Methods and systems for performing a validation process on a part to be process are provided. An identifier associated with the part is received. A listing of at least one automated process based on the identifier is displayed. An indication of a selected automated process from the listing is received. First instructions are transmitted to an automated process device for performing an automated processing program in accordance with the selected automated process. Processing results associated with the part are received from the automated process device. Second instructions are transmitted to a validation process device for performing a validation program in accordance with a validation process associated with the selected automated process. Validation results associated with the part are received from the validation process device. The processing results and the validation results are stored in association with the identifier.
A rotor system is provided in one example embodiment and may include a rotor duct; at least one rotor blade, wherein the at least one rotor blade comprises a tip end; and a multi-material tip extension affixed at the tip end of the at least one rotor blade, wherein the multi-material tip extension comprises an inboard portion fabricated from a first material and an outboard portion fabricated from a second material, wherein the second material is different than the first material.
One embodiment is a system including a component for installation on a vehicle comprising a central maintenance computer (“CMC”); a configuration/maintenance module (“CMM”) associated with the component and including memory for storing component information, a sensor for detecting a condition and generating data indicative thereof; a microprocessor for processing the sensor data and updating the component information with the processing results; and a communications interface between the CMM and the CMC. The system further includes a remaining useful life (“RUL”) module associated with the component that periodically updates an RUL, the RUL module periodically updating an RUL value for the component and communicating the updated RUL value to the CMM for storage in the memory. The CMC communicates with the CMM to update the component information included in the memory based on information input to the CMC by a user or changes in a condition of the vehicle.
G07C 5/00 - Registering or indicating the working of vehicles
B64F 5/60 - Testing or inspecting aircraft components or systems
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
A bonded part includes a first surface facing toward a second surface, and a cured adhesive between the first and second surfaces defining a bond line. A surface structure on the first surface is within the bond line and has surface protrusions arranged in a pattern. Each surface protrusion protrudes outwardly from a first end at the first surface to a second end adjacent to the second surface. A thickness of the surface protrusions is substantially equal to the thickness of the bond line. The cured adhesive extends around the surface protrusions. The thickness of the bond line between the first and second surfaces is substantially constant along the bond line, and is greater than a thickness of the cured adhesive between the second ends of the protrusions and the second surface.
B32B 3/30 - 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 layer with cavities or internal voids characterised by a layer formed with recesses or projections, e.g. grooved, ribbed
B32B 7/12 - Interconnection of layers using interposed adhesives or interposed materials with bonding properties
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
B32B 15/14 - Layered products essentially comprising metal next to a fibrous or filamentary layer
B32B 37/12 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
One embodiment is a bearing carrier assembly including a circular shield having top and bottom surfaces; and a number of bearing separators integrated with the bottom surface of the shield, wherein each pair of bearing separators defines a receptacle for receiving and retaining a bearing therewithin and wherein the shield blocks the received bearings from debris and retains lubricant around the received bearings. Each of the bearing separators may include a spacer element for separating adjacent ones of the bearings. The bearing carrier assembly may be made up of a number of carrier sections that interconnect to form the bearing carrier assembly.
F16C 19/16 - Bearings with rolling contact, for exclusively rotary movement with bearing balls essentially of the same size in one or more circular rows for both radial and axial load with a single row of balls
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
B64C 27/20 - Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
In some examples, an aircraft comprises a motorized module. The motorized module comprises a motor and a first coil. The motor is to operate equipment onboard the aircraft and generates vibrations during operation. The first coil is operable to wirelessly transmit power to a separate module onboard the aircraft based on electromagnetic induction between the first coil and a second coil in a separate module, and wirelessly transfer data with the separate module via the second coil based on the electromagnetic induction, the data being associated with the motor. A gap separates the motorized module and the separate module. The gap isolates the separate module from the vibrations.
B64D 31/14 - Transmitting means between initiating means and power plants
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
H02J 50/10 - Circuit arrangements or systems for wireless supply or distribution of electric power using inductive coupling
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
10.
Assembly fixture with anisotropic thermal properties
In one embodiment, an assembly fixture may include a base structure including a plurality of strands of a fiber-reinforced thermoplastic material comprising a thermoplastic embedded with a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is aligned within each strand of the plurality of strands, and wherein the base structure further comprises an anisotropic thermal expansion property based on an orientation of the plurality of reinforcement fibers within the base structure, The assembly fixture may further include a plurality of fastening structures coupled to the base structure, wherein the plurality of fastening structures is configured to fasten a plurality of components of a composite structure for assembly using a heated bonding process.
B29C 70/52 - Pultrusion, i.e. forming and compressing by continuously pulling through a die
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 33/38 - 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 characterised by the material or the manufacturing process
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
B29C 65/78 - Means for handling the parts to be joined, e.g. for making containers or hollow articles
B29C 70/54 - Component parts, details or accessories; Auxiliary operations
B29K 105/10 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of continuous length, e.g. cords, rovings, mats, fabrics, strands or yarns oriented
B29K 105/14 - Condition, form or state of moulded material containing reinforcements, fillers or inserts of short lengths, e.g. chopped filaments, staple fibres or bristles oriented
A method for generating a simulation model to evaluate a flight control system including determining at least one high level requirement for an aircraft flight system during a non-automated engineering process; generating at least one specification of the high level requirement; generating a model computer-readable program code based on the at least one specification; executing the model computer-readable program code to generate a model code unit; executing the model code unit to generate a procedure document; executing the model code unit to perform a simulation method to generate a bench test computer-readable program code: executing the bench test computer-readable program code on a bench test computing device to generate a simulation output; and comparing the simulation output to the at least one specification of the high level requirement to generate a pass or fail result.
G06F 30/20 - Design optimisation, verification or simulation
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
In an embodiment, a method includes monitoring environmental conditions via a plurality of sensors positioned in proximity to a vehicle. The method also includes receiving, from one or more of the plurality of sensors, a first measured value of a first environmental variable and at least one additional measured value of at least one additional environmental variable. In addition, the method includes automatically determining, via a machine-learning model, a first expected value of the first environmental variable given the at least one additional measured value of the at least one additional environmental variable. Furthermore, the method includes automatically generating a storage decision in relation to the first measured value based, at least in part, on an evaluation of the first measured value relative to the first expected value. Additionally, the method includes causing execution of the storage decision at least with respect to onboard storage of the vehicle.
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
H03M 7/30 - Compression; Expansion; Suppression of unnecessary data, e.g. redundancy reduction
H04L 29/08 - Transmission control procedure, e.g. data link level control procedure
H04W 4/48 - Services specially adapted for particular environments, situations or purposes for vehicles, e.g. vehicle-to-pedestrians [V2P] for in-vehicle communication
An apparatus is described and in one embodiment includes a first portion comprising an inner diameter, a first outer diameter, and a first length and a second portion, wherein the first portion and the second portion are integrally connected together, the second portion comprising the inner diameter, at least one second outer diameter, and a second length. The embodiment further includes a flange comprising a contact surface, wherein the inner diameter of the first portion and the second portion provides a hollow pathway through the apparatus.
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
G01L 19/00 - MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE - Details of, or accessories for, apparatus for measuring steady or quasi-steady pressure of a fluent medium insofar as such details or accessories are not special to particular types of pressure gauges
16.
System and method for selectively modulating the flow of bleed air used for high pressure turbine stage cooling in a power turbine engine
A method for selectively modulating bleed air used for cooling a downstream turbine section in a gas turbine engine. The method including: measuring an engine and/or aircraft performance parameter by an engine sensor device; comparing the engine and/or aircraft performance parameter to a performance threshold; determining a bleed trigger condition, if the engine and/or aircraft performance parameter crosses the performance threshold; determining a non-cooling condition, if the engine and/or aircraft performance parameter is below the performance threshold; actuating a flow control valve to an open position, in response to the bleed trigger condition, so that bleed air is extracted from the compressor section and flowed to the downstream turbine section; and terminating, in response to the non-cooling condition, the flow of the bleed air to the downstream turbine section of the engine by actuating the flow control valve to a closed position.
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
F01D 17/04 - Arrangement of sensing elements responsive to load
F01D 17/06 - Arrangement of sensing elements responsive to speed
F01D 17/08 - Arrangement of sensing elements responsive to condition of working fluid, e.g. pressure
F02C 6/08 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
B64F 5/60 - Testing or inspecting aircraft components or systems
B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
An exemplary liquid tank level measurement system includes a tank having a wall, an accelerometer attached to the wall and configured to measure a vibration in the wall, and an instrument electronically connected to the accelerometer, the instrument configured to communicate a liquid level condition responsive to a vibration measurement received from the accelerometer.
One embodiment is a system comprising fuel tank comprising a pressure vessel for storing fuel for a vehicle, the fuel tank disposed within a fuselage of the vehicle and extending a majority of a length of the fuselage, wherein a center of gravity of the fuel tank is substantially aligned with a center of gravity of the fuselage. The fuel tank may be disposed within the fuselage such that the fuel tank bears at least a portion of a load borne by the fuselage. Alternatively, the fuel tank may be disposed within the fuselage such that the fuel tank is isolated from loads borne by the fuselage. In certain embodiments, the fuel tank comprises a filament wound pressure vessel.
An inboard beam includes a body having an upper flange and a lower flange coupled thereto. The upper flange includes a first upper inboard aperture and an upper outboard aperture formed therein. The lower flange includes a first lower inboard aperture and a lower outboard aperture formed therein. An upper beam fitting is coupled to the upper flange and lower beam fitting is coupled to the lower flange. The upper beam fitting includes a first upper inboard post. The upper beam fitting includes an upper outboard post extending parallel to the inboard post. The lower beam fitting includes a first lower inboard post. The lower beam fitting includes a lower outboard post extending parallel to the lower inboard post.
A method of increasing a stability speed of a tiltrotor aircraft includes pivoting a rotor assembly having at least three rotor blades from a first position for operating the tiltrotor aircraft in a helicopter mode to a second position for operating the tiltrotor aircraft in an airplane mode, and increasing a stiffness of the rotor assembly when the rotor assembly is in the second position.
An exemplary rotorcraft includes a power train with an engine coupled to a gearbox, a main rotor blade having a mast coupled to the power train, a control input linkage in communication between a pilot input device and the main rotor blade configured to communicate a control input force from the pilot input device to the main rotor blade, and a counterweight system in connection with the control input linkage and the power train to apply a centrifugal force to the control input linkage.
B64C 27/605 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including swash plate, spider or cam mechanisms
A parasite aircraft for airborne deployment and retrieve includes a wing; a fuselage rotatably mounted to the wing; a dock disposed on top of the fuselage and configured to receive a maneuverable capture device of a carrier aircraft; a pair of tail members extending from the fuselage; and a plurality of landing gear mounted to the wing. A method of preparing a parasite aircraft for flight includes unfolding an end portion of a wing; unfolding an end portion of a tail member of the parasite aircraft; and rotating a fuselage of the parasite aircraft so that the fuselage is perpendicular to the wing. A method of preparing a parasite aircraft for storage includes rotating a fuselage of the parasite aircraft to be parallel with a wing of the parasite aircraft; folding an end portion of the wing; and folding an end portion of a tail member of the parasite aircraft.
A system for image guided assembly of a structure, the structure defining an interior area accessible through at least one access opening, the interior area including at least one fastener hole. The system including a first fastening tool including an arm with first and second ends; and a support plate on the first end, the support plate including at least one connection member to securely retain a fastener therein, the at least one connection member configured to facilitate alignment of the fastener with the at least one fastener hole; an image capturing device disposed on the arm first end configured to generate a captured image of the interior area; a light source associated with the arm first end, the light source configured to generate light at the first end of the arm; and a display device located outside the interior area for displaying the captured image of the interior area.
B25B 23/18 - Devices for illuminating the head of the screw or the nut
B23Q 17/24 - Arrangements for indicating or measuring on machine tools using optics
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
B25B 23/10 - Arrangements for handling screws or nuts for holding or positioning screw or nut prior to or during its rotation using mechanical gripping means
B25J 1/04 - Manipulators positioned in space by hand rigid, e.g. shelf-reachers
B33Y 80/00 - Products made by additive manufacturing
Various implementation described herein are directed to a method for identifying a blockage in a pitot-static system. A pressure signal is received. Pressure fluctuations in the pressure signal are identified. A determination is made as to whether a blockage has occurred in the pitot-static system based on the identified pressure fluctuations.
G01P 21/02 - Testing or calibrating of apparatus or devices covered by the other groups of this subclass of speedometers
G01P 5/16 - Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring differences of pressure in the fluid using Pitot tubes
25.
Systems and methods for executing aircraft take-off and landing events
In one embodiment, a method is performed by a computer system in an aircraft. The method includes receiving an advance indication of a take-off or landing event to be executed by the aircraft in proximity to a landing area such that the landing area includes an arrangement of a plurality of emitters of electromagnetic radiation. The method further includes, responsive to the receiving, detecting, via a sensor in communication with the computer system, emission states of at least some of the plurality of emitters. In addition, the method includes transforming the detected emission states into an instruction set for the take-off or landing event. The method also includes initiating monitoring of the aircraft relative to the instruction set as the aircraft executes the take-off or landing event in proximity to the landing area.
Embodiments are directed to an aerodynamic spinner fairing having a sidewall and one or more airflow intakes in the sidewall. The airflow intakes are closed during a first phase of flight and open during a second phase of flight. The first phase of flight may be an airplane mode for a tiltrotor aircraft, and the second phase of flight may be a helicopter mode for the tiltrotor aircraft. The airflow intakes may comprise an opening in the sidewall, and a door that is configured to move between a first position covering the opening and a second position exposing the opening to external airflow. An actuator coupled to the door may operate to move the door between the first position and the second position. One or more guide vanes within the aerodynamic spinner fairing may be configured to direct air received via the airflow intakes to provide convection cooling.
B64C 23/00 - Influencing air flow over aircraft surfaces, not otherwise provided for
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 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
A method of selectively preventing flapping of a rotor hub includes providing a flapping lock proximate to a rotor hub and shaft assembly and moving the flapping lock from an unlocked position to a locked position, the flapping lock operable in the locked position to prevent at least some flapping movement of the rotor hub relative to the shaft, the flapping lock operable in the unlocked position to allow the at least some flapping movement of the rotor hub relative to the shaft.
B64C 27/41 - Rotors having articulated joints with flapping hinge or universal joint, common to the blades
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 27/50 - Blades foldable to facilitate stowage of aircraft
B64C 27/52 - Tilting of rotor bodily relative to fuselage
B64C 27/605 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including swash plate, spider or cam mechanisms
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
An aircraft includes a variable-speed gearbox. The variable-speed gearbox includes a low-speed gear train and a high-speed gear train, each gear train of which is configured to selectively provide torque from an engine of the aircraft to a proprotor. The variable-speed gearbox also includes a hydraulic system configured to provide torque to the proprotor. The hydraulic system includes a hydraulic pump driven by the engine of the tiltrotor aircraft and a variable-displacement motor driven by a hydraulic fluid from the hydraulic pump.
F16H 61/02 - Control functions within change-speed- or reversing-gearings for conveying rotary motion characterised by the signals used
F16H 61/12 - Detecting malfunction or potential malfunction, e.g. fail safe
F16H 3/083 - Toothed gearings for conveying rotary motion with variable gear ratio or for reversing rotary motion without gears having orbital motion exclusively or essentially with continuously- meshing gears, that can be disengaged from their shafts with radially acting and axially controlled clutching members, e.g. sliding keys
F16H 3/097 - Toothed gearings for conveying rotary motion with variable gear ratio or for reversing rotary motion without gears having orbital motion exclusively or essentially with continuously- meshing gears, that can be disengaged from their shafts characterised by the disposition of the gears with two or more countershafts the input and output shafts being aligned on the same axis
F16H 61/00 - Control functions within change-speed- or reversing-gearings for conveying rotary motion
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 35/04 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
F16H 47/02 - Combinations of mechanical gearing with fluid clutches or fluid gearing the fluid gearing being of the volumetric type
29.
Electrical load shed to increase available aircraft power
Embodiments are directed to systems and methods for managing electrical load in an aircraft comprising a generator coupled to an aircraft engine, and a power distribution controller configured to monitor current engine operating parameters and to reduce an electrical load on the generator when the engine operating parameters reach a limit during specified aircraft operating conditions. The system may further comprise a non-essential electrical bus coupled to the generator, wherein the electrical load on the generator is reduced by disconnecting the non-essential bus from the generator. The generator may be coupled to the aircraft engine via an accessory gearbox or a transmission gearbox. The monitored current engine operating parameters comprise one or more of an engine torque, a gas generator RPM, and a temperature. The aircraft operating conditions may comprise one or more of a takeoff, a landing, or an engine failure.
B64D 41/00 - Power installations for auxiliary purposes
B60R 16/03 - Electric or fluid circuits specially adapted for vehicles and not otherwise provided for; Arrangement of elements of electric or fluid circuits specially adapted for vehicles and not otherwise provided for electric for supply of electrical power to vehicle subsystems
H02B 1/20 - Bus-bar or other wiring layouts, e.g. in cubicles, in switchyards
An aircraft having an electric motor coupled to a rotor and an instrument electronically connected to the electric motor and configured to communicate a time available value before a motor condition reaches a motor condition limit.
B64D 31/06 - Initiating means actuated automatically
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
G01C 23/00 - Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
An aircraft includes a first rotor assembly, a second rotor assembly, and a rotor phase angle control system. The system includes a phase adjustor operably associated with the first rotor assembly and the second rotor assembly. The method includes sensing vibrations exerted on the aircraft and offsetting a phase angle of the first rotor assembly and the second rotor assembly to minimize the vibrations.
B64C 11/50 - Phase synchronisation between multiple propellers
G10K 11/178 - Methods or devices for protecting against, or for damping, noise or other acoustic waves in general using interference effects; Masking sound by electro-acoustically regenerating the original acoustic waves in anti-phase
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
A notch treatment method for flaw simulation including providing the specimen with the notch, the notch having a re-melt material layer; isolating the notch; and selectively etching the notch to provide an etched surface of the notch; wherein at least a portion of the re-melt material layer has been removed from the notch. In one aspect, there is provided a notch treatment method for flaw simulation including providing the specimen with the notch, the notch having a re-melt material layer, the specimen includes steel or an alloy thereof; isolating the notch; and selectively etching the notch with a first etching solution and a second etching solution to provide an etched surface on the notch; wherein at least a portion of the re-melt material layer has been removed from the notch.
A material dispensing system including a first frame and a first application head. The first application head supported by the first frame including a first bias ply assembly comprising a bias ply roll supported on a bias ply dispenser unit, the first bias ply assembly configured to pass bias ply material along a bias path; and a first non-bias ply assembly comprising a non-bias ply roll supported by a non-bias ply dispenser unit, the non-bias ply assembly configured to pass non-bias ply material along a non-bias path; wherein the bias path and the non-bias path are substantially parallel. Another aspect provides a material dispensing system including a first frame and a first application head supported thereby; and a second frame and a second application head supported thereby; wherein the first frame and the second frame move in an X direction during operation. Another aspect includes preparing a composite article.
B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
B29C 70/34 - 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 and shaping or impregnating by compression
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
A method of blade fold for a tiltrotor aircraft includes configuring the tiltrotor aircraft in a flight ready position with a rotor system in an inverted-Y position, unlocking a first rotor blade of the rotor system to permit the first rotor blade to pivot relative to a yoke of the rotor system, restraining the first rotor blade to allow the first rotor blade to pivot relative to the yoke as the yoke is rotated, rotating the rotor system in a first direction so that the first rotor blade pivots closer to a second rotor blade, rotating the rotor system in a second direction to orient the rotor system into a modified inverted-Y position, unlocking a third rotor blade to allow the third rotor blade to pivot relative to the yoke as the yoke is rotated, and rotating the rotor system in the second direction so that the third rotor blade pivots closer to the second rotor blade.
The aircraft includes a rotor. The rotor includes a plurality of rotor blades. The aircraft further includes a non-rotating aircraft component. A proximity sensor is disposed with at least one of the non-rotating aircraft component and the rotor blades. A flight control computer is electrically coupled to the proximity sensor.
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 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
36.
Blade fold method and apparatus for a tilt rotor hub
A folding rotor blade assembly includes a blade fold support and a blade-fold actuator system coupled to the blade fold support. The blade-fold actuator system includes a motor, a tab configured to selectively prevent rotation of a blade tang of a rotor blade, and a cam connected to the blade fold support and coupled to the motor, the cam configured to move the tab between a locked position that prevents rotation of the blade tang and an unlocked position that permits rotation of the blade tang.
A blade-fold bushing system includes a splined bushing comprising a first plurality of teeth, a castellated bushing comprising a second plurality of teeth and a shaft portion configured to coaxially fit within the splined bushing, and a lock bushing coaxially aligned with the castellated bushing. A support tool for use with a blade-fold bushing system includes an outer head comprising a third plurality of teeth configured to mesh with the first plurality of teeth of the splined bushing, and an inner head comprising a fourth plurality of teeth configured to mesh with the second plurality of teeth of the castellated bushing.
A system for monitoring lubrication of a drive train, including a lubricant pressure sensor to detect a pressure of the lubricant in the drive train and to provide a lubricant pressure signal; lubricant volume sensor to detect a volume of the lubricant in the drive train and to provide a lubricant volume signal; non-contact temperature sensor to detect a temperature of the drive train and to provide a non-contact temperature signal; and logic management system in communication with the lubricant pressure sensor, the lubricant volume sensor, and the non-contact temperature sensor; the logic management system configured to receive and process the lubricant pressure signal, the lubricant volume signal, and the non-contact temperature signal; wherein when the lubricant pressure signal reaches a predetermined minimum pressure level and the lubricant volume signal reaches a predetermined minimum volume level, the logic management system displays non-contact temperature measurement data to a display device.
F16H 57/04 - Features relating to lubrication or cooling
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
G07C 5/12 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time in graphical form
B64D 43/00 - Arrangements or adaptations of instruments
G06F 7/00 - Methods or arrangements for processing data by operating upon the order or content of the data handled
G06F 17/00 - Digital computing or data processing equipment or methods, specially adapted for specific functions
G06F 7/70 - Methods or arrangements for performing computations using a digital non-denominational number representation, i.e. number representation without radix; Computing devices using combinations of denominational and non-denominational quantity representations using stochastic pulse trains, i.e. randomly occurring pulses the average pulse rates of which represent numbers
G06G 7/00 - Devices in which the computing operation is performed by varying electric or magnetic quantities
G06G 7/76 - Analogue computers for specific processes, systems, or devices, e.g. simulators for traffic
In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, an adapter ring, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the swashplate and the adapter ring, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the swashplate and the adapter ring, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.
B64C 27/605 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including swash plate, spider or cam mechanisms
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
41.
Systems and methods for controlled filtering of aircraft control input
In one embodiment, a method is performed by a control computer. The method includes receiving a time series of control inputs in relation to a control axis of an aircraft, where the control computer causes actuation in response to each control input in the time series as the control input is received. The method also includes determining aircraft oscillation over a sample period corresponding to the time series. The method also includes evaluating information related to the determined aircraft oscillation using engagement settings associated with a control filter. The method also includes engaging the control filter responsive to the information satisfying the engagement settings, where the engaged control filter systematically attenuates future control inputs in relation to the control axis prior to actuation responsive thereto.
An ice-management method for an aircraft includes scavenging torque from a mast of the aircraft with a system that is configured to provide an ice-management capability. The method includes using the scavenged torque to impart a vibratory force to an arm of the system and imparting the vibratory force from the arm to an inner surface of a spinner of the aircraft via a contact of the arm.
B64D 15/12 - De-icing or preventing icing on exterior surfaces of aircraft by electric heating
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
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
An aircraft, including a fixed nacelle disposed on a wing of the aircraft, the fixed nacelle including a nacelle opening; a proprotor pylon disposed on the wing and rotatable relative to the fixed nacelle between a substantially horizontal position and a non-horizontal position, wherein rotation of the proprotor pylon to a non-horizontal position exposes the nacelle opening; and a movable cover disposed on at least one of the wing and fixed nacelle, said movable cover including a plurality of cover members that are movable between a closed position where at least a portion of the cover members collectively form a protective cover in front of the nacelle opening when the proprotor pylon is positioned in the non-horizontal position and a stowed position where at least a portion of the plurality of cover members are stowed. In other aspects, there is provide a method of covering a nacelle opening.
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 7/00 - Arrangement of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
B64D 7/04 - Arrangement of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft the armaments being firearms fixedly mounted
A folding rotor blade assembly for an aircraft a yoke, an inboard beam coupled to the yoke, an inboard centrifugal force bearing coupled to the inboard beam, a grip coupled to the inboard beam, an outboard bearing housing coupled to the grip, and a rotor blade pivotally coupled to the grip by a blade fold bolt that is positioned outboard of the outboard bearing housing.
A fairing is provided in one example embodiment and may include an apparatus to receive at least one of a foot traffic load and a hand traffic load, wherein the apparatus can include: a step portion that is to receive at least a portion of the foot traffic load; a handhold portion that is to receive at least a portion of the hand traffic load, wherein the handhold portion extends downward from the step portion; and a support structure, wherein the support structure extends downward from of the step portion. The apparatus can include an outer flange attached to the fairing. At least a portion of the step portion the apparatus can be recessed within the fairing at a distance between one inch and three inches from a top surface of the fairing. The handhold portion can include one or more drain holes.
An exemplary passive oil system includes a reservoir housing configured in operation to rotate around a rotational axis, the reservoir housing defining a reservoir between a top wall, a bottom wall, innermost side, and an outer sidewall; and an outlet positioned adjacent the outer sidewall to discharge a lubrication fluid contained in the reservoir in response to the reservoir housing rotating around the rotational axis.
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
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
B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
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 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 7/00 - Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical propert; Layered products characterised by the interconnection of layers
B32B 7/02 - Physical, chemical or physicochemical properties
A masking tool system includes a first masking body and a second masking body. The first masking body includes a bore passing through a portion of the first masking body and a first sealing element disposed on a first end of the first masking body. The second masking body includes a bore passing through the second masking body and a second sealing element disposed on a first end of the second masking body. The system may also include a rod configured to pass through the bores of the first and second masking bodies and to secure the first and second masking bodies to a metallic article placed therebetween. A diagonal length of the masking tool system induces a wobbling rotation during processing.
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
An embodiment of the present invention provides a blocking door that is pivotally disposed on a fixed nacelle of a tiltrotor aircraft for pivoting between a stowed position when a proprotor pylon is in the substantially horizontal position and a protective blocking position in front of the proprotor pylon when the proprotor pylon is positioned in the non-horizontal position. In other aspects, there is provided a blocking door and a method of reducing infrared and/or radar signatures of rotorcraft with a rotatable proprotor.
B64D 29/06 - Attaching of nacelles, fairings, or cowlings
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 7/00 - Arrangement of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft
F41H 3/00 - Camouflage, i.e. means or methods for concealment or disguise
52.
Methods and Systems for Manufacturing Composite Components
A method for forming composite components includes disposing composite laminate over a mandrel. The method further includes infusing the composite laminate with a resin. A gelation of the infused resin is caused by applying a first environmental condition to the composite laminate and mandrel. At least a portion of the mandrel is deformed by applying a second environmental condition to the composite laminate and mandrel. The method further includes forming a composite structure by curing the composite laminate infused with resin. The deformed mandrel is removed from the composite structure after forming the composite structure.
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
B29C 35/02 - Heating or curing, e.g. crosslinking or vulcanising
B29C 33/44 - 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
B29C 33/38 - 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 characterised by the material or the manufacturing process
A light weight hybrid torque transfer joint trunnion has an integral metal hub spline fitting oriented on a center axis. This integral metal hub spline fitting may be made of steel, aluminum, titanium, or the like and may be generally cylindrical. The integral metal hub spline fitting defines an integral central internally-splined mast or driveshaft coupling opening centered about the center axis. A composite material body centrally retains, and is cured to, the metal hub spline fitting. Torque transfer joint link attachment pins extend from the composite material body and are rigidly linked to the metal hub spline fitting. In an example constant-velocity joint, a plurality of pivoting linkages may each be rotatably coupled to the torque transfer joint link attachment pins, and each of the plurality of pivoting linkages may, in turn be secured to a rotor yoke configured to mount a plurality of rotorcraft blades.
F16D 3/60 - 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 pushing or pulling links attached to both parts
F16D 1/10 - Quick-acting couplings in which the parts are connected by simply bringing them together axially
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B29C 70/84 - Moulding material on preformed parts to be joined
An afterbody for a rotor blade of a rotorcraft is unitarily formed of a single material of construction. The afterbody includes an upper surface disposed from a lower surface, a concave leading edge connected to the upper surface and the lower surface, and a trailing edge formed at an intersection of the upper surface with the lower surface.
A standpipe assembly for a rotorcraft includes a slip ring positioned within the mast of the rotorcraft. The slip ring includes a stator rotationally connected to a rotor. A flexible coupling is connected to the stator and a standpipe tube is connected to the flexible coupling. The flexible coupling is capable of angular, axial, and torsional displacement.
H01R 39/34 - Connections of conductor to slip-ring
F16D 3/72 - 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
F16D 3/52 - 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 a continuous strip, spring, or the like engaging the coupling parts at a number of places
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.
In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, a phase adapter fulcrum, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the plurality of actuators and the swashplate, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the plurality of actuators and the plurality of lower pitch links, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.
B64C 27/605 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including swash plate, spider or cam mechanisms
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.
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
G05G 9/047 - Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only in which movement in two or more ways can occur simultaneously the controlling member being movable by hand about orthogonal axes, e.g. joysticks
B64C 13/14 - Initiating means actuated personally lockable
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.
An aspect provides a skid landing gear assembly including a cross member disposed between a first skid tube and a second skid tube, and a tension cable member configured to be disposed in the cross member; wherein the tension cable member resists outward deflection of at least a portion of the skid landing gear assembly when a downward load is applied to the skid landing gear assembly. In other aspects, there are methods of avoiding ground resonance in a skid landing gear assembly, methods of assembling a skid landing gear assembly, methods of operating a helicopter with a skid landing gear assembly, and methods of improving the service life of a skid landing gear assembly.
An example of an aerial vehicle includes a rudder removably connected to the aerial vehicle by a twist lock mechanism. The twist lock mechanism is biased in a locked position by an elastic member.
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
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
65.
AUTOMATIC HEADING CORRECTION FOR DIRECTIONAL GYROSCOPES
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.
An emergency escape window for a rotorcraft includes a window frame, a window pane set inside the window frame, a plurality of pins connecting the window frame to the fuselage of the rotorcraft, and a release mechanism having at least one actuator connected to a respective pin and constructed to retract the pin from the window frame. The escape window can then be pivoted away and/or completely detached from the fuselage in the event of an emergency to allow occupants to safely exit the rotorcraft. The disclosure also relate to a method of operating an emergency escape window for a rotorcraft and to a rotorcraft having an emergency escape window.
A hybrid yoke including a center and yoke arms connected to flexure arms. An inboard centrifugal force bearing assembly connects to the yoke arm and a grip and an outboard shear bearing assembly connects to the flexure arm and the grip. In use, the center and yoke arms carry the centrifugal force at a position inboard of the flexure arm.
A tri-hybrid yoke including a center ring connected to a CF fitting connected to flexure arms. An inboard centrifugal force bearing assembly connects to the CF fitting and a grip. An outboard shear bearing assembly connects to the flexure arm and the grip. In use, the center ring and the CF fittings carry the centrifugal force at a position inboard of the flexure arm.
A multi-piece inboard beam assembly for use in a rotor blade assembly of a rotorcraft. The inboard beam assembly includes an inboard beam connected to an inboard beam fitting with an anti-rotational connection. The inboard beam is connected to a yoke via bearings and the inboard beam fitting is connected to a grip in a double shear condition. In use, the grip, the inboard beam fitting with the double shear connection, the inboard beam, a centrifugal force bearing held by the inboard beam, and the yoke carry the centrifugal force created upon rotation of the rotor blade assembly.
A system and method for preventing a maximum asymmetric condition between pylon tilt angles due to a degraded pylon in a fly-by-wire tiltrotor aircraft during transitions between airplane mode and helicopter mode includes a conversion system for imparting movement on a right and left pylon. A flight control computer is operatively connected to a set of transducers for measuring pylon angles. The flight control computer is further connected to a set of actuators which are attached to each pylon. The flight control computer receives flight dynamics input from the set of transducers and/or the pilot and sends pylon command to the set of actuators. The conversion system measures the difference between the pylon angles during the transition and provides a pylon command adjustment if the difference exceeds a preset threshold.
A system is provided in one example embodiment and may include a first reservoir for a lubricant; a second reservoir for the lubricant, wherein the first reservoir and the second reservoir are interconnected; a first pumping element to pump the lubricant from the first reservoir at a first flow rate; a second pumping element to pump the lubricant at a second flow rate, wherein the first flow rate and the second flow rate are different; and a gearbox coupled to the first pumping element and the second pumping element. The first reservoir may have a larger volume than the second reservoir and the first flow rate may be higher than the second flow rate.
A method for operating a sensor system includes detecting a first wake trigger by a plurality of sensors for a component disposed in a remote location, generating, by each sensor, sensor service data that includes a battery charge level of the sensor, determining an active sensor according to the sensor service data of each sensor of the plurality of sensors, and assigning the active sensor to enter an active mode assigning each sensor of the plurality of sensors, other than the active sensor, to enter a sleep mode, generating, by the active sensor, sensor reading data for the component until an inactive trigger is detected, sending the sensor reading data using a wireless transmission to a sensor data server, and leaving the active mode by the active sensor and entering a sleep mode in response to the active sensor detecting an inactive trigger.
G08B 21/00 - Alarms responsive to a single specified undesired or abnormal condition and not otherwise provided for
H04Q 9/00 - Arrangements in telecontrol or telemetry systems for selectively calling a substation from a main station, in which substation desired apparatus is selected for applying a control signal thereto or for obtaining measured values therefrom
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
G07C 5/00 - Registering or indicating the working of vehicles
73.
Dual blade fold bolts and inboard centrifugal bearing in a folding rotor blade assembly
A folding rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a yoke with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard shear bearing. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.
A rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a yoke with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard CF bearing and the yoke tip. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.
A folding yoke comprising a bilateral center yoke pivotally connected to separate foldable yoke arms permits rotor blade fold about a single through bolt connection inboard of a set of bearings. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.
F04F 5/16 - Jet pumps, i.e. devices in which fluid flow is induced by pressure drop caused by velocity of another fluid flow the inducing fluid being elastic fluid displacing elastic fluids
A folding yoke comprising a center yoke pivotally connected to separate foldable flexible yoke arms permits rotor blade fold about a single through bolt connection inboard of a set of bearings. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.
A folding rotor blade assembly for a tiltrotor aircraft comprising a rotor blade pivotally connected to a grip with dual concentric blade bolts having a common central axis providing a pivotal axis inboard of an outboard bearing. A folding spindle connects the outboard bearing to an outboard tip of a yoke. The outboard bearing and the spindle fold with the rotor blade relative to the yoke. In use, the compact folded arrangement of the rotor blades reduces folded aircraft dimensions in response to ever increasing restricted storage space parameters.
In one embodiment, an aircraft electronics system includes a hardware processor, a charge collection circuit to collect charge; a switching circuit controlled by the hardware processor to discharge the charge collected on the charge collection circuit through a bonding circuit formed from a chassis and a bonding surface; and a voltage measurement circuit to measure a voltage difference between measurement terminals across the chassis and the bonding surface.
G01R 27/26 - Measuring inductance or capacitance; Measuring quality factor, e.g. by using the resonance method; Measuring loss factor; Measuring dielectric constants
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
G01R 31/02 - Testing of electric apparatus, lines, or components for short-circuits, discontinuities, leakage, or incorrect line connection
H02H 5/10 - Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal non-electric working conditions with or without subsequent reconnection responsive to mechanical injury, e.g. rupture of line, breakage of earth connection
B64D 43/00 - Arrangements or adaptations of instruments
G01R 31/00 - Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
H02J 7/34 - Parallel operation in networks using both storage and other dc sources, e.g. providing buffering
H02H 3/04 - Emergency protective circuit arrangements for automatic disconnection directly responsive to an undesired change from normal electric working condition, with or without subsequent reconnection - Details with warning or supervision in addition to disconnection, e.g. for indicating that protective apparatus has functioned
H05F 1/00 - Preventing the formation of electrostatic charges
In one embodiment, a split torque gearbox can include a first compound gear and a second compound gear. The compound gears can each include a piston housing with a fluid inlet and a piston received in the piston housing and defining a space within the first piston housing exposed to the fluid inlet. The split torque gearbox can include a fluid line coupled to each of the fluid inlets to supply a fluid to the pistons at a predetermined pressure, the fluid line coupled to the second fluid inlet to supply fluid to the second piston assembly at the predetermined pressure. Pressure developed in the pistons is equal for all gear shafts, and can equalize torque imbalances in the split torque gearbox.
F16H 57/022 - Adjustment of gear shafts or bearings
F16H 1/22 - Toothed gearings for conveying rotary motion without gears having orbital motion involving more than two intermeshing members with arrangements for dividing torque between two or more intermediate shafts
In one embodiment, a centrifugal force generating device comprises a first hydraulic rotor, a second hydraulic rotor, and one or more hydraulic control valves. The first hydraulic rotor comprises a first mass and is configured to rotationally drive the first mass around a first axis of rotation using a first flow of hydraulic fluid through the first hydraulic rotor. The second hydraulic rotor comprises a second mass and is configured to rotationally drive the second mass around a second axis of rotation using a second flow of hydraulic fluid through the second hydraulic rotor. The one or more hydraulic control valves are configured to control the first flow of hydraulic fluid through the first hydraulic rotor and the second flow of hydraulic fluid through the second hydraulic rotor.
B06B 1/18 - Processes or apparatus for generating mechanical vibrations of infrasonic, sonic or ultrasonic frequency wherein the vibrator is actuated by pressure fluid
F16F 15/023 - Suppression of vibrations of non-rotating, e.g. reciprocating, systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating system using fluid means
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
According to one embodiment, a rotorcraft includes a body, a rotor blade, a drive system that can be operated to rotate the rotor blade, and an emergency valve control unit. The drive system contains a first gearbox assembly, a second gearbox assembly, a first lubrication system that can deliver lubricant to the first gearbox assembly, and a second lubrication system that can deliver lubricant to the second gearbox assembly. The drive system also contains an emergency valve that can be opened to deliver lubricant from the first lubrication system to the second gearbox assembly. The emergency valve control unit can instruct the emergency valve to open.
A cable reel restraint device comprises a cable reel, a retractable cable, first and second springs, first and second attachment interfaces, and a preload selection control. The retractable cable is configured to extend from and retract onto the cable reel. The first spring is configured to exert force for preloading the second spring, and the second spring is configured to exert force for retracting the retractable cable. The first attachment interface is coupled to the cable reel by a first spherical bearing, and the second attachment interface is coupled to the retractable cable by a second spherical bearing. Moreover, the first and second attachment interfaces are configured for being fastened to first and second attachment points. The preload selection control is configured to select a particular preload magnitude and cause the first spring to preload the second spring with a load of the particular preload magnitude.
A mounting assembly for coupling an accessory to a frame including a base configured to be coupled to the frame; the base having a hollow portion; the hollow portion including a receiving end including a tapered socket; an internal interlocking portion adjacent to the tapered socket; and a securing end opposite from the receiving end; a shaft configured to be connected to an accessory at a first end and received in the hollow portion of the base in an engaged position, the shaft including a tapered boss adjacent to the first end, the tapered boss configured to engage the tapered socket; an external interlocking portion adjacent to the tapered boss configured to engage the internal interlocking portion; and a second end opposite from the first end, the second end including a threaded surface; wherein when the shaft is in an engaged position, the shaft is static in the hollow portion.
B64D 29/06 - Attaching of nacelles, fairings, or cowlings
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
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
85.
Multirotor aircraft with collective for autorotation
A multirotor aircraft comprises at least three proprotors. Each proprotor has a plurality of rotor blades pivotably attached to a mast assembly. When a rotor blade pitch angle is changed for a proprotor, all rotor blades on the proprotor change to a same pitch angle. The proprotors are configured to spin freely when a power source is disengaged or fails. In various embodiments, one or more engines provides power to each proprotor, or at least one engine provides power to two or more proprotors. A rotor blade control system is configured to control a collective rotor blade pitch angle on each proprotor independently of the rotor blade pitch on the other proprotors. The rotor blade control system is configured to set a negative collective rotor blade pitch angle on an unpowered proprotor, such as in response to manual inputs by a pilot or in response to current engine conditions.
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
B64C 27/54 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
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 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
In one embodiment, a tiltrotor aircraft may comprise a fuselage; a biplane wing coupled to the fuselage, wherein the biplane wing comprises an upper wing structure and a lower wing structure; a plurality of tiltrotors coupled to the biplane wing; and at least one engine to power the plurality of tiltrotors.
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64C 3/38 - Adjustment of complete wings or parts thereof
B64C 9/14 - Adjustable control surfaces or members, e.g. rudders forming slots
B64C 39/08 - Aircraft not otherwise provided for having multiple wings
B64C 15/12 - Attitude, flight direction or altitude control by jet reaction the jets being propulsion jets the power plant being tiltable
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
There is provided a rotorcraft, including a body, including a front portion and a tail portion; a main rotor system coupled to the front portion of the body, the main rotor system operable to provide a lifting force on the body; and an anti-torque system coupled to the tail portion of the body, the anti-torque system including a primary tail rotor system and a secondary tail rotor system; wherein the primary tail rotor system and the secondary tail rotor system are operable to provide a first anti-torque force and a second anti-torque force. In other aspects, there are methods of providing anti-torque force in a rotorcraft.
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
A rotor system including a hub; a rim configured to rotate about the hub, the rim including an interior surface and an engagement surface; a plurality of rotor blades extending from the hub and coupled to the interior surface of the rim; and one or more outer drive gears disposed adjacent to the engagement surface of the rim; each of the one or more outer drive gears including a plurality of teeth for engaging the engagement surface of the rim; wherein the one or more outer drive gears are configured to rotate the rim such that the plurality of rotor blades rotates about the hub. Other aspects provide an aircraft rotor system and methods of operating an aircraft rotor system.
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 intentionally activated frangible bonding system comprises a frangible adhesive, adhesive primer, composite material matrix, and/or the like, having a polydispersion of at least one additive spread throughout the frangible bonding material. The additive degrades a bond provided by the frangible bonding material, upon application of a specific energy to the frangible bonding material. An energy emitter is configured to selectively direct the specific energy toward a structure or assembly comprising components bonded by the frangible bonding material to degrade the frangible bonding material bonding the components for disassembly.
Systems and methods of operating a test apparatus to simulate testing a production aircraft component include assembling a test assembly having a test specimen and a wear protection material disposed on opposing sides of the test specimen, an outer plate disposed on each side of the test specimen in contact with the wear protection material, and a bolt disposed through the test specimen and the outer plates and applying a preload against the wear protection material. The test assembly is secured in a test machine, and the test machine is operated to provide a predetermined displacement of the test specimen relative to the outer plates at a predetermined frequency at a determined frequency of displacement cycles. The preload, the predetermined displacement, and the predetermined frequency of displacement cycles are determined through finite element analysis of an analytical model of the production component.
One example of a mount for a rotorcraft comprises a structural support member, a bracket, and an elastomer. The bracket is configured to attach to a component of the rotorcraft. The component of the rotorcraft produces vibrations at a first frequency. The structural support member configured to transfer a weight of the component of a rotorcraft to an airframe of the rotorcraft. A rotor system of the aircraft vibrates the airframe of the rotorcraft at a second frequency. The elastomer is located between a structural support member and a bracket. The elastomer is configured to attenuate noise caused by the vibrations at the first frequency by isolating the vibrations at the first frequency from reaching the airframe of the rotorcraft while the airframe vibrates at the second frequency.
A hybrid power system for a vertical takeoff and landing (“VTOL”) aircraft including a first power source operable to provide a power output for at least a forward flight mode; and a second power source configured to provide a high specific power output for an altitude adjustment flight mode, the second power source including an auxiliary gas generator coupled to a turbine and a drive system. In other aspects, there is provided a VTOL aircraft and methods for providing power to a VTOL aircraft.
B64D 27/10 - Aircraft characterised by the type or position of power plant of gas-turbine type
B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
B64D 41/00 - Power installations for auxiliary purposes
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
F02C 6/14 - Gas-turbine plants having means for storing energy, e.g. for meeting peak loads
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 door system for a nacelle of a tiltrotor aircraft, the nacelle including a movable proprotor housing rotatable relative to a fixed portion of the nacelle from a forward flight mode to a vertical flight mode and a proprotor gearbox door connected to the movable proprotor housing and pivotably coupled to the fixed portion. The door system including a linkage to pivotably couple the door and the fixed portion of the nacelle; a track assembly mounted to the movable proprotor housing; and a door roller mechanism connected to the proprotor gearbox door. The door roller mechanism traverses the track assembly during rotation of the movable proprotor housing.
Disclosed herein is an aircraft that includes an exhaust manifold for combining one or more system exhaust paths located upstream of equipment inlets and directing the exhausts upwards towards the rotor linkages such that the exhaust is expelled and diffused forward of the equipment inlets. According to one aspect of the present disclosure, the exhaust manifold includes a structure for supporting a transmission cowling at the top of the aircraft and/or on the sides of the aircraft. For example, the exhaust manifold may include a platform that contains the exhaust ducts and may include a frame extending from the platform that follows the contours of the cowling, such that the cowling lays along the support frame for additional mechanical support.
In an embodiment, a rotorcraft includes: tail rotor blades; a tail rotor actuator coupled to the tail rotor blades such that the pitch of the tail rotor blades varies according to a current extension of the tail rotor actuator; pilot flight controls electrically coupled to the tail rotor actuator; and a flight control computer electrically coupled to the tail rotor actuator and the pilot flight controls, the flight control computer configured to: determine the current extension of the tail rotor actuator; determine whether the current extension of the tail rotor actuator is within a margin of a maximum extension of the tail rotor actuator; and indicate a first warning to a pilot in response to the current extension of the tail rotor actuator being within the margin of the maximum extension of the tail rotor actuator.
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
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
B64D 43/00 - Arrangements or adaptations of instruments
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 33/38 - 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 characterised by the material or the manufacturing process
B29C 70/46 - 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
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
B29C 70/88 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts characterised primarily by possessing specific properties, e.g. electrically conductive or locally reinforced
B29C 48/18 - Articles comprising two or more components, e.g. co-extruded layers the components being layers
There is provided an ice protection system for a rotary aircraft, including a rotor blade susceptible to an ice buildup having an inboard portion and an outboard portion, the length of the inboard portion and the length of the outboard portion define a total length of the rotor blade; a first deicing system coupled to the inboard portion of the rotor blade, the first deicing system including a plurality of spanwise zones; and a second deicing system coupled to the outboard portion of the rotor blade, the second deicing system including a plurality of chordwise zones. In one aspect, there is provided a deicing system for a rotary aircraft. In another aspect, there is a method to de-ice a rotor blade of an aircraft.
In one embodiment of the present disclosure, there is provided an aircraft having a bi-folding cowl for providing full access to equipment without completely removing the cowl. The bi-folding cowl has an upper portion and a lower portion mechanically connected along the adjacent edges, where the upper and lower portions fold so that the inner surfaces face each other when opened. In another embodiment, the bi-folding cowl has at least three maintenance positions, including partially-opened, fully-opened, and fully-opened, lying flat on the surface of the aircraft.
In one embodiment of the present disclosure, there is provided an aircraft that includes a cowling having a j-track mounted on the inwardly facing surface and a rod pivotally connected to a stationary part of the aircraft at a first end and moveable within the j-track at a second end, so that, when the cowling is opened, the second end moves to lock into the j-shaped portion and hold the cowling open. In various embodiments, the first end may be pivotally connected to the aircraft by a quick release pin, and the second end may be connected to the j-track by a torsion spring. In another embodiment of the present disclosure, the cowling is a bi-folding cowl having an upper portion and a lower portion, where the rod and the lower portion may include structures for retaining the lower portion in an opened position.
This disclosure relates to an air inlet for an aircraft with an integrated hand hold. One innovative aspect of the subject matter described herein can be implemented as an air inlet on the exterior surface of a cowling for a rotorcraft, wherein the air inlet having a scoop that includes a bottom surface having a wide, flat, front edge that angles downward towards the back, an opening in the back for air to enter, and two lateral sides coupled to the bottom surface, where the two sides are planar on a top surface and become longer in height towards the opening in the back, and hand hold, where the hand hold is a trough or an indentation in the bottom surface of the scoop that extends along a side.
