main section.
B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
An aircraft capable of vertical takeoff and landing, stationary flight and forward flight includes a closed wing that provides lift whenever the aircraft is in forward flight, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. The fuselage can have a rear module substantially disposed within a perimeter of the distributed airframe, and a front module removably connected to the rear module and substantially aligned with the longitudinal axis. One or more engines or motors are disposed within or attached to the closed wing, fuselage or spokes. Three or more propellers are proximate to a leading edge of the closed wing or the one or more spokes, distributed along the closed wing or the one or more spokes, and operably connected to the one or more engines or motors. The propellers provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight, and provide thrust whenever the aircraft is in forward flight.
B64C 39/06 - Aircraft not otherwise provided for having disc- or ring-shaped wings
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64C 27/30 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with provision for reducing drag of inoperative rotor
B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
B64D 27/02 - Aircraft characterised by the type or position of power plant
A rotor blade rotation system comprising a fold linkage (306) coupled to a rotating portion of a bearing plate (308a) and in mechanical communication with rotor blades (202), the fold linkage is positioned between the bearing plate and the rotor blade, an actuator is coupled to a non- rotating portion of the bearing plate (308b) to reposition the bearing plate from a first position to a second position such that the fold linkage pivots the rotor blades from a deployed position to a forward folded position. The rotation system is characterised in the tip of all the rotor blades are upstream from the hub (304) and the hub is upstream from the bearing plate when the rotor blades are in the forward folded position in contrast to backward folding rotor blades which may not be desirable for some aircraft designs.
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64C 27/30 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with provision for reducing drag of inoperative rotor
B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
B64C 39/06 - Aircraft not otherwise provided for having disc- or ring-shaped wings
The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.
B64C 39/06 - Aircraft not otherwise provided for having disc- or ring-shaped wings
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64C 27/30 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with provision for reducing drag of inoperative rotor
B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
B64D 27/02 - Aircraft characterised by the type or position of power plant
ABSTRACT The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors. Date Recue/Date Received 2020-11-18
B64C 39/06 - Aircraft not otherwise provided for having disc- or ring-shaped wings
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64C 27/30 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with provision for reducing drag of inoperative rotor
B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
B64D 27/02 - Aircraft characterised by the type or position of power plant
45.
METHOD OF MANUFACTURING A TILTROTOR WING STRUCTURE
A method of manufacturing a tiltrotor wing structure including providing a spar mold having a plurality of bores extending from an exterior surface of the mold to an interior surface of the mold, the plurality of bores corresponding to a plurality of primary coordination holes in a spar member, the spar mold having a periphery defined by a top edge, a bottom edge and outboard ends; selecting a plurality of resin impregnated plies to ensure that the plies continuously extend beyond the periphery of the spar mold; laying the plies in the spar mold; curing the plies in the mold to form a cured spar member that extends beyond the periphery of the spar mold, and accurately drilling a plurality of primary coordination holes in the cured spar member in the spar mold. The method reduces assembly steps, thereby reducing manufacturing fixtures and floor space.
B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
A method of making a composite skin for a tiltrotor aircraft includes providing a first skin in a mold, and providing honeycomb panels having an array of large cells onto the first skin. The method includes assembling the honeycomb panels along a longitudinal axis of the first skin to form a honeycomb core, positioning filler members between the honeycomb panels, and positioning filler members on the outboard ends of the honeycomb core. The method includes positioning a second skin onto the honeycomb core, and curing an adhesive to create a bond between the first skin, the honeycomb core, and the second skin to form the composite skin. The method provides sufficient compressive strength and support for a wing of the tiltrotor aircraft, while reducing the manufacturing time and labor associated with conventional methods which involve laying plies of hundreds of reinforcement strips made of various types, size, and orientations.
B64C 1/12 - Construction or attachment of skin panels
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
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
B32B 7/12 - Interconnection of layers using interposed adhesives or interposed materials with bonding properties
B64C 3/26 - Construction, shape, or attachment of separate skins, e.g. panels
A rib assembly for an aircraft wing including a rib web having a top and a bottom, the rib web includes a first laminate, a second laminate, and a honeycomb panel having an array of large cells disposed between the first laminate and the second laminate, each cell having a width of at least 1 cm; and a plurality of skin flanges for fixedly attaching the rib web to a skin of the wing, each skin flange has a base member having a first portion and a second portion and a vertical member extending from the base member. The rib assembly overcomes problems associated with conventional rib assemblies that require a large number of fasteners and support components, which limits fuel space in the wing.
An emergency lighting system (ELS) for an aircraft has a capacitor, a light emitting diode (LED) selectively powered by the capacitor, and at least one of a photoluminescent sign and a photoluminescent panel configured to receive light emitted from the LED.
H02J 9/02 - Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which an auxiliary distribution system and its associated lamps are brought into service
F21K 9/00 - Light sources using semiconductor devices as light-generating elements, e.g. using light-emitting diodes [LED] or lasers
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
F21K 2/00 - Non-electric light sources using luminescence; Light sources using electrochemiluminescence
F21V 23/00 - Arrangement of electric circuit elements in or on lighting devices
G09F 13/20 - Illuminated signs; Luminous advertising with luminescent surfaces or parts
An emergency lighting system (ELS) for an aircraft has a capacitor, at least one of an onboard power system and a ground power unit configured to charge the capacitor, and a light emitting diode (LED) selectively powered by the capacitor.
H02J 9/02 - Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which an auxiliary distribution system and its associated lamps are brought into service
F21K 9/00 - Light sources using semiconductor devices as light-generating elements, e.g. using light-emitting diodes [LED] or lasers
B64D 47/02 - Arrangements or adaptations of signal or lighting devices
F21V 23/00 - Arrangement of electric circuit elements in or on lighting devices
F21V 23/04 - Arrangement of electric circuit elements in or on lighting devices the elements being switches
G09F 13/20 - Illuminated signs; Luminous advertising with luminescent surfaces or parts
A method of manufacturing a flexible element configured for pressing against composite material received on a mold surface of a mold during cure, including placing a porous material over the mold surface, forming a sealed enclosure containing the mold surface and the porous material, infusing a curable liquid material such as silicone in liquid form into the enclosure under vacuum and through the porous material, curing the liquid material to form the flexible element, and opening the enclosure and disengaging the flexible element from the mold. In a particular embodiment, the flexible element is a pressure pad.
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
51.
MODULAR TOOLING FOR MANUFACTURING MULTI-CAVITY COMPOSITE STRUCTURES
A method of manufacturing a monolithic component having internal wall(s), including separately placing uncured composite material on a mold parts, placing the mold parts on a support plate with a portion of the uncured composite material extending between and in contact with the adjacent mold parts, interconnecting the adjacent mold parts through a connection allowing limited relative movement on the support plate along a direction corresponding to a thickness of the uncured composite material therebetween, biasing the adjacent mold part toward each other along the limited relative movement to provide a compressive force on the uncured composite material extending therebetween, and curing the composite material to obtain the monolithic component with each internal wall being formed between adjacent mold parts. The bias causes the adjacent mold parts to move toward each other as the thickness of uncured material extending therebetween reduces during curing. A tool assembly is also discussed.
B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
A method of manufacturing a self-supporting, monolithic fuselage body, including engaging peripheral mandrel sections around at least one central mandrel section, placing uncured composite material on the mold surface, curing the composite material on the mold surface, and sliding the central mandrel section(s) out of engagement with the peripheral mandrel sections and disengaging the peripheral mandrel sections from the cured composite material without collapsing the mandrel sections. The peripheral mandrel sections each include a shape-retaining core of a thermally insulating material and an outer layer on an outer surface of the shape-retaining core. The outer layer has a coefficient of thermal expansion within the range of variation of that of the coefficient of thermal expansion of the composite material. A mandrel for layup and cure of a predetermined composite material in the manufacture of a monolithic fuselage is also discussed.
B29C 70/48 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM]
One aspect of a method of manufacturing a honeycomb core includes positioning a first thermoplastic columnar cell adjacent a second thermoplastic columnar cell, modifying a thermoplastic property of the first thermoplastic columnar cell, wherein the modified thermoplastic property permits joining a circumferential surface of the first thermoplastic columnar cell to a circumferential surface of the second thermoplastic columnar cell. The method also includes joining the circumferential surface of the first thermoplastic columnar cell having the modified thermoplastic property to the circumferential surface of the second thermoplastic columnar cell resulting in the honeycomb core.
An aircraft monitoring system includes multiple wireless aircraft sensors and multiple meta sensors mounted on-board an aircraft. Each wireless aircraft sensor is configured to sense an aircraft parameter. Each meta sensor is associated with an aircraft sensor and is configured to determine a location or orientation on the aircraft of the aircraft sensor. A data acquisition system mounted on-board the aircraft and connected to the multiple aircraft sensors and the multiple meta sensors can perform aircraft monitoring operations based on the sensed aircraft parameters and on a location or orientation of the aircraft sensors.
One example of a rotorcraft blade control system includes a mechanical linkage to connect to a rotorcraft blade including a feather axis and a pneumatic muscle connected to the mechanical linkage. The system also includes a movement member connected to the mechanical linkage, the pneumatic muscle and the movement member to move the mechanical linkage to control movement of the rotorcraft blade on the feather axis. The pneumatic muscle can be a first pneumatic muscle and the movement member can be a second pneumatic muscle or a bias spring.
B64C 27/64 - Transmitting means, e.g. interrelated with initiating means or means acting on blades using fluid pressure, e.g. having fluid power amplification
A method of repairing a core stiffened structure, including removing a damaged portion of the core stiffened structure; bonding a shelf onto a first core member; bonding a second core member to a shelf; and securing a skin patch over the second core member.
B29C 73/14 - Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass using preformed elements using elements composed of two parts joined together after having been placed one on each side of the article
One aspect of a process of inspecting a joint that connects two parts includes directing an ultrasonic beam from an ultrasonic beam transmitter at a joint that connects two parts, the ultrasonic beam forming an angle between at least 14 degrees and at most 21 degrees with a joint axis of the joint, wherein the ultrasonic beam passes through a joint thickness of the joint. The process also includes determining a quality of the joint based, in part, on a difference between a strength of the ultrasonic beam directed at the joint and a strength of a portion of the ultrasonic beam that passed through the joint thickness.
One aspect of a process to inspect a composite component includes traversing multiple ultrasonic probe array portions on respective multiple component surfaces of the composite component. The multiple component surfaces are either separate from or at angles to each other. The process includes simultaneously passing an ultrasonic signal into the multiple component surfaces through the multiple ultrasonic probe array portions. The process also includes receiving a response to the ultrasonic signal through the multiple ultrasonic probe array portions.
A rotorcraft autopilot system includes a series actuator connecting a cockpit control component to a swashplate of a rotorcraft, the series actuator to modify a control input from the cockpit control component to the swashplate through a downstream control component. The rotorcraft autopilot system also includes a differential friction system connected to the cockpit control component, the differential friction system to control the series actuator to automatically adjust a position of the cockpit control component during rotorcraft flight based, in part, on a flight mode of the rotorcraft.
B64C 27/57 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
B64C 13/18 - Initiating means actuated automatically, e.g. responsive to gust detectors using automatic pilot
Some examples of techniques to cost-effectively embed fiber optic cables in laminate structures and to terminate the fiber optic cables on the surface of the laminate for robust and easily-repairable connections can be implemented in rotorcraft composites. To position a cable in the rotorcraft composite, a length of a fiber optic cable is embedded between layers of a composite rotorcraft material. The length of the fiber optic cable is oriented in a substantially S-shape between the layers. An end of the length of the substantially S-shaped fiber optic cable is extended to an edge of the composite rotorcraft material. The end of the length of the substantially S-shaped fiber optic cable is terminated at the edge of the composite rotorcraft material in either a storage area or easily machinable embedded connection.
G02B 6/46 - Processes or apparatus adapted for installing optical fibres or optical cables
B29C 70/68 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers
A convertible helicopter ring member includes a ring member and a drive mechanism. The drive mechanism orients the ring member substantially in-plane with a tail rotor of a helicopter during a first mode of helicopter operation and orients the ring member substantially off-plane with the tail rotor of the helicopter during a second mode of helicopter operation that is different from the first mode.
B64C 27/82 - Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft
B64C 9/00 - Adjustable control surfaces or members, e.g. rudders
A rotorcraft actuator monitoring system to monitor leakage past dynamic rotorcraft actuator seals of a rotorcraft actuator includes a body member and a fluid level indication housing attached to the body member. The body member is mounted to surround a dynamic rotorcraft actuator seal that seals fluid in a rotorcraft actuator, where the body member captures fluid that leaks past the dynamic rotorcraft actuator seal. The fluid level indication housing collects the fluid captured by the body member and indicates that a predetermined volume of fluid that leaked past the dynamic rotorcraft actuator seal has been collected.
B64C 13/40 - Transmitting means with power amplification using fluid pressure
B64C 27/64 - Transmitting means, e.g. interrelated with initiating means or means acting on blades using fluid pressure, e.g. having fluid power amplification
F15B 19/00 - Testing fluid-pressure actuator systems or apparatus, so far as not provided for elsewhere
F15B 21/00 - Common features of fluid actuator systems; Fluid-pressure actuator systems or details thereof, not covered by any other group of this subclass
G01M 3/04 - Investigating fluid tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point
G01M 3/24 - Investigating fluid tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point using infrasonic, sonic, or ultrasonic vibrations
A variable state planetary shifting transmission can include an input shaft, an output shaft; and a planetary system having a sun gear associated with the input shaft, a planetary carrier, and a ring gear associated with a ring housing. The transmission can include an overrunning clutch operably coupled to the planetary carrier. The transmission can include a clutch assembly coupled to the planetary carrier. The transmission is capable of changing the speed ratio between the input shaft and the output shaft by selective engagement of the clutch assembly against the ring gear which can cause either the freeing or locking of the planetary carrier by the overrunning clutch.
F16H 3/58 - Gearings having only two central gears, connected by orbital gears with sets of orbital gears, each consisting of two or more intermeshing orbital gears
B64D 35/00 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
F16H 63/24 - Final output mechanisms therefor; Actuating means for the final output mechanisms each of the final output mechanisms being moved by only one of the various final actuating mechanisms
One example of a retention system for a rotorcraft pedal assembly includes an insertion member, an axial retention member, and a transverse retention member. The insertion member, which is inserted through a side of a pedal assembly, includes a spring compressible against the side of the pedal assembly in response to the insertion member being inserted through the side. The axial retention member receives and retains the insertion member on an opposing side of the pedal assembly. The transverse retention member is inserted through a passage formed in the axial retention member to secure the axial retention member against the side of the pedal assembly.
G05G 1/34 - Double foot controls, e.g. for instruction vehicles
B64C 27/56 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated
F16B 21/12 - Means without screw-thread for preventing relative axial movement of a pin, spigot, shaft, or the like and a member surrounding it; Stud-and-socket releasable fastenings without screw-thread by separate parts with locking-pins or split-pins thrust into holes
This description relates to a strapped windshield assembly for a rotorcraft. In some implementations, the rotorcraft includes an airframe, a windshield, and a plurality of independent straps connected to the airframe and the windshield, the straps operative to move independently with respect to one another. The independent movement of the straps allow relative movement of portions of the windshield in response to a strike. In some implementations, the straps are spaced every 4-6 inches along an edge of the windshield. In some implementations, the straps are over an edge of the windshield. The straps can have a modulus of elasticity of 8-12 millions of pounds per square inch (MSI). The windshield can include polycarbonate material.
B64D 7/00 - Arrangement of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
A damper for a rotor hub for a rotorcraft can include a housing, a piston resiliently coupled to the housing with a first elastomeric member and a second elastomeric member, a plurality of conical members, a fluid, and an orifice. The conical members may be coupled between the housing and the piston in a compressive state, such that a relative motion between the piston and the housing causes the conical members to flex by a compressive load change produced by the relative motion between the piston and the housing. The elastomeric members, the piston, the housing, and the conical members form inner chambers between the conical members and the piston and outer chambers between the conical members and the housing, each comprising an at least partially conical shape, Flexure of the conical members pumps the fluid through the orifice.
A control system having a series of control loops for determining the upper and lower cyclic limit increments due to the contribution of collective pitch in rotorcraft based at least on nacelle angle and airspeed.
B64C 27/57 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
B64C 19/00 - Aircraft control not otherwise provided for
B64C 27/52 - Tilting of rotor bodily relative to fuselage
According to one embodiment, a method of managing pilot and copilot control of engine power in an aircraft includes receiving, from a first pilot input device, a first signal representative of a pilot selection of an increase power position or a decrease power position and receiving, from a second pilot input device, a second signal representative of a pilot selection of an increase power position or a decrease power position. One of the first signal and the second signal is prioritized. An aircraft engine is then instructed to change power output based on the prioritized signal.
According to one embodiment, a rotor brake includes a first braking surface having an opening therethrough, a second braking surface adjacent to the first braking surface, and an impeller disposed between the first and second braking surfaces such that rotation of the impeller pulls fluid through the opening of the first braking surface and expels the fluid out through a gap between the first and second braking surfaces.
A bearing can include a ball member, a race, and a liner located on an interior surface of the race, the liner having a first surface bonded to an interior surface of the race, the liner having a second surface that is adjacent to the ball member. The bearing also includes a wafer having a wear surface that is aligned with the second surface of the liner, the wafer being an electrically conductive member. Operational wear of the liner can be calculated by comparing a measured resistance of the wafer to an original known resistance of the wafer.
In some aspects, a heat treatment process is described for precipitation hardening steel. The heat treatment process can include a solution treatment for a precipitation hardening steel part. The solution treatment includes heating the precipitation hardening steel part to an austenitizing temperature. The heat treatment process can also include a quenching or cooling treatment, in which the precipitation hardening steel part is cooled to a martensitizing temperature. The heat treatment process can also include an aging treatment, in which the precipitation hardening steel part is heated to a temperature of 1000 °F and held at that temperature for five or more hours until a fracture toughness of the precipitation hardening steel part is greater than 120 ksi.sqroot.in.
In some aspects, a master cylinder assembly for vertical lift aircraft is configured to move pressurized fluid through a conduit in response to applied movement of an input lever. A low pressure relief valve can be connected to a first conduit to limit pressure to a low level. An isolation valve can be connected to the first conduit and configured to isolate the low pressure relief valve from the conduit when engaged. A high pressure relief valve can be connected to a second fluid conduit to limit pressure to a high level. In some aspects, a rotor brake actuator is fluidly connected to the first conduit and the second conduit and configured to engage a rotor brake in response to hydraulic fluid pressure.
B60T 11/10 - Transmitting braking action from initiating means to ultimate brake actuator without power assistance or drive or where such assistance or drive is irrelevant transmitting by fluid means, e.g. hydraulic
The rotor hub can include a rotor blade; a rotor yoke; a grip member having an inboard portion, an upper extension, and a lower extension; and a rotor blade having a root end coupled to the upper extension and the lower extension of the grip member with a first bolt, a second bolt, and a third bolt. The first bolt is located on a spanwise axis of the rotor blade. The second bolt is offset from the spanwise axis by a first chordwise distance and is offset from the first bolt by a first spanwise distance. The third bolt is offset from the spanwise axis by a second chordwise distance and is offset from the first bolt by a second spanwise distance.
A composite assembly has a composite core material substantially in abutment with an inner profile of an outer spar component comprising thickness variations as measured along the outer spar component inner profile, composite skins located on the composite core material, an inner spar component, and an adhesive disposed between the outer spar component and the inner spar component. The inner spar component includes an inner spar component outer profile substantially complementary to the outer spar component inner profile. The inner spar component is at least partially enveloped by the outer spar component and is substantially in abutment to the outer spar component inner profile. The outer spar component is relatively C- shaped and comprises folded ends that abut the composite skin of the composite assembly, the thickness variations including the folded ends. Undesirable void spaces and/or crushing of portions of the composite assembly in the mold may be avoided.
A quill shaft is configured for transferring torque and accepting misalignments between a fixed gearbox and a rotatable spindle gearbox in a propulsion system of a tiltrotor aircraft, the quill shaft includes a first splined portion configured for coupling to an output gear of the fixed gearbox, and a second splined portion configured for coupling to an input gear of the spindle gearbox. The spindle gearbox includes a rotor mast associated therewith, the spindle gearbox being rotatable so that the tiltrotor aircraft can selectively operate in a helicopter mode and airplane mode. An interior portion of the quill shaft includes a feature attachable to a removal tool.
B64D 35/00 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
F16H 1/26 - Special means compensating for misalignment of axes
76.
SYSTEM AND METHOD OF POST-CURE PROCESSING OF COMPOSITE CORE
A method of cutting a wafer of composite core from a bulk composite core includes stabilizing the bulk composite core with a fixture, the bulk composite core having a plurality of tube members. The method also includes cutting through each of the tube members to create the wafer while the bulk composite core is stabilized by the fixture.
A method of joining a first bulk composite core and a second bulk composite core by applying an adhesive to a surface network of the first bulk composite core; inserting a plurality of mandrels into a plurality of cell members of the first bulk composite core and a plurality of cell members of the second composite core, thereby aligning the cell members of the first bulk composite core to the cell members of the second bulk composite core; pressing the respective surface networks of the first bulk composite core and the second bulk composite core together with the adhesive located therebetween; and curing the adhesive.
A flight control system uses a governor configured to regulate the speed of a rotor in the aircraft through collective pitch control of a rotor blade, and a limiter configured to selectively remove the threshold limit of the governor when the collective pitch control exceeds a threshold limit, so as to permit a pilot full command of the collective above the threshold limit. The threshold limit is selectively removed and phased back in to provide temporary pilot control to "cushion" landing of an aircraft when an engine has failed.
B64C 27/57 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
A flight control system uses a governor configured to regulate the speed of a rotor in the aircraft through collective pitch control of a rotor blade. The governor has a threshold limit relating to the maximum pitch angle of the rotor blade. A symmetric collective pitch is produced from a power lever and a collective gain.
B64C 27/57 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust
A valve assembly for an engine, the valve assembly can include a housing; an in-flow port configured for connection with a drain line; a first out-flow port configured for connection with a fuel line; a second out-flow port configured for connection with a disposal line; and a passageway that is rotatable with a handle, the passageway being operable to redirect a flow of a fluid between the fuel line and the disposal line. The handle is configured to impede an attachment of the fluid source to a water wash connection when the passageway is in a position to direct the flow of the fluid from the drain line to the fuel line.
F02C 7/232 - Fuel valves; Draining valves or systems
B64D 37/00 - Arrangements in connection with fuel supply for power plant
F16K 11/02 - 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
A fastening assembly includes a body and a retaining device. The retaining device is secured to the body for placement along a surface. The body is configured to flex between a relaxed state and a compressed state. The body is compressed between two external surfaces in a compressed state to maintain the alignment and position of the retaining device without the fastener. The flexure of the body causes the body to exert an outward spring force against the external surfaces sufficient to maintain the location of the retaining devices before insertion of a fastener. The fastening assembly includes the fastener for insertion into the retaining device.
A damper includes a housing that forms a fluidly sealed cavity for receiving a fluid therein. The fluid is configured to change fluid properties as electrical energy is induced. An electrical subsystem provides electrical energy to the fluid, which is monitored with a control subsystem. The method includes inducing the fluid with electrical energy to change the dampening effects of the damper in real time.
F16F 13/26 - Units comprising springs of the non-fluid type as well as vibration-dampers, shock-absorbers, or fluid springs comprising both a plastics spring and a damper, e.g. a friction damper characterised by adjusting or regulating devices responsive to exterior conditions
F16F 9/18 - Devices with one or more members, e.g. pistons, vanes, moving to and fro in chambers and using throttling effect involving only straight-line movement of the effective parts with a closed cylinder and a piston separating two or more working spaces therein
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
F16F 13/16 - Units of the bushing type specially adapted for receiving axial loads
An apparatus is disclosed includes an active vibration isolation system that includes a vibration isolator, a dual fluid pump in fluid communication with the vibration isolator and a hydraulic system, wherein the dual fluid pump is configured to segregate a tuning fluid from a hydraulic fluid and an electric-hydraulic servo valve in fluid communication with the dual fluid pump.
F16F 9/32 - Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium - Details
B64D 27/00 - Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
F16F 9/16 - Devices with one or more members, e.g. pistons, vanes, moving to and fro in chambers and using throttling effect involving only straight-line movement of the effective parts
A method of wrapping a plurality of mandrels with a composite material can include rotating each mandrel at a rotational speed; translating each mandrel at a translation speed; positioning each mandrel back to back such that an aft face of a preceding mandrel is approximate to a forward face of a trailing mandrel; and sequentially wrapping each mandrel with the composite material in a helical orientation.
B29C 53/50 - Bending and joining, e.g. for making hollow articles by bending sheets or strips at right angles to the longitudinal axis of the article being formed and joining the edges for articles of indefinite length, i.e. bending a strip progressively using internal forming surfaces, e.g. mandrels
85.
SYSTEMS AND METHODS OF CONSTRUCTING COMPOSITE ASSEMBLIES
A method of constructing a cured composite assembly includes positioning a composite assembly within a bonding tool, wherein the composite assembly comprises an uncured composite spar and a skin and performing a curing cycle on the composite assembly to simultaneously cure the uncured composite spar and bond the skin to the cured composite spar.
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
A method of manipulating a thin-walled structure includes providing a thin- walled structure in a first unconstrained configuration, constraining the thin-walled structure to a first constrained configuration in which a first feature of the thin-walled structure is spatially located relative to the a second feature of the thin-walled structure in a predetermined manner, wherein an open volume of the thin-walled structure is constrained to maintain a predetermined open volume shape, and machining the thin-walled structure to a second constrained configuration in which the first feature of the thin-walled structure remains spatially located relative to the second feature of the thin-walled structure in the predetermined manner.
B21D 47/00 - Making rigid structural elements or units, e.g. honeycomb structures
B23P 15/00 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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
87.
LOW SHEAR MODULUS TRANSITION SHIM FOR ELASTOMERIC BEARING BONDING IN TORSIONAL APPLICATIONS
A bearing assembly comprises a bearing, a shim disposed within the bearing, and a component disposed within the shim. The shim comprises a first material, the component comprises a second material, and the first material has an elastic modulus value that is lower than an elastic modulus value of the second material. An apparatus comprises an elastomeric bearing, a fiberglass shim, and a steel spindle that is connected to the elastomeric bearing through the shim. A method for reducing strain in an adhesive layer that connects a bearing to a component comprises selecting a shim material having an elastic modulus value that is less than an elastic modulus value of the component and providing instructions to connect the component to the shim by placing the adhesive layer between an outer surface of the component and an inner surface of the shim.
A series battery start controller for starting an aircraft turbine engine and method thereof is provided, wherein the battery series start controller connects two batteries in series when an aircraft engine starter is engaged to provide a higher voltage to start the aircraft engine and to provide adequate operational voltage to aircraft engine instruments and other aircraft electrical systems, and wherein the battery series start controller reconnects the batteries in parallel when the electrical load drawn by the starting aircraft engine decreases and the supplied voltage to the aircraft rises to a predetermined threshold.
A bimetallic shaft for use in gearbox applications wherein the member of shaft that protrudes from the gearbox is designed and constructed from a corrosion- resistant metallic compound to prevent corrosion and wear to exposed shaft material. A gearbox comprising a bimetallic shaft having a corrosion-resistant material on the portion of the bimetallic shaft that protrudes from a gearbox housing, wherein a gearbox shaft seal radially surrounds the bimetallic shaft. A method of providing a bimetallic gearbox shaft comprising: a first shaft member having a first shaft axis, a second shaft having a second shaft axis with the first and second shaft members being made from different materials, and a joint that permanently affixes the first shaft member to the second shaft member such that the first shaft axis is aligned with the second shaft axis. The first shaft member may be formed from a non-corrosion-resistant material and the second shaft member may be formed from a corrosion-resistant material.
A rotor blade has a spanwise axis, a root comprising an anchor having an anchor surface configured to form at least one of a normal angle relative to the spanwise axis and an acute angle relative to the spanwise axis, and a selectively removable tip comprising a connector having a connector surface configured to complement the anchor surface.
The system for adaptively governing a speed of a rotor assembly in an aircraft can include a processor configured for comparing receivable data to limit data in an algorithm and subsequently making one or more commands that affect the speed of the rotor assembly, the algorithm being configured for analyzing power available during operation of the aircraft. The method can include calculating a first power available by comparing an actual transmission torque to a transmission torque limit; calculating a second power available by comparing an actual engine exhaust temperature to an engine exhaust temperature limit; and comparing the first power available to the second power available.
A method of making a composite core can include configuring a plurality of mandrels to have a desired thermal expansion characteristic, placing a composite material around each mandrel, placing the plurality of mandrels in a tool, the tool being configured to constrain the plurality of mandrels as the mandrels experience a thermal expansion, heating the mandrels so that the mandrels thermally expand, thereby applying a pressure to the composite material during a cure cycle, and then cooling and separating the mandrels from the composite core. The mandrel is configured as an internal form for making a tube member of a composite core.
A method of manufacturing a composite core including wrapping each of a plurality of mandrels with a composite material and stacking the plurality of mandrels wrapped with the composite material in a tool. A heated fluid may be moved through an interior of the plurality of mandrels to controllably heat the composite material in a curing process. A pressure may be controllably applied to the tool with a bladder during a curing process. A tooling system for manufacturing a composite core is also discussed.
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 70/08 - Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, with or without non-reinforced layers
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
C08J 5/12 - Bonding of a preformed macromolecular material to the same or other solid material such as metal, glass, leather, e.g. using adhesives
A method of manufacturing a composite core can include: wrapping a mandrel in a mandrel wrapping process by securing a mandrel with a winding jig; orienting the composite material at a wrap angle to the mandrel; and depositing the composite material around a circumference of the mandrel. The method can further include assembling the wrapped mandrels in a tool and applying a pressure to the composite material during a curing cycle.
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 63/12 - Lining or sheathing, i.e. applying preformed layers or sheathings of plastics; Apparatus therefor using sheet or web-like material by folding, winding, bending or the like by winding spirally
95.
BRUSHLESS ALTERNATOR FOR HELICOPTER TRANSMISSION INSTALL
A system and method to converting mechanical rotational energy of an aircraft input shaft of a transmission to electrical energy. The system includes an alternator having an inductor carried by the aircraft transmission and a magnet carried by the aircraft input shaft. The input shaft rotates the magnet in relation to the inductor, which in turn converts the mechanical rotational energy to electrical energy.
A system and method to change a spring rate of a damper in real time. The damper includes a housing having an inner surface that forms a cavity. An elastomeric material is disposed within the cavity and fixedly attached to the inner surface of the housing. A first chamber is formed by a first end of the elastomeric material and the inner surface of the housing. The method includes restricting movement of the elastomeric material by regulating the pressure within the first chamber, which in turn changes the spring rate of the damper.
F16F 1/387 - Springs made of material having high internal friction with a sleeve of elastic material between a rigid outer sleeve and a rigid inner sleeve or pin comprising means for modifying the rigidity in particular directions
F16F 7/12 - Vibration-dampers; Shock-absorbers using plastic deformation of members
F16F 13/16 - Units of the bushing type specially adapted for receiving axial loads
F16F 13/20 - Units comprising springs of the non-fluid type as well as vibration-dampers, shock-absorbers, or fluid springs comprising both a plastics spring and a damper, e.g. a friction damper the damper being a fluid damper, e.g. the plastics spring not forming a part of the wall of the fluid chamber of the damper characterised by comprising also a pneumatic spring
97.
AUTOMATED DIAGNOSTIC INSPECTION OF MECHANICAL CONTROLS
A system and method to diagnosis an actuator of a flight control system. The system and method includes interfacing a diagnostic computer to the flight control system, commanding movement of an actuator with the diagnostic computer via the flight control system, measuring performance of the actuator via the diagnostic computer, and comparing the measured performance of the actuator with allowable performance values.
A rotor system has a rotor (302), an axis of rotation about which the rotor (302) may be rotated, a linkage system (310) having a first adjustable length portion (210) and a second adjustable length portion (212), wherein the second adjustable length portion (212) is configured to provide a relatively finer adjustment of an overall effective length of the linkage system (310) as compared to the first adjustable length portion (210) and wherein the rotor (302) is configured to rotate about the axis in response to changing the overall effective length of the linkage system (310).
A cross tube for a helicopter skid landing gear, including a monolithic metallic tube having a central portion extending transversely between two end portions with longitudinal central axes of the central portion and of the end portions being located in a plane, where the central portion has inner and outer heights, the end portions each have inner and outer heights, and the inner and outer heights of one of the central portion and the end portion are respectively greater than the inner and outer heights of the other of the central portion and the end portion. A skid tube with two portions with cross-sections having one or both of different orientations with respect to one another and different dimensions with respect to one another, and a method of forming a structural tube for a helicopter skid landing gear are also provided.
The cooling system of the present disclosure is configured to promote heat transfer in a gearbox. The system can include a container for housing a gas, the gas having a sufficient percentage of helium so that once the gas is introduced into the gearbox, the helium increases heat transfer from the heat generating components of the gearbox. The method of the present disclosure can include selectively introducing the helium gas into the gearbox.
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