A rotorcraft includes a drive shaft coupled to an engine; a sprag clutch coupled the drive shaft; and an output shaft coupled to the sprag clutch, wherein the sprag clutch physically contacts a first contact surface of the output shaft during operation, wherein a first cross-sectional thickness of the output shaft near the middle of the first contact surface is greater than a second cross-sectional thickness of the output shaft near a first edge of the first contact surface.
F16H 1/28 - Toothed gearings for conveying rotary motion with gears having orbital motion
B64D 35/00 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions
F16D 41/07 - Freewheels or freewheel clutches with intermediate wedging coupling members between an inner and an outer surface the intermediate members wedging by pivoting or rocking, e.g. sprags between two cylindrical surfaces
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
F16D 41/06 - Freewheels or freewheel clutches with intermediate wedging coupling members between an inner and an outer surface
An improved compound planetary gear system. In embodiments, a compound planetary gear system includes at least one planet pinion including a main shaft having a first gear for meshing with a sun gear and a second gear for meshing with a ring gear, and a carrier for supporting the at least one planet pinion. Teeth of the first gear are configured with a first helical angle with respect to a longitudinal angle of the at least one planet pinion, teeth of the second gear are configured with a second helical angle with respect to the longitudinal angle of the at least one planet pinion, the first helical angle different from the second helical angle.
F16H 1/34 - Toothed gearings for conveying rotary motion with gears having orbital motion involving gears essentially having intermeshing elements other than involute or cycloidal teeth
F16H 1/28 - Toothed gearings for conveying rotary motion with gears having orbital motion
F16H 57/08 - General details of gearing of gearings with members having orbital motion
According to one implementation of the present disclosure, a method is disclosed. The method includes: detecting, on or proximate to one or more surfaces of an aircraft, a presence of an electric-field above a predetermined threshold; and in response to the detection, activating one or more beam sources to generate an ionized column of charge away from the aircraft.
A technique is directed to controlling vehicle motion. The technique involves setting a set of motion control parameters which controls motion of the utility vehicle to a set of initial values. The technique further involves receiving stability control inputs which include a geolocation signal identifying a current location of the utility vehicle and a set of motion signals identifying a set of current motion characteristics of the utility vehicle. The technique further involves changing, based on the geolocation signal and the set of motion signals, at least one motion control parameter of the set of motion control parameters which controls motion of the utility vehicle from an initial value to an updated value which is different from the initial value.
B60L 15/20 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train for control of the vehicle or its driving motor to achieve a desired performance, e.g. speed, torque, programmed variation of speed
The invention discloses a powered leg rest assembly for aircraft, featuring a motor-driven gear train rotating an output shaft connected to a leg rest extension mechanism and leg rest cushion. Monitored by a hollow shaft single-turn absolute encoder and backed by limit switches, the leg rest's position is precisely regulated during deployment. A motion control system ensures clearance from seat cushion thigh support, extending the leg rest away from the seat cushion. A power-on brake, activated at the commanded position, securely holds the leg rest. The assembly is designed for manual stowing in case of power loss or system fault. Incorporating back drivability, ergonomic extension, and real-time feedback, this innovation provides enhanced comfort and adaptability for aircraft occupants.
A rotor-blade weight-carrier system includes a weight carrier positioned within a rotor blade and a plurality of weights positioned within the weight carrier.
There is disclosed in one example, one or more tangible, non-transitory computer-readable storage media having stored thereon machine-executable instructions to: receive battery data from at least one sensor connected to a battery bank of an electric vertical takeoff and landing (eVTOL) aircraft, wherein the battery bank comprises a plurality of batteries; compute from the battery data an available flight time remaining for the eVTOL aircraft; compute a nominal flight time remaining, wherein the nominal flight time remaining excludes a reserve flight time; and display the nominal flight time remaining to a pilot in a human-readable format.
One embodiment is an aircraft including a fuselage; a wing connected to the fuselage; first and second booms connected to the wing on opposite sides of the fuselage; first and second forward propulsion systems attached to forward ends of the first and second booms; first and second aft propulsion systems fixedly attached proximate aft ends of the first and second booms; and first and second wing-mounted propulsion systems connected to outboard ends of wings; wherein the first and second wing-mounted propulsion systems are tiltable between a first position when the aircraft is in a hover mode and a second position when the aircraft is in a cruise mode.
A flight control system, including a flight control computer (FCC) configured for providing a first and second flight function, and sending, to effectors of an aircraft, first command signals based on the first and second flight functions, and a second computer configured for providing one or more autonomy functions associated with operation of the aircraft, and that are different from the first and second flight functions, monitoring operation of the FCC, determining whether the FCC has failed, and providing a fail-safe mode for at least the first flight function in response to determining that the FCC has failed. Providing the fail-safe mode includes providing one or more critical flight functions that includes the first flight function, and sending, to the effectors, second command signals that replace a first command signal associated with the first flight function and that are based on the critical flight functions.
An aircraft recording system provides gapless asynchronous data recording. A data acquisition system is connected to a data ingestion interface, such that data acquisition system captures avionics data. An endpoint is associated with the aircraft data acquisition system and located remotely from the aircraft, which persists the plurality of events. An asynchronous messaging platform is provided that is adapted to digest and publish a plurality of packet payload words. A data file caching system is provided that is adapted to cache aircraft data files by ingesting data from the asynchronous messaging platform, writing the ingested data to a cache buffer, and based on a determination that a file descriptor is available, flushing the cache buffer to the file descriptor. A data file persistence system persists the aircraft data files by claiming the file descriptor, flushing the cache buffer to physical storage, and releasing the file descriptor.
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 5/00 - Registering or indicating the working of vehicles
An embodiment position locking apparatus includes a track tube, convex-curved serrations in the track tube, a radial pawl, a pin, concave-curved serrations in the radial pawl, and a motion-translation component. The radial pawl may have a pivot point and the pin extending from the radial pawl. The motion-translation component may have a slot formed therein and disposed adjacent the radial pawl. The pin may extend into the slot so the slot at least partially constrains motion of the pin such that a pivotal motion of the motion-translation component is translated to a slider motion of the pin to control a rate of angular motion of the radial pawl pivoting about the pivot point and so the concave-curved serrations engage and disengage with the convex-curved serrations to lock and unlock a position of the track tube relative to the radial pawl.
Techniques control a utility vehicle. Such techniques involve obtaining access to a lithium battery powered utility vehicle having a utility vehicle body, a lithium battery system supported by the utility vehicle body, the lithium battery system being constructed and arranged to store electric power, a motor system supported by the utility vehicle body, the motor system being constructed and arranged to provide vehicle propulsion in response to electric power from the lithium battery system, and a set of user controls electrically coupled with the motor system. The set of user controls is constructed and arranged to transition the motor system between a non-operational state and an operational state in response to detection of a wireless device. Such techniques further involve detecting the wireless device, and transitioning the motor system between the non-operational state and the operational state in response to detection of the wireless device.
B60L 53/00 - Methods of charging batteries, specially adapted for electric vehiclesCharging stations or on-board charging equipment thereforExchange of energy storage elements in electric vehicles
B60L 1/00 - Supplying electric power to auxiliary equipment of electrically-propelled vehicles
B60L 7/12 - Dynamic electric regenerative braking for vehicles propelled by DC motors
B60L 53/50 - Charging stations characterised by energy-storage or power-generation means
B60L 58/10 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries
B60R 16/033 - Electric or fluid circuits specially adapted for vehicles and not otherwise provided forArrangement 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 characterised by the use of electrical cells or batteries
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
H02J 9/00 - Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
H02P 1/02 - Arrangements for starting electric motors or dynamo-electric converters Details
H02P 3/06 - Arrangements for stopping or slowing electric motors, generators, or dynamo-electric converters for stopping or slowing an individual dynamo-electric motor or dynamo-electric converter
13.
Distributed Propulsion System for Vertical Take Off and Landing Closed Wing Aircraft
An aircraft includes a closed wing, 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. A source of electric power is disposed within or attached to the closed wing, fuselage or one or more spokes. A plurality of electric motors are disposed within or attached to the one or more spokes in a distributed configuration. Each electric motor is connected to the source of electric power. A propeller is operably connected to each of the electric motors and proximate to a leading edge of the one or more spokes. One or more processors are communicably coupled to the plurality of electric motors. A longitudinal axis of the fuselage is substantially vertical in the vertical takeoff and landing and the stationary flight, and substantially in a direction of flight in the forward flight.
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 1/00 - FuselagesConstructional features common to fuselages, wings, stabilising surfaces or the like
An exemplary tiltrotor aircraft having a vertical takeoff and landing (VTOL) flight mode and a forward flight mode includes tiltable rotors located at forward boom ends, tiltable ducted fans located at wings aft of the forward boom ends, and aft rotors located on aft boom portions.
Embodiments include an aircraft comprising a fuselage; a wing connected to the fuselage; and first and second propulsion systems connected to the wing on opposite sides of the fuselage, wherein at least a portion of each of the first and second propulsion systems and at least a portion of the wing are tiltable between a first position in which the aircraft is in a hover mode and a second position in which the aircraft is in a cruise mode, wherein each of the propulsion systems includes pylon and a rotor assembly comprising a plurality of rotor blades.
B64D 27/24 - Aircraft characterised by the type or position of power plants using steam or spring force
B64D 27/30 - Aircraft characterised by electric power plants
B64D 35/04 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
16.
DETECTING OBJECTS AND DISTANCE TO OBJECTS FOR ROTORCRAFT ROTOR STRIKE AVOIDANCE
In certain embodiments, a method includes accessing image information generated by one or more image sensors configured to generate the image information for a surrounding environment of a rotorcraft. The method includes causing one or more AI models to process the image information to generate proximity information for the image information. The proximity information includes depth measurements for one or more image objects from the image information that correspond to one or more physical objects in the surrounding environment of the rotorcraft. The method includes initiating, in response to generating the proximity information from the image information, further analysis of the proximity information for the one or more image objects to facilitate avoiding, based on the proximity information, a collision of a rotor blade of the rotorcraft with the one or more physical objects that correspond to the one or more image objects.
B64D 45/08 - Landing aidsSafety measures to prevent collision with earth's surface optical
G06T 7/55 - Depth or shape recovery from multiple images
G06T 7/70 - Determining position or orientation of objects or cameras
G06V 10/764 - Arrangements for image or video recognition or understanding using pattern recognition or machine learning using classification, e.g. of video objects
A technique is directed to controlling a vehicle. The technique involves setting a set of motion control parameters which controls motion of the vehicle to a set of initial values. The technique further involves receiving a set of motion signals from a set of sensors, the set of motion signals indicating a set of current motion characteristics of the vehicle. The technique further involves, based on the set of motion signals, changing at least one motion control parameter of the set of motion control parameters which controls motion of the vehicle from an initial value to an updated value which is different from the initial value.
B60W 30/04 - Control of vehicle driving stability related to roll-over prevention
B60W 10/08 - Conjoint control of vehicle sub-units of different type or different function including control of propulsion units including control of electric propulsion units, e.g. motors or generators
B60W 10/26 - Conjoint control of vehicle sub-units of different type or different function including control of energy storage means for electrical energy, e.g. batteries or capacitors
A control system for implementing passenger preferences and setting in aircraft systems includes an RFID reader operable to detect and identify an RFID tag associated with a passenger boarding, or aboard, an aircraft. Information associated with the passenger is retrieved and used to effect settings of various aircraft systems according to passenger preferences, such as HVAC temperature and air flow, as well as audio, visual, and lighting. In alternative embodiments other wireless detection hardware, such as NFC is used to identify passengers and to implement preferred settings of aircraft systems.
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
G06K 7/10 - Methods or arrangements for sensing record carriers by electromagnetic radiation, e.g. optical sensingMethods or arrangements for sensing record carriers by corpuscular radiation
A heliport docking system provides automated transport, fueling, maintenance, and logistical management of VTOLs. The heliport docking system can include a plurality of helipads that can be autonomously transported from area-to-area to assist in the logistics of heliport management and control. The helipad system can include a surface on which a VTOL can land and a controller that can perform functions related to routing, maintenance, object detection, and transport, among others. The helipad system can releasably secure the VTOL to the helipad and transport the VTOL to different areas of the heliport system. The helipad system can also fuel the VTOL by providing, electricity, combustible fuel, or other suitable energy source, and perform a maintenance check of the VTOL and create maintenance crew of any VTOL irregularities.
Systems and methods are disclosed for providing performant, pre-initialization data caching for capturing faults during aircraft recording system startup and writing to one or more local caches an aircraft recording system (ARS) device. One or more candidate input parameter values are captured upon power up of the aircraft recording system, the one or more candidate input parameter values associated with one or more aircraft input parameters corresponding to one or more aircraft system controls. The one or more candidate input parameter values may not have been capable of being captured prior to a full aircraft recording system initialization. An external embedded data processing system is initialized, and upon successful initialization locally cached pre-initialization aircraft data is retrieved and stored in combination with subsequently-acquired aircraft data. The one or more candidate input parameter values may be one or more fault conditions associated with the aircraft.
The technology of this application is generally directed to a method for temporary installation of a third military transponder while maintaining an existing dual civil transponder architecture. In one example embodiment, coax relays are installed between one of the civil transponders, the corresponding antennas, and the military transponder. A switch is installed to drive the coax relays and determine which transponder (e.g., civil or military) is connected to the antennas. The circuit breaker of the transponder not being used at the time can be pulled and collared to remove power to the equipment, and a software configuration loader card is used to configure the avionics.
A removable bracket configured to install to a structure. The removable bracket includes a main bracket body and a mounting clip attached to the main bracket body. The mounting clip includes a pair of prongs configured to insert into a pair of holes in the structure and become secured to the structure.
F16M 13/02 - Other supports for positioning apparatus or articlesMeans for steadying hand-held apparatus or articles for supporting on, or attaching to, an object, e.g. tree, gate, window-frame, cycle
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
25.
RACK SHELF SYSTEMS AND METHOD FOR LOADING PAYLOADS INTO A RACK SHELF SYSTEM
In an embodiment a tray includes a base area having a top side, a bottom side, a rear end, peripheral sides and a front end, a plurality of flanges extending upward from the top side and arranged at the rear end and the peripheral sides, a pin, bolt or stud arranged at an outside of a flange arranged at the rear end or a hole arranged in the flange at the rear end configured to receive a pin, bolt or stud, a first plurality of restraining rings arranged at a first side flange at the first peripheral side and a second plurality of restraining rings arranged at a second side flange at the second peripheral side.
An aircraft-transport skid system includes a first outer frame rail, a second outer frame rail, a first lower inner frame rail, a second lower inner frame rail, and a plurality of lateral support rails connecting the first outer frame rail, the second outer frame rail, the first lower inner frame rail, and the second lower inner frame rail. The first outer frame rail, the second outer frame rail, the first lower inner frame rail, and the second lower inner frame rail are parallel to one another;
A rotorcraft propulsion system includes a mast coupled to a rotor assembly, a gear coupled to the mast, the gear during use producing an axial reaction force, a flexure shaft extending from the gear, where the flexure shaft does not rotate with the gear and the flexure shaft flexes in response to radial loads from the gear, and a load cell on the flexure shaft to measure the axial reaction force.
B64D 35/00 - Transmitting power from power plants to propellers or rotorsArrangements of transmissions
G01L 3/10 - Rotary-transmission dynamometers wherein the torque-transmitting element comprises a torsionally-flexible shaft involving electric or magnetic means for indicating
Techniques control a utility vehicle. Such techniques involve setting a set of maximum motion limits imposed on the utility vehicle to a set of initial values. Such techniques further involve receiving a set of input signals from a set of sensors, the set of input signals indicating a set of current physical attributes of the utility vehicle. Such techniques further involve, based on the set of input signals, changing at least one maximum motion limit of the set of maximum motion limits from an initial value to an updated value which is different from the initial value.
B60L 15/20 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train for control of the vehicle or its driving motor to achieve a desired performance, e.g. speed, torque, programmed variation of speed
B60K 31/00 - Vehicle fittings, acting on a single sub-unit only, for automatically controlling vehicle speed, i.e. preventing speed from exceeding an arbitrarily established velocity or maintaining speed at a particular velocity, as selected by the vehicle operator
B60L 50/60 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by batteries
29.
Aircraft with Hybrid Power Supply and Unobstructed Cabin Door Access
An aircraft having unobstructed cabin door access includes a hybrid power drive with a combustion engine connected to an electricity generating machine. Components of the hybrid power drive are positioned throughout the aircraft to provide a weight distribution having an aft bias. The aircraft further includes a forward swept wing and a cabin door positioned forward of the forward swept wing, such that access into a fuselage of the aircraft via the cabin door is unobstructed by the forward swept wing.
Double flanged clevis pins are provided in aircraft flight control pulley systems and are mounted between the opposed side walls of the pulley mounting bracket at a closely spaced separation distance relative to a respective pulley and the cable retained within the pulley groove. The outboard facing surface of each of the clevis pin flanges is positioned in abutting relationship with an adjacent inboard facing surface portion of a respective one of the opposed side walls of the mounting bracket while outboard ends of the clevis pin extend coaxially outwardly therefrom and through the adjacent mounting bracket side wall. The central pin section of the clevis pin is therefore closely spaced above an adjacent portion of the circumferential edge of the pulley in which an aircraft control cable is received. Such an assembly thereby serves to maintain the control cable within the pulley groove and prevents one or both of the bracket side walls from being deformed over time that may in turn undesirably chafe the control cable.
B64C 19/00 - Aircraft control not otherwise provided for
F16B 21/12 - Means without screw-thread for preventing relative axial movement of a pin, spigot, shaft, or the like and a member surrounding itStud-and-socket releasable fastenings without screw-thread by separate parts with locking-pins or split-pins thrust into holes
F16C 13/00 - Rolls, drums, discs, or the likeBearings or mountings therefor
A configurable aircraft aisle flooring system which includes a flat floor configuration and a drop-down aisle configuration. The flat floor configuration provides floor panels positioned to span across a trough of an aircraft aisle to form a level surface between upper sections of an aircraft aisle. The drop-down aisle configuration provides floor panels positioned below the upper section of the aircraft aisle to have a drop-down step between the upper sections of the aircraft aisle.
Techniques are directed to charging a battery of a utility vehicle. Such techniques involve receiving a geolocation signal which identifies a current location of the utility vehicle. Such techniques further involve generating a geolocation assessment result indicating whether the utility vehicle is currently within an early charge termination geographic area based on the geolocation signal. Such techniques further involve charging the battery in accordance with the geolocation assessment result, the battery being charged to a first charge threshold when the geolocation assessment result indicates that the utility vehicle is currently not within the early charge termination geographic area, and the battery being charged to a second charge threshold when the geolocation assessment result indicates that the utility vehicle is currently within the early charge termination geographic area. The second charge threshold is different from the first charge threshold.
Techniques are disclosed for offloading aircraft data. The aircraft data are received over a network data collection interface associated with an aircraft recording system (ARS). The ARS is adapted to produce aircraft-data messages via a message-broker proxy related to the data received. An associated message is received, and it is determined whether an event has occurred via an event detector process interface. Next, a tag is applied to the event based upon a determination that the event has occurred. The tagged event is then published via the message broker. A published event is received and then recorded to a file via a media recording process interface. It is then determined which data to offload from a recorded event file via a file manager. The associated data is then transmitted via a data offload pathway to a data hub.
G07C 5/00 - Registering or indicating the working of vehicles
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 technique is directed to managing vehicle access within a geographic region. The technique involves receiving a set of climate input signals that defines climate for the geographic region. The technique further involves, based on the set of climate input signals, performing a climate assessment operation that assesses whether to allow vehicle access within a set of geofenced areas overlying the geographic region. The technique further involves, based on a result of the climate assessment operation, providing an access control signal which controls vehicle access to the set of geofenced areas overlying the geographic region.
A component retainer, wherein the retainer comprises an annular-shaped body defining a central aperture, and a plurality of engagement tabs extending substantially orthogonally from the annular-shaped body. Each engagement tab comprises an engagement tab body and a retaining tooth integrally formed with the engagement tab body and extending radially inward toward a center of the central aperture.
A method for metal bonding includes providing at least two metal sheet assemblies wherein each metal sheet assembly includes at least one frame member and a flat metal sheet. Each frame member is placed onto the flat metal sheet to form a metal sheet assembly. The metal sheet assemblies are stacked upon one another to form a sheet stack, and the sheet stack is autoclaved to allow for bonding to occur between the flat metal sheet and the frame member of each metal sheet assembly. The sheet stack is removed from the autoclave and each metal sheet assembly is unstacked from the sheet stack. Each bonded metal sheet assembly then undergoes a roll forming process to provide at a curved metal sheet assembly.
B32B 37/10 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using direct action of vacuum or fluid pressure
B32B 15/01 - Layered products essentially comprising metal all layers being exclusively metallic
B32B 37/06 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the heating method
B32B 38/00 - Ancillary operations in connection with laminating processes
An aircraft is described and includes a fuselage; wings attached to the fuselage; and a torque box within the fuselage, the torque box including a side panel, the side panel comprising a composite laminate material including a plurality of stiffening beads integrated therewith. The plurality of stiffening beads may be integrated with the side panel and extend parallel to one another.
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
A golf car scorecard holder assembly, wherein the assembly includes a baseplate having a topside face, an underside face and a clip attachment portion. The assembly additionally includes a retention clip pivotally connectable to the clip attachment portion of the baseplate such that a pivot axis of the retention clip relative to the baseplate is adjacent the underside face of the baseplate. The assembly further includes a biasing device disposed between a backside of the retention clip and the topside face of the baseplate, the biasing device structured and operable to exert a closing force on the retention clip to bias the retention clip to a Closed position.
Methods and systems are described for a gearbox lockout device. It may be desirable in certain vehicles to lock a drive shaft within a gearbox for a period of time. Lockout embodiments under the present disclosure include a shaft configured to selectively engage the drive shaft via teeth. An inner and outer collar surrounding the shaft can be manipulated to restrict the movement of the shaft once the shaft's teeth are engaged with the teeth of the drive shaft. The system can be torqued up and locked in place. This can allow for more safe transporting of the vehicle, easier maintenance, or other advantages.
A low drag nacelle and pylon fairing for an aircraft includes a fairing configured to provide a low drag connection between a pylon and a nacelle. The fairing includes an aft-facing face formed between the nacelle and a trailing edge of the pylon with the aft-facing face being configured with a vent for exhausting air in the same direction as engine jet exhaust flow. The fairing includes aerodynamically formed curves providing a larger aft-facing face compared with traditional fairing arrangements. A substantial improvement in drag reduction is achieved by venting air into the space immediately beyond the aft-facing face.
Additively manufactured aircraft vent structures are provided with a one-piece frame which includes a substantially planar face plate defining a longitudinally elongate vent opening and a series of fixed-position vanes unitarily joined to the planar face plate which extend latitudinally across the vent opening. Each of the vanes may be curvilinear and provided such that unidirectional venting is established or may be in a V-shaped configuration of vane pairs such that multidirectional venting is established. Alternatively or additionally, the vanes may have a widthwise dimension between leading and trailing edges thereof such that the trailing edges of each vane terminally extends at least to a latitudinal plane defined by a leading edge of an immediately adjacent one of the vanes.
An aircraft seat includes a base frame; a seat frame rotatably connected to a top side of the base frame, wherein the seat frame is configured to rotate about a vertical axis; an internal gear plate fixedly connected to the base frame, wherein the internal gear plate includes gear teeth arranged around an opening; a guide plate fixedly connected to a bottom side of the seat frame, wherein the guide plate includes a first guide wall and a second guide wall; and a cart attached to the guide plate between the first guide wall and the second guide wall, wherein the cart includes pawl teeth configured to mesh with the gear teeth, wherein the cart is movable along the guide plate to mesh the pawl teeth with a portion of the gear teeth.
A rotor-blade assembly has a lock system to enable and disable a folding degree of freedom and a pitching degree of freedom of a rotor blade. A grip couples a blade to a hub, the blade being pivotable about a fold axis relative to the grip, the blade and grip being pivotable together about a pitch axis relative to the hub. A fold lock prevents folding of the blade in a fold-lock position and allows folding of the rotor blade in a pitch-lock position, and a pitch lock allows pitch movement of the rotor blade in a fold-lock position and prevents pitch movement of the rotor blade in the pitch-lock position. A rotary actuator carried by the grip has actuator arms coupled through linkage to the pitch lock and fold lock, and the actuator is configured for moving the pitch lock and fold lock between the fold-lock and pitch-lock positions.
Lightning strike protection for composite propellers is provided by a bonding tab assembly which is electrically bonded to an electrically conductive protective band fixed to a leading edge of the composite propeller blade. The bonding tab establishes an electrically conductive path for a lightning strike on the protective band to be directed to the propeller hub thereby providing lightning strike protection to the propeller. The bonding tab assembly may include a mounting bracket having a lower mounting flange and an upright mounting plate, the lower mounting adapted to being attached to a counterweight clamp attached to a metallic blade collar surrounding the propeller blade shank. A bonding tab is attached to the upright mounting plate of the mounting bracket and adapted to being brought into spring-biased contact with a portion of the protective metal band affixed to the leading edge of the composite propeller blade.
Force absorbing shoulder belt assemblies for vehicle seats (e.g., aircraft seats) absorb and thereby reduce shoulder belt forces on the upper torso of a seat occupant in the event of a rapid deceleration event (e.g., a vehicle crash). A one-piece base mounting plate is provided which includes a central base plate section, a forwardly bent section and a forwardly projecting section extending from the forwardly bent section subjacent to the central base plate section. A pair of aligned perforations formed through the central base plate section laterally adjacent to the forwardly projecting section may be provided. The exertion of a deceleration force of predetermined magnitude on the shoulder web strap of an inertial reel attached to the forwardly projecting section along a force vector will cause a shear pin bolt normally connecting the central base plate section to the subjacent forwardly projecting section to shear thereby separating the latter from the former which in turn causes the forwardly bent portion to unbend in a direction of the force vector and/or to tear the central base plate section along the aligned perforations thereby absorbing at least a portion of the deceleration force.
Force absorbing shoulder belt assemblies for vehicle seats, especially aircraft seats, are provided. The shoulder belt assemblies will include a box structure defining an interior space having an open rear end and adapted to being fixed to adjacent vehicle structure, a block of a compressible material positioned within the interior space of the box structure, a rear plate in pressing contact with the rear face of the block of compressible material, and an inertial reel assembly carried by the rear plate and including a shoulder web strap which extends through the rear plate, the block of compressible material and the box structure. When a deceleration force of predetermined magnitude is exerted on the shoulder web strap of the inertial reel, the rear plate will responsively be forcibly pressed against the block of compressible material thereby compressively crushing the compressible material within the box structure to thereby absorb shock force of the shoulder web strap against vehicle seat occupant's torso.
An aircraft that has a blade position control system (BPCS). The BPCS includes an actuator, a multilobe component configured for at least one of longitudinal movement along a mast axis as a function of actuation of the actuator and rotational movement relative to the mast axis as a function of actuation of the actuator. Movement of the multilobe component selectively restricts at least one of pitch movement and folding of a plurality of rotor blades.
Aircraft recording system configuration devices and methods are disclosed. The systems and methods provide a context-sensitive interface for rapid configuration. An aircraft recording system is operatively coupled to a data collection interface that is powered off and in an unconfigured state upon an initial installation of the aircraft recording system configuration device onboard an aircraft. A physical interface is disposed on an outer surface of the aircraft recording system configuration device, such that activating the physical interface causes an initial configuration of the aircraft recording system to be established. An indicator is further provided that disposed on the outer surface of the aircraft recording system configuration device, wherein the indicator is configured to indicate different states of the aircraft recording system.
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
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
51.
Neural Network Supported Augmented Reality for Technician Support
A system for technician support includes at least one processor, at least one stored artificial intelligence (AI) model stored therein, and a computer program for execution by the processor. The computer program includes instructions for determining an engineering process to be performed on a workpiece, and having one or more elements associated with an assembly process or a maintenance process for the workpiece, receiving sensor data from one or more sensors, the sensor data reflecting at least a physical state of the workpiece, providing the sensor data to the at least one AI model, causing the at least one AI model to process the sensor data to generate at least one classification result that indicates whether the sensor data indicates whether each element was correctly performed, and validating execution of the engineering process in response to each element being correctly performed, and providing a visual notification to a user.
G05B 19/418 - Total factory control, i.e. centrally controlling a plurality of machines, e.g. direct or distributed numerical control [DNC], flexible manufacturing systems [FMS], integrated manufacturing systems [IMS] or computer integrated manufacturing [CIM]
Techniques are disclosed for data collection in connection with one or more aircraft. Avionics inputs are received, at an avionics data collection platform, regarding a plurality of avionics parameters. The avionics parameters may be associated with components of the aircraft and collected by way of avionics sensors. The avionics parameters are aggregated by way of the data collection platform. The aggregated avionics parameters are multiplexed at the data collection platform. The multiplexed and aggregated plurality of avionics parameters are transmitted over loosely-coupled networking connections to an aircraft recording system. The aircraft recording system includes a network collector and an embedded microcontroller system. A prioritized aggregation of the avionics parameters is provided by way of the network collector and the embedded microcontroller system to external systems.
A repositionable pocket for an aircraft having a rigid pocket wall pivotally attached to the aircraft sidewall and at least one strap assembly connecting the pocket to the sidewall. The strap assembly has a first end fixable to the sidewall and a second end repositionably fastened to the pocket. The strap is preferably made to be elastic and urges the attached pocket into a closed orientation thereby securing any stowed items between the pocket and the aircraft sidewall. Strap adjustability accommodates different sized objects for stowage.
Blended falx winglets are provided which include an initial winglet section adapted to being attached to an aircraft wingtip, and forward and aft sub-winglets extending outwardly and upwardly from the initial winglet section. The forward and aft sub-winglets may have respective curved transition sections with different radii of curvature, e.g., the radius of curvature of the curved transition section of the forward sub-winglet may be greater than the radius of curvature of the curved transition section of the aft sub-winglet.
Airfoil venting systems are provided which include an airfoil (e.g., a winglet or an aircraft wing) having leading and trailing edges and an internal channel adapted to being fluid-connected to an on-board aircraft system which in use requires air to be exhausted. A series of venting apertures are positioned on at least a portion of the trailing edge of the airfoil and fluid-connected to the internal channel whereby air from the on-board aircraft system can be exhausted therethrough.
Multi-way valves for conditioned airflow control systems. In embodiments, a multi-way valve includes an intake configured to receive an airflow as in input to the multi-way valve, a plurality of outlets, each of the plurality of outlets configured to provide at least a portion of the airflow as an output of the multi-way valve, a gate assembly including a gate opening configured to allow air to flow through the gate opening, and an actuator configured to move the gate assembly to a position configured to allow the airflow to concurrently flow through the gate opening to a first set of outlets of the plurality of outlets while preventing the airflow from flowing to a second set of outlets of the plurality of outlets.
F16K 11/076 - Multiple-way valves, e.g. mixing valvesPipe fittings incorporating such valvesArrangement of valves and flow lines specially adapted for mixing fluid with all movable sealing faces moving as one unit comprising only sliding valves with pivoted closure members with sealing faces shaped as surfaces of solids of revolution
57.
PASSIVE DEHUMIDIFIER FOR ENVIRONMENT CONTROL UNITS
Passive dehumidifiers for environmental control units (ECUs) are presented. In embodiments, the passive dehumidifier may include a plenum with an intake to receive an airflow with moisture (e.g., water droplets, water vapor, etc.) present. Upon entering the passive dehumidifier, the airflow may experience a reduction in inertia and a change from a first direction to a second direction. The directional change may be sharp enough (e.g., greater than 90 degrees) that the moisture in the airflow are not able to follow the airflow and are instead directed to impinge and be collected on a collector wall, which may include one or more hydrophilic surfaces facilitating the impinged water droplets to form a liquid film upon impact on the collector wall. The film may collapse due to gravity and may be drained out through and/or on a hydrophilic screen mesh (e.g., hydrophilic screen mesh surface) on the collector wall surface(s).
B01D 45/06 - Separating dispersed particles from gases or vapours by gravity, inertia, or centrifugal forces by utilising inertia by reversal of direction of flow
B01D 45/08 - Separating dispersed particles from gases or vapours by gravity, inertia, or centrifugal forces by utilising inertia by impingement against baffle separators
58.
BATTERY COLD PLATE AND CHASSIS WITH INTERLOCKING JOINTS
A cold plate is couplable with a component for dissipating heat from a component. The cold plate includes a top plate coupled with a bottom plate to receive a cooling medium therebetween. The top plate includes a body and a plurality of walls extending from the body, wherein each wall of the plurality of walls includes a recess extending within the wall. The bottom plate includes a body and a plurality of walls extending from the body such that an end portion of each wall of the bottom plate is inserted within the recess of each wall of the top plate to form an interlocking joint.
F28D 1/03 - Heat-exchange apparatus having stationary conduit assemblies for one heat-exchange medium only, the media being in contact with different sides of the conduit wall, in which the other heat-exchange medium is a large body of fluid, e.g. domestic or motor car radiators with the heat-exchange conduits immersed in the body of fluid with plate-like or laminated conduits
F28D 21/00 - Heat-exchange apparatus not covered by any of the groups
F28F 3/12 - Elements constructed in the shape of a hollow panel, e.g. with channels
An exemplary tiltrotor aircraft having a vertical takeoff and landing (VTOL) flight mode and a forward flight mode includes tiltable rotors located at forward boom ends, tiltable ducted fans located at wings aft of the forward boom ends, and aft rotors located on aft boom portions.
A rotating pylon assembly for aircraft thrust vectoring control. In embodiments, the rotating pylon assembly of embodiments includes a rotating sleeve disposed within a fixed boom of the aircraft, and configured to support a rotor assembly. The rotating pylon assembly includes a bearing assembly configured to functionally couple the rotating sleeve against an inner surface of the fixed boom. The bearing assembly enables the rotating sleeve to rotate against the inner surface of the fixed boom and about a longitudinal axis of the fixed boom. An actuator is configured to rotate the rotating sleeve about the longitudinal axis of the fixed boom. The rotating sleeve may cause the rotor assembly to be rotated or swung about the longitudinal axis of the fixed boom to position the rotor assembly in a position to vector the thrust provided by the rotor assembly based on a control command.
A seat system with a seat back element including a vertical support disposed in a seat back interior region, and one or more first connector portions attached to the vertical support and aligned in a first direction, and a seat back panel having one or more second connector portions attached to an interior surface and configured to connect to the one or more first connector portions. The seat back panel has a first sidewall disposed at a first side and further has a second sidewall disposed on at a second side opposite the first side. The seat back panel has an upper wall portion forming a contiguous first surface with the first sidewall and second sidewall. The second connector portions connect to the first connector portions and attach the seat back panel to the seat back element.
A method of forming a composite part is described and includes connecting a layup form tool to a vacuum source; overlaying a release film on a surface of the layup form tool; engaging the vacuum source to affix the release film to the surface of the layup form tool using vacuum pressure; overlaying at least one sheet of composite material on the release film affixed to the surface of the layup form tool to form the composite part; and removing the formed composite part from the layup form tool.
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
B29C 70/56 - Tensioning reinforcements before or during shaping
A passenger seat comprising a first armrest assembly; a second armrest assembly, the second armrest assembly comprising: a side panel comprising an armrest portion and a side portion, the side panel comprising a first magnet secured on an interior side of the side panel; an interior compartment disposed within the side panel; and an access panel in a removably attached position to the side panel, the access panel comprising a second magnet secured on an interior side of the access panel, the first magnet being aligned with the second magnet when the access panel is in the removably attached position.
A fuel tank has an outer shell, a media guide disposed within the space at least partially defined by the outer shell, the media guide being configured to receive a media within cells of the media guide. The fuel tank further has a spring space disposed between the media guide and the outer shell and a compressible spring disposed within the spring space and connected between the outer shell and the media guide.
An aircraft windscreen comprises a plurality of liquid crystal display (LCD) films positioned on or within various portions of the windscreen to define a corresponding plurality of zones. The opacity of the LCD films are individually and separately controllable by control circuitry in communication with user controls to allow a user to darken or lighten portions of the various LCD films to achieve a desired level of gradient tint in the defined zones to block external light, such as sunlight, from the aircraft.
A life vest container, a method for assembling a life vest container and a method for removing a life vest from a life vest container are disclosed. In an embodiment a leg rest includes linkages of a deployment and stowage mechanism, the linkages of the deployment and stowage mechanism being connectable to a seat, a mounting fixture connected to the linkages and a container secured to the mounting fixture, the container being configured to store a life vest.
In an embodiment a leg rest includes a mounting fixture, an extension frame and a deployment and stowage mechanism configured to deploy the leg rest from or stow the leg rest to a seat, wherein the extension frame is movably connected to the mounting fixture so that the extension frame moves relative to the mounting fixture when the deployment and stowage mechanism moves the leg rest relative to the seat.
An aircraft door handle and lighting system for an entryway on an aircraft. The system includes a face plate with recessed areas. One recessed area includes a handle positioned for a user to grasp when entering or exiting the aircraft, and another recessed area includes a light source configured to direct light towards one or more stairs. Another recessed area is configured on the opposite side of the entryway and includes a light source configured to direct light towards the stairs.
A wireless charging table for use in an aircraft includes a frame assembly for mounting the wireless charging table within the aircraft; a table leaf support coupled to the frame assembly and maneuverable between a stowed position and a deployed position; a main table leaf mounted to the table leaf support and having a power unit; and an electrical system to provide power to the power unit when the table leaf support is in the deployed position. When the table leaf support is in the deployed position, an electrical connection is established between a power source and the power unit, and when the table leaf support is in the stowed position, the electrical connection is broken between the power source and the power unit. The power unit is to provide wireless charging to one or more devices when the electrical connection is established.
A golf cart includes a golf cart body and a golf cart windshield supported by the golf cart body. The golf cart windshield is constructed and arranged to provide a driver of the golf cart with a windshield view of an environment in front of the golf cart. The golf cart further includes a windshield-level display device coupled with the golf cart body. The windshield-level display device is constructed and arranged to provide the driver of the golf cart with an electronic view of golf cart information. The windshield view of the environment in front of the golf cart and the electronic view of the golf cart information are provided at a same height to the driver of the golf cart. Additionally, the electronic view is provided at a predefined distance above a bottom of the windshield view.
Techniques to control a utility vehicle involve initially setting a maximum speed constraint imposed on the utility vehicle to an initial value. Such techniques further involve receiving a state of charge signal that indicates a current state of charge of a lithium battery which provides electric power for utility vehicle propulsion. Such techniques further involve, based on the state of charge signal that indicates the current state of charge of the lithium battery, adjusting the maximum speed constraint imposed on the utility vehicle from the initial value to an adjusted value that is different from the initial value.
B60L 15/10 - Methods, circuits or devices for controlling the propulsion of electrically-propelled vehicles, e.g. their traction-motor speed, to achieve a desired performanceAdaptation of control equipment on electrically-propelled vehicles for remote actuation from a stationary place, from alternative parts of the vehicle or from alternative vehicles of the same vehicle train for automatic control superimposed on human control to limit the acceleration of the vehicle, e.g. to prevent excessive motor current
B60L 7/14 - Dynamic electric regenerative braking for vehicles propelled by AC motors
B60L 50/60 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by batteries
B60L 58/12 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries responding to state of charge [SoC]
A system for storage includes a drawer configured to open with a push, a drawer base, and a seat. A drawer face of the drawer is free of a handle. The drawer opens in a first direction along two or more slides. The drawer base is under the drawer, the drawer being coupled to the drawer base. The seat is over the drawer. The seat faces perpendicular to the first direction.
A heated seat for an aircraft includes a heating element disposed on a cushioning material and overlayed by an upholstery. The heating element includes a flexible base and a plurality of thin and flexible heating coils that conform to the seat shape such that no cushioning material is applied between the heating element and the upholstery. By providing direct contact between the heating element and the upholstery, smaller heating elements requiring less electrical power may be used to sufficiently heat the seat compared with traditional heating elements.
A golf bag retention yoke comprising at least one beverage container holder well and/or at least one golf tee holder aperture integrally formed therein. The at least one beverage container holder is structured and operable to removably retain a beverage container and the least one golf tee holder aperture structured and operable to removably retain a golf tee.
B60N 3/10 - Arrangements or adaptations of other passenger fittings, not otherwise provided for of receptacles for food or beverages, e.g. refrigerated
A mechanical logic gate system for an aircraft seat which includes a flywheel operatively connected to a pivot tube and control cables. The control cables attach to swivel locking and tracking mechanisms which enable swiveling and tracking of the aircraft seat. Spring pin plungers are configured to extend into the flywheel for locking it in place. When both spring pin plungers are retracted from the flywheel via control cables, the aircraft seat is disabled from swiveling.
A heated battery cell conductor includes an upper conductor having a plurality of tabs each configured for direct physical contact with a battery terminal at a top end of one of a plurality of battery cells, respectively. A lower conductor includes a plurality of tabs each configured for direct physical contact with a battery terminal at a bottom end of one of the battery cells, respectively. The upper conductor and the lower conductor each include a conductor substrate configured for conducting an electrical current, a thermally conductive and electrically isolated layer disposed on the conductor substrate, a channel formed in the thermally conductive and electrically isolated layer, and a resistive heating element disposed in the channel such that the upper conductor and the lower conductor each conduct heat to the battery cells via the resistive heating element.
H01M 10/42 - Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
H01M 10/48 - Accumulators combined with arrangements for measuring, testing or indicating the condition of cells, e.g. the level or density of the electrolyte
H01M 50/213 - Racks, modules or packs for multiple batteries or multiple cells characterised by their shape adapted for cells having curved cross-section, e.g. round or elliptic
H01M 50/503 - Interconnectors for connecting terminals of adjacent batteriesInterconnectors for connecting cells outside a battery casing characterised by the shape of the interconnectors
H01M 50/507 - Interconnectors for connecting terminals of adjacent batteriesInterconnectors for connecting cells outside a battery casing comprising an arrangement of two or more busbars within a container structure, e.g. busbar modules
82.
Method and Apparatus for Embedded Heating of Battery Cell Holders
A heated battery cell holder includes an upper cell holder having a plurality of holders each configured for securing an upper portion of one of a plurality of battery cells, respectively. A lower cell holder includes a plurality of holders each configured for securing a lower portion of one of the battery cells, respectively. An upper heating element is embedded in the upper cell holder for heating the upper portion of each of the battery cells, and a lower heating element is embedded in the lower cell holder for heating the lower portion of each of the battery cells.
H01M 10/637 - Control systems characterised by the use of reversible temperature-sensitive devices, e.g. NTC, PTC or bimetal devicesControl systems characterised by control of the internal current flowing through the cells, e.g. by switching
H01M 10/653 - Means for temperature control structurally associated with the cells characterised by electrically insulating or thermally conductive materials
H01M 50/291 - MountingsSecondary casings or framesRacks, modules or packsSuspension devicesShock absorbersTransport or carrying devicesHolders characterised by spacing elements or positioning means within frames, racks or packs characterised by their shape
A system and method for a central control arm with tensioning for a lateral tracking and swivel system in a seat are provided. The control system includes a central control arm body, where the central control arm body has one or more attachment points and a cable interface feature, one or more paddle arms, and one or more adjustment mechanisms attached to the central control arm body, where each adjustment mechanism of the one or more adjustment mechanisms is aligned longitudinally along the central control arm body with a respective attachment point of the one or more attachment points, where each adjustment mechanism of the one or more adjustment mechanisms has a set screw that impinges on a face of a paddle arm of the one or more paddle arms.
Embodiments are directed to operating a multi-engine aircraft during a cruise flight condition. A first engine is put off-line during flight while allowing a second engine to continue operating. The second engine provides sufficient power to maintain the multi-engine aircraft in the cruise flight condition. An outside air temperature, a first engine temperature, and/or an engine oil temperature is monitored and, when the temperature is below a predetermined threshold, the engine oil for the off-line first engine is warmed. The off-line engine oil may be warmed by continuously or periodically cranking the first engine without restarting the first engine. Alternatively, the engine oil may be warmed using a heat exchanger, such as an air-to-oil or oil-to-oil heat exchanger, or by using electronic heaters on an oil tank.
An aircraft seat includes a base frame; a seat frame rotatably connected to a top side of the base frame, wherein the seat frame is configured to rotate about a vertical axis; a slot plate connected to the top side of the base frame, wherein the slot plate has a slot in a top surface of the slot plate; and a pin mount connected to a bottom side of the seat frame, wherein the pin mount has a pin that protrudes downward, wherein the pin is configured to protrude into the slot when the seat frame is rotated into a first orientation relative to the base frame.
A seat release system and device, the system including an interface assembly that provides actuation signaling, an actuation device that communicatively provides mechanical motion in response to the actuation signaling, a cable connected to the actuation device, and a recline release cylinder having a gas release button and a release lever at a first end, and having a cylinder piston arm in the recline release cylinder at a second end. The release lever is attached to a second end of the cable where the cable moves the release lever in response to the mechanical motion of the actuation device. The gas release button vents the recline release cylinder to atmosphere in response to being depressed as a result of the cable moving the release lever. The cylinder piston arm may move in the recline release cylinder in response to the gas release button being depressed.
A curved screen skylight for an aircraft includes a curved display screen which is configured to display imagery provided from a camera positioned on the aircraft or preloaded imagery stored on a memory storage device. The curved screen display conforms to an aircraft overhead panel and can be secured using flanges extending from the overhead panel.
G06F 3/0482 - Interaction with lists of selectable items, e.g. menus
B64D 11/00 - Passenger or crew accommodationFlight-deck installations not otherwise provided for
G06F 3/0484 - Interaction techniques based on graphical user interfaces [GUI] for the control of specific functions or operations, e.g. selecting or manipulating an object, an image or a displayed text element, setting a parameter value or selecting a range
H04N 7/18 - Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast
Propeller restraint kits for turboprop aircraft are provided which include at least one, and preferably a pair, of propeller restraint systems. Each propeller restraint system will preferably include an open-ended propeller restraint boot that may be formed of a flexible and durable fabric material which is sized and configured for placement over the tip of a propeller blade. A cowling attachment assembly is provided in the kit and is adapted to being attached to an aircraft cowling skin. A propeller boot tether strap of predetermined length interconnects the propeller restraint boot and the cowling attachment assembly. The cowling attachment assembly includes (i) a quick disconnect (QD) pin assembly connected to a terminal end of the propeller boot tether strap, and (ii) a pin receiver adapted to being positionally attached to an interior portion of the aircraft cowling skin.
An aircraft comprising a fuselage; a vent disposed through a bottom surface of the fuselage; and a drainage system for transporting fluid leaked from a fluid source out of the fuselage via the vent in response to a first condition, the drainage system comprising a container having a top and a bottom; and a siphon tube within the container, the siphon tube having an inlet and an outlet and comprising a 180 degree bend between the inlet and the outlet.
An embodiment seat control system includes a control board having a processing unit, wherein the processing unit has one or more processors and one or more memories, and a mainboard. The processing unit is communicatively attached to the mainboard and mainboard has a plurality of receptacles and mainboard includes one or more communication buses between at least one of the plurality of receptacles and the processing unit. The system further has one or more system modules, where each module of the one or more system modules is configured to be connected to a respective receptacle of the plurality of receptacles, where each module of the one or more system modules implements a functional capability of a seat, and where the one or more system modules are nondestructively removeable from the mainboard.
A vehicle canopy, wherein the canopy comprises a main panel having a top face and a bottom face; a front wall extending from a front of the main panel; a back wall extending from a rear of the main panel; a pair of opposing sidewalls extending from opposing sides of the main panel; and one or more support rib integrally formed with the main panel and extending laterally across the main panel, the one or more support rib structured and operable to provide rigidity and stiffness to the main panel to prevent deformation of the main panel within the target zone.
B60J 7/16 - Non-fixed roofsRoofs with movable panels of non-sliding type, i.e. movable or removable roofs or panels, e.g. let-down tops or roofs capable of being easily detached or of assuming a collapsed or inoperative position non-foldable
A door management system on an aircraft includes a fuselage extending along a longitudinal axis in a fore-aft direction parallel to forward flight, an opening in a sidewall of the fuselage, a door mounted on the sidewall to slide in the fore-aft direction between a closed position covering the opening and an open position revealing the opening, a cable attached to the fuselage and the door and a speed governor operatively coupled to the cable to limit a velocity of the door as it moves between the open position and the closed position.
E05F 15/643 - Power-operated mechanisms for wings using electrical actuators using rotary electromotors for horizontally-sliding wings operated by flexible elongated pulling elements, e.g. belts, chains or cables
B64C 1/14 - WindowsDoorsHatch covers or access panelsSurrounding frame structuresCanopiesWindscreens
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
E05F 11/04 - Man-operated mechanisms for operating wings, including those which also operate the fastening for wings in general, e.g. fanlights with cords, chains, or cables
An aircraft nacelle includes a forward cruise inlet, a forward-cruise-inlet conduit coupled to the forward cruise inlet and operable to supply air from the forward cruise inlet to an engine housed by the aircraft nacelle, an inlet barrier filter, an inlet-barrier-filter compartment coupled to the inlet barrier filter, a plurality of gills coupled between the inlet-barrier-filter compartment and the engine and operable to be in an open state and a closed state, a filter-purge door coupled to the inlet-barrier-filter compartment and operable to be in a closed state and an open state. When the plurality of gills are in the closed state and the filter-purge door is in the open state, air from the filter-purge door flows from the inlet-barrier-filter compartment through the inlet barrier filter.
A machining fixture counterbore bolt fitting includes a counterbore bolt, (SHCS) screw and jam nut. The counterbore bolt defines an axial bore therethrough, sized to location clearance or sliding fit receive the screw and a counterbore sized to running fit receive a head of the screw and of a depth for the head of the screw to bear on the bottom of the counterbore. The counterbore bolt is threaded through a machining fixture to bring a distal end of the bolt into contact with a surface of a part to be machined, with the axial bore around a screw-threaded bore in a fixture mating surface of the part. The screw is threaded into the screw-threaded bore, holding the part against movement with respect to the fixture. The head of the screw bears on the counterbore bottom, pulling the fixture mating surface against the bolt shaft threaded through the machining fixture.
A variable-sweep wing for a tiltrotor aircraft includes a fuselage link coupled to the fuselage and a pylon link coupled to a pylon. A wing airframe has a root end pivotably coupled to the fuselage link and a tip end pivotably coupled to the pylon link. A driveshaft is coupled between the fuselage link and the pylon link and is positioned within the wing airframe. The driveshaft is operable to transmit torque from the main gearbox to a proprotor gearbox. A crank is coupled between the fuselage link and the pylon link and is positioned within the wing airframe. The fuselage link, the pylon link, the driveshaft and the crank form a linkage such that pivoting the crank relative to the fuselage link causes the wing airframe to shift between a substantially straight wing configuration for low-speed forward flight and a swept wing configuration for high-speed forward flight.
A system for retracting a center console of an aircraft having a cockpit with an interior area includes the center console being positioned within the interior area of the cockpit and supporting one or more aircraft controls; a mechanism supporting the center console and to facilitate movement of the center console between an extended position and a retracted position; a control system for operating the mechanism to facilitate movement, the control system having at least one sensor for monitoring the interior space of the cockpit; the at least one sensor is to determine when a person is entering the cockpit; and the control system is to activate movement of the center console to the retracted position upon the sensor determining the person is entering the cockpit.
A charge control system includes a lithium battery configured to provide lithium battery power to a set of electrical loads, a user signaling device, and control circuitry coupled with the lithium battery and the user signaling device. The control circuitry is operative to: (A) detect availability of charge from an external charger, (B) in response to detection of the availability of charge from the external charger and prior to controlling the external charger to adjust the amount of charge stored by the lithium battery, perform a set of pre-charging assessment operations, and (C) based on the set of pre-charging assessment operations, provide a user notification via the user signaling device, the user notification indicating whether the lithium battery is properly setup for charge adjustment. When the user signaling device generates the user notification, the user is informed that the utility vehicle is properly connected to the external charger.
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
B60L 53/36 - Means for automatic or assisted adjustment of the relative position of charging devices and vehicles by positioning the vehicle
B60L 58/12 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries responding to state of charge [SoC]
99.
Inner member for main rotor centrifugal force bearing
A back-to-back spherical bearing assembly for a rotary system of a rotary aircraft includes a spherical bearing member having an interior cavity and a spherical bearing surface defining a bearing focal point, a first elastomeric and a second elastomeric bonded to the spherical bearing surface on opposite sides of the bearing focal point, an inboard attachment bonded to the first elastomeric and configured to be secured to a rotor hub of the rotary system, and an outboard attachment bonded to the second elastomeric and configured to be secured to a rotor blade of the rotary system.
A lightweight electric vehicle includes a chassis, a pair of rear wheel assemblies, a pair of front wheel assemblies, a front suspension system, a rear suspension system, a pedestal supported by the chassis, a frontmost seat supported by the pedestal, a rearmost seat configured to accommodate a plurality of occupants and supported by the chassis, a floorboard coupled the chassis, and an electric motor configured to drive at least one of the pair of front wheel assemblies or the pair of rear wheel assemblies. The rearmost seat faces forward. At least a portion of the rearmost seat is located longitudinally rearward of an axis extending through a center of the pair of rear wheel assemblies. The floorboard is substantially flat such that a first footwell in front of the frontmost seat and a second footwell in front of the rearmost seat are coplanar.
B62D 21/02 - Understructures, i.e. chassis frame on which a vehicle body may be mounted comprising longitudinally or transversely arranged frame members
B60G 3/06 - Resilient suspensions for a single wheel with a single pivoted arm the arm being essentially transverse to the longitudinal axis of the vehicle the arm being rigid
B60G 3/10 - Resilient suspensions for a single wheel with a single pivoted arm the arm being essentially transverse to the longitudinal axis of the vehicle the arm itself being resilient, e.g. leaf spring
B60G 3/20 - Resilient suspensions for a single wheel with two or more pivoted arms, e.g. parallelogram all arms being rigid
B60G 11/04 - Resilient suspensions characterised by arrangement, location, or kind of springs having leaf springs only arranged substantially parallel to the longitudinal axis of the vehicle
