One embodiment is a rotor assembly for an aircraft, the rotor assembly comprising a plurality of rotor blades, wherein at least one of the rotor blades comprises a rotor alignment drag assembly comprising a drag structure on a surface of the at least one of the rotor blades, wherein the drag structure is moveable between a first position in which the drag structure is stowed within the at least one of the rotor blades, and a second position in which the drag structure is extended from the surface of the at least one of the rotor blades; and an actuation mechanism for moving the drag structure from the first position to the second position when a speed of the rotor assembly falls below a first threshold speed.
A tactile signal seat belt sleeve has tactile signal producing elements arrayed along a sleeve that is adapted to fit over a seat belt for a vehicle, such as an aircraft. The elements may be arranged, for example, along the body-facing side of the belt. Each sleeve incorporates a signal-receiving element that allows for the activation of vibration-producing motors embedded in the fabric of the seat belt sleeve or belting. Vibration motors, such as piezoelectric devices, can be used to produce the tactile feedback. The haptic feedback assembly is connected to an interface unit that uses data from aircraft systems to sense, for example, the aircraft altitude and pitch, roll and yaw system. The interface unit generates signal to haptic devices to create appropriate vibrations patterns to the sleeve. The vibrations may be used to indicate directions of turn using output signals from various navigations systems.
An entry step lighting system for a deployable aircraft stairway. The system includes steps that having integrated light sources that direct and provide illumination to the steps. Some light sources illuminate strip lenses which indicate proximity to the step edges. Light emitted by a second group of light sources is directed into an angled face established on a riser wall between each step. The light bounces off of each angled face to illuminate the step below.
A method and system for controlling a fluid valve are described that avoid the effects of hysteresis. In hysteresis, the power signals associated with a valve position are different on the upstroke and downstroke. As a result, predicting the valve position can be difficult if you only know the current power signal. Instead of using upstrokes and downstrokes, a valve can momentarily be set to zero power, or a rest position when receiving a new command signal. This way the command signal is applied from a zero power or rest position, making the valve position more predictable and accurate.
F16K 37/00 - Special means in or on valves or other cut-off apparatus for indicating or recording operation thereof, or for enabling an alarm to be given
F16K 1/22 - Lift valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with pivoted closure members with pivoted discs or flaps with axis of rotation crossing the valve member, e.g. butterfly valves
G05B 15/02 - Systems controlled by a computer electric
5.
TILTED PROPELLERS FOR ENHANCED DISTRIBUTED PROPULSION CONTROL AUTHORITY
An aircraft comprises a fuselage, a plurality of support structures coupled to the fuselage, and a first propeller and a second propeller connected to a motor and symmetrically distributed along the plurality of support structures, the first propeller configured to create a first thrust having a first horizontal force vector and the second propeller configured to create a second thrust having a second horizontal force vector. A summation of the first and second horizontal force vectors is substantially zero when the first thrust is substantially equal to the second thrust, and a first rotational axis of the first propeller and a second rotational axis of the second propeller are substantially coplanar with a vertical axis disposed between the first and second propeller. A movement of the aircraft is controlled by selectively increasing or decreasing a thrust of either the first propeller or the second propeller.
Techniques control a utility vehicle. Such techniques involve storing electric power in a lithium battery of the utility vehicle. Such techniques further involve operating a motor controller of the utility vehicle in a normal mode in which the motor controller provides electric power from a lithium battery of the utility vehicle to an electric motor of the utility vehicle to turn one or more ground engaging members of the utility vehicle. Such techniques further involve, after operating the motor controller in the normal operating mode, operating the motor controller in a walkaway mode in which the motor controller configures the electric motor to provide braking torque.
B60L 53/00 - Methods of charging batteries, specially adapted for electric vehicles; Charging stations or on-board charging equipment therefor; Exchange 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 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 characterised by the use of electrical cells or batteries
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
A coupling system is described that allows users to avoid having to manipulate two tools at the same time while reaching around to both sides of the coupled components. A lock plate can rest above one or more holes passing through (and for joining together) the components. A blade pin with a partially hollow cylinder can be inserted through holes in the lock plate and at least partially through the holes. A blade bolt can be inserted into the holes and the cylinder from the other side. The blade bolt can comprise an o-ring that engages with an inner diameter of a portion of the cylinder and holds the parts together with an interference fit. A portion of the bolt can extend through the top of the holes, and a washer and nut can be attached to or about a threaded portion of the bolt. During each state of installation a user will not have to reach to both sides of the system while manipulating multiple tools.
F16B 39/10 - Locking of screws, bolts, or nuts in which the locking takes place after screwing down by a plate or ring immovable with regard to the bolt or object
F16B 39/04 - Locking of screws, bolts, or nuts in which the locking takes place after screwing down with a member penetrating the screw-threaded surface of at least one part, e.g. a pin, wedge, cotter-pin, screw
8.
Tailsitter with Pivoting Pole for Controlling External Loads
Load management system and methods are described for aircraft, including tailsitters. A load management system can comprise a pole coupled the fuselage and free to rotate and swing. The pole can comprise a cargo hook and a distal end that can be releasably coupled to a cargo cable or cargo. The pole can be coupled near its distal end to a retractable cable that is deployed from a position aft of the pole. During landing, takeoff, and when otherwise in hover mode, the retractable cable can be retracted—holding the pole along or near the fuselage. During transition to, or during, flight mode, the retractable cable can be deployed which can harmonize the cargo's center of gravity with the needs of the tailsitter aircraft.
In certain embodiments, a rotorcraft includes a first engine, a second engine, a primary engine-start system for the first engine, a fast-start engine-start system for the first engine, and a computer system. The computer system is configured to detect a failure of the second engine during a reduced engine operation (REO) flight mode in which the first engine has been intentionally shut down inflight and the second engine is to remain operational, and to automatically initiate, in response to detecting the failure of the second engine during the REO flight mode, an automatic restart of the first engine using the fast-start engine-start system.
Various implementations described herein are related to an aircraft having a multi-engine configuration with multiple engines. The aircraft may have a flight control system coupled to the multiple engines with a multi-engine interface. The flight control system may be configured to reduce fuel consumption of at least one engine of the multiple engines during reduced-engine operation by pulse modulating fuel delivery to the at least one engine of the multiple engines.
A multi-mode aircraft power-split-transmission system includes a rotational power input and a power-split transmission. The power-split transmission includes a sun gear, a planetary carrier, a ring gear, a first rotational power output, and a second rotational power output. The multi-mode aircraft power-split-transmission system also includes a first resistance device coupled to the first rotational power output and fixed to an airframe of the multi-mode aircraft and a second resistance device coupled to the second rotational power output and fixed to the airframe. Operation of the first resistance device causes power received from the rotational power input to be directed to the second rotational power output.
An electro-hydraulic flow control system for controlling the movement of a cutting implement of a turf mower. The flow control system comprises a hydraulic system for raising and lowering the cutting implement. The hydraulic system comprises a hydraulic fluid, a hydraulic actuator, and a hydraulic pump. The control system additionally comprises an electromechanical fluid flow control system for controlling a flow of the hydraulic fluid through the hydraulic system. The electromechanical fluid control system comprises a routing valve, a float valve, a weight transfer valve, a weight transfer pressure adjustment (WTPA) valve, and a control module for control operation of the routing valve, the float valve, the weight transfer valve, and the WTPA valve to control operation of the actuator and thereby control movement of the cutting implement.
A01B 63/10 - Lifting or adjusting devices or arrangements for agricultural machines or implements for implements mounted on tractors operated by hydraulic or pneumatic means
An aircraft weight and balance system includes a user interface that displays an interior layout of an aircraft with seat icons and cargo icons corresponding to seats and cargo zones onboard the aircraft. The seat and cargo icons are moveable to different locations within the interior layout, and an updated weight and center-of-gravity of the aircraft is automatically determined based on the different locations of the seat and cargo icons. An aircraft weight and balance method includes displaying an interior layout of an aircraft on a user interface including seat icons corresponding to seats onboard the aircraft, moving one or more of the seat icons to a different location within the interior layout based on a user input, determining an updated weight and center-of-gravity of the aircraft based on a current location of the seat icons, and displaying the updated weight and center-of-gravity of the aircraft on the user interface.
G01G 23/37 - Indicating the weight by electrical means, e.g. using photoelectric cells involving digital counting
G01G 19/07 - Weighing apparatus or methods adapted for special purposes not provided for in groups for weighing wheeled or rolling bodies, e.g. vehicles for weighing aircraft
G01M 1/12 - Static balancing; Determining position of centre of gravity
A window roller shade and dimming pane assembly includes a rigid frame having a first side member on a first side and a second side member on a second side opposite the first side. An outer pane and an inner pane are disposed within the rigid frame with a gap between the outer pane and the inner pane. A roller shade includes a motor for rolling and unrolling the roller shade. A first constant force spring and a second constant force spring are each configured to pull the roller shade downwardly through the gap while the motor is unrolling the roller shade. A dimming film is disposed on the inner pane for dimming light through the inner pane. A window interface is operatively coupled to the inner pane for receiving touch input for controlling the dimming film and the roller shade.
A vehicle includes a first rotor system having a rotor blade having an axis of rotation, a rotatable inboard drive component, and a rotatable outboard drive component. The first rotor system further includes a flexible closed loop component associated with each of the inboard drive component and the outboard drive component. Movement of the closed loop component can selectively cause at least one of rotation of the rotor blade about the axis of rotation and movement of the axis of rotation.
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
B64D 31/14 - Transmitting means between initiating means and power plants
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
Techniques are directed to operating a utility vehicle having global positioning system (GPS) circuitry and a geofencing data repository. Such techniques involve receiving, from the GPS circuitry, GPS output that indicates geolocation. The techniques further involve updating geofencing data within the geofencing data repository based on the GPS output that indicates geolocation. The techniques further involve, after updating the geofencing data, providing control to the utility vehicle based on the geofencing data within the geofencing data repository.
A tailsitter aircraft for deploying a tow line includes an airframe having wings with pylons extending therebetween and a thrust array attached to the airframe, the thrust array including propulsion assemblies configured to transition the airframe between a forward flight orientation and a VTOL orientation. The tailsitter aircraft includes an attenuation spool coupled to the airframe and an attenuation cable having a first end coupled to the attenuation spool and a second end coupled to the tow line, the attenuation cable partially or fully wound around the attenuation spool. The tailsitter aircraft also includes a spool sensor to detect movement of the attenuation spool and a flight control system implementing a tow line tension monitoring module in communication with the spool sensor to determine a tow line tension parameter and a tow line tension reaction module to initiate an aircraft response based on the tow line tension parameter.
An aircraft comprises a fuselage, first and second wing segments each having a leading edge and a trailing edge, a plurality of spokes coupling the fuselage to the first and second wing segments, one or more motors disposed within or attached to the plurality of spokes, and three or more propellers proximate to a leading edge of the plurality of spokes, distributed along the plurality of spokes, and operably connected to the motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight. When the aircraft is in vertical takeoff and landing and stationary flight, the fuselage is approximately vertical. When the aircraft is in forward flight, the fuselage is approximately in the direction of the forward flight and extends forward beyond the leading edges of the first wing segment and the second wing segment.
B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
B64D 31/00 - Power plant control; Arrangement thereof
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
One embodiment is an apparatus for inhibiting accidental contact by a human with a tail rotor connected to an empennage of an aircraft. The apparatus includes an inverted V-tail connected to an empennage of the aircraft forward of the tail rotor, the inverted V-tail stabilizer comprising a first V-tail stabilizer on a side of the empennage to which the tail rotor is connected and a second V-tail stabilizer on a side of the empennage opposite the side of the empennage to which the tail rotor is connected; and a shroud bar having a first end connected to an outboard end of the first V-tail stabilizer and a second end opposite the first end connected to the empennage aft of the tail rotor, wherein a horizontal distance from the shroud bar to the tail rotor is greater than a length of an arm of the human.
B64C 27/82 - Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft
B64C 27/20 - Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
Breathing systems and methods for a gearbox is described. Embodiments preferably create a closed system for air within the gearbox. As an operating gearbox warms the air or fluid within, or an altitude change causes air to expand or contract, increased pressure can result and air can escape through tubing to a cannister. The cannister can receive the expanding air in an impermeable cavity that is proximate to a bladder open or partially open to an exterior environment. Air can press on the bladder, expanding the cavity and shrinking the bladder until a pressure equilibrium is reached. As operation of the gearbox is lowered or powered off, or another altitude change occurs, the air can cool and/or retract into the gearbox. The bladder can then expand and press on the cavity until equalizing the pressure within the cannister.
One embodiment is a rotorcraft comprising a fuselage; an empennage at an aft end of the fuselage; a tail rotor connected to the empennage; and a tail rotor guard (TRG) around the tail rotor, the TRG shrouding to the tail rotor; and a light emitting diode (LED) lighting element integrated into at least one surface of the TRG.
A system and method for defeating a door lock. More specifically, a door having an outside door handle with a key-lock, and having an interior door handle of the type that includes both a paddle along with the handle runs the risk of being left in locked mode in the event of a mechanical malfunction. This problem has been overcome by mechanically linking the paddle on the interior handle to unlatch the key-lock.
E05B 77/30 - Functions related to actuation of locks from the passenger compartment of the vehicle allowing opening by means of an inner door handle, even if the door is locked
An aircraft door system and related closure method. The system involves the use of a ball transfer device as an initial contact made in the closing of an aircraft door. The closing door next encounters guiding and fitting arrangements are also employed to laterally align the lower portion of the aircraft door with the corresponding portion of the frame upon the closing. Finally, the closing door then encounters load path ties which are employed about the door. The arrangement above allows the door refit the door within what is a deformed doorframe due to weight and structural considerations.
A door sill protector includes a base rotatably mounted to a door sill via a hinge. The hinge allows the base to be rotated between a stowed position and a deployed position. A plurality of support feet are disposed on an underside of the base. Each of the support feet is pivotable for pivoting between an extended orientation and a retracted orientation. A linkage bar is mechanically coupled to the support feet such that the support feet collectively pivot in unison between the extended orientation and the retracted orientation.
A doorway side guide system includes a base mechanically coupled with a bottom portion of a doorway. A mounting member is rotatably coupled to the base via a hinge for rotating between a deployed position and a stowed position. A contact member is mechanically coupled with the mounting member via a pivot such that the contact member is configured to rotate about the pivot. The contact member extends outside of the doorway in the deployed position for guiding cargo through the doorway and for protecting a doorframe of the doorway.
A system and method for unlatching an aircraft door is disclosed. The system includes a latch pin design which enables retraction of the pin in the event the ordinary unlatching mechanical systems fail. The system includes the use of a rod that is reversely threaded on each side. Rotation of the rod either extends or retracts the pin.
A safety system for aircraft passenger seats is described. A pallet that can be removably coupled to seats can also be removably coupled to the aircraft floor and one or more brackets, tension fittings, or machined straps that can be coupled to structural beams or components in an aircraft. A keel tension fitting can be attached to a keel beam and then be coupled to the pallet and thereby the seats. By attaching to the keel beam the safety system allows the seating arrangement (pallet and seats) to withstand greater stresses and forces, resulting in increased safety.
An aircraft includes a frame, a transmission, and a liquid inertia vibration elimination (“LIVE”) system coupled between the frame and the transmission. The LIVE system is configured to attenuate communication of vibrations from the transmission to the frame. The LIVE system includes a first liquid zone, a second liquid zone, a plug at least partially segregating the first liquid zone from the second liquid zone, and the plug has an aperture in fluid communication with the first liquid zone and the second liquid zone. A splash guard is disposed within the second liquid zone and offset from the plug.
A rotor system for an aircraft includes an open rotor assembly comprising a plurality of rotor blades connected to a rotor mast via a yoke, wherein the rotor assembly is tiltable between a first position corresponding to an airplane mode and a second position corresponding to a helicopter mode; and a drive system for providing rotational energy to the open rotor assembly via the rotor mast, the drive system comprising at least one electric motor for providing rotational energy to a drive shaft and a gearbox connected to the drive shaft for receiving rotational energy from the at least one electric motor via the drive shaft and providing rotational energy to the rotor mast via a rotor shaft; wherein the drive system is rotatable relative to the wing about a tilt axis and the rotor shaft is coaxial with the drive shaft.
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
B64D 29/02 - Power-plant nacelles, fairings, or cowlings associated with wings
B64D 35/02 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the type of power plant
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
H02K 7/108 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with friction clutches
H02K 7/116 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with gears
30.
STOWABLE VEHICLE DOOR SECURING SYSTEM AND APPARATUS
Disclosed is an apparatus for maintaining a position of a vehicle door relative to a vehicle frame may include a link and a fastener. The link may have a first end and a second end. The first end may have a loop and the first end may be at an opposite end of the link from the second end. The fastener may be on a surface of the link and may be configured to fasten the link to the vehicle frame. A hook may be on the second end. The loop may be an arc or an incomplete circular portion. The vehicle may be a rotorcraft vehicle.
A modular airfoil-shaped battery disposed in a wing of an aircraft is presented. In one embodiment, the present disclosure provides for a system configured to have batteries or battery modules stored and accessible through access openings in the forward wing spar. The access openings in the forward spar can provide access for battery insertion and removal, as well as electrical and thermal management connections. Such forward spar access openings can be a relatively small, as the access opening need to only be as large as the battery cross section. A battery can comprise one or more battery modules based on the application requirements. The aircraft battery can be distributed among more, smaller battery modules. The battery modules can be placed in different locations in the wing. For example, the battery modules can be placed proximate an aircraft fuselage to achieve a better center of gravity.
H01M 50/249 - Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders specially adapted for aircraft or vehicles, e.g. cars or trains
H01M 50/271 - Lids or covers for the racks or secondary casings
H01M 50/233 - Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders characterised by physical properties of casings or racks, e.g. dimensions
B60L 53/80 - Exchanging energy storage elements, e.g. removable batteries
B60L 50/64 - Constructional details of batteries specially adapted for electric vehicles
A fluid pump system for an aircraft has a rotatable component having first and second fluid ports, each port in fluid communication with a selected interior portion of the component, the portions being spaced from each other. A valve controls allows a first flow rate through the first fluid port and allows a second flow rate through the second fluid port when the component is in a first angular orientation. The valve allows a third flow rate through the first fluid port and allows a fourth flow rate through the second fluid port when the component is in a second angular orientation.
F16H 57/04 - Features relating to lubrication or cooling
B64D 35/00 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
F01M 11/06 - Means for keeping lubricant level constant or for accommodating movement or position of machines or engines
F16K 11/076 - Multiple-way valves, e.g. mixing valves; Pipe fittings incorporating such valves; Arrangement of valves and flow lines specially adapted for mixing fluid with all movable sealing faces moving as one unit comprising only sliding valves with pivoted closure members with sealing faces shaped as surfaces of solids of revolution
F01M 11/04 - Filling or draining lubricant of or from machines or engines
In an embodiment, a rotorcraft includes a control element; a first detent sensor connected to the control element, the first detent sensor being operable to generate detent slip rate data indicating movement of the control element and detent state data indicating pilot control of the control element; a first trim motor connected to the control element and operable to generate trim rate data; and an FCC in signal communication with the first detent sensor and the first trim motor, the FCC including an error monitor operable to compare the detent slip rate data with the trim rate data and determine whether the first detent sensor is functional or defective, operable to provide a first flight management function when the first detent sensor is determined to be functional, and operable to provide a second flight management function when the first detent sensor is determined to be defective.
A handle assembly for an escape hatch. A handle assembly for an escape hatch comprises an interior handle and an exterior handle. The interior handle has an interior cam associated therewith and the exterior handle has an exterior cam associated therewith. The interior cam and the exterior cam each have a concave profile surface and a curved profile surface. A middle cam is sandwiched between the interior cam and the exterior cam and has a notched profile. The interior and exterior cams are associated with a tumbler having a flag. The middle cam is associated with an output rod operatively coupled to a second flag. Each of the interior handle and the exterior handle can be successively rotated in a first arc of rotation and a second arc of rotation with one hand. The first and second arcs of rotation are respectively associated with the flag and the second flag.
An escape hatch stay system for an aircraft and methods of using the escape hatch stay system. An escape hatch stay system includes a first stop arm, a second stop arm, and a gas strut. The first stop arm is rotatably coupled to the second stop arm, and the second stop arm is pivotably coupled to the gas strut. The first and second stop arms are lockable to preclude relative movement therebetween to lock the escape hatch in an open position. When the escape hatch is in the open position, the escape hatch may not be closed shut without manual intervention. When the escape hatch is in the open position, a load applicable to push the escape hatch open past the open position is damped by the gas strut.
E05C 17/32 - Devices for holding wings open; Devices for limiting opening of wings or for holding wings open by a movable member extending between frame and wing; Braking devices, stops or buffers, combined therewith by mechanical means with a movable bar or equivalent member extending between frame and wing consisting of two or more pivoted rods
E05F 1/10 - Closers or openers for wings, not otherwise provided for in this subclass spring-actuated for swinging wings
In certain embodiments, a method includes forming a battery electrode on a substrate. Forming the battery electrode on the substrate includes depositing a first electrode active material layer on a first portion of a surface of the substrate and depositing, to form a current collector, a conductive material using a thin film deposition process on a surface of the first electrode active material layer. The conductive material is deposited over an edge of the first electrode active material layer and onto a second portion of the surface of the substrate, the second portion of the substrate being adjacent to the first portion of the substrate. The method includes removing the battery electrode from the substrate, the battery electrode including the first electrode active material layer and the current collector.
A compact battery module incorporating a dual-sided printed circuit board (PCB) bus is presented. The present disclosure provides for an increase in battery cells per given volume by utilizing both sides of a PCB bus. In one embodiment, a PCB bus can be configured to receive battery cell terminals on both sides of the PCB via one or more connectors, thereby providing for a more compact battery module that is simpler and eliminates interconnections. By having a single PCB disposed between battery cells having both the positive negative terminals on one side, a more compact design can be realized with fewer printed circuit boards and lower weight.
H01M 50/284 - Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders with incorporated circuit boards, e.g. printed circuit boards [PCB]
H01M 10/42 - Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
40.
SYSTEM, APPARATUS, AND METHOD OF MANUFACTURE FOR A RIB STRUCTURE
One embodiment includes a rib structure to be used, for example, in any number of aerospace applications, the rib structure, comprising a first piece having a first curvature in a first plane; and a second piece having a second curvature in a second plane that is different from the first plane. The first piece and the second piece are bonded together to form the rib structure. In certain embodiments, the first piece further comprises a plurality of discontinuous flanges to interface with a plurality of skin surfaces. In other examples, the first piece includes an aft spar interface for bonding to a surface. In some implementations, the first piece includes a forward spar interface for bonding to a surface. Manufacturing of the airframe/aircraft parts, panels, and rib components can include any suitable composites, alloys, titanium, aluminum, artificial materials, sheet metal, etc.
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
B32B 3/28 - 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 comprising a deformed thin sheet, e.g. corrugated, crumpled
B32B 7/05 - Interconnection of layers the layers not being connected over the whole surface, e.g. discontinuous connection or patterned connection
B32B 15/01 - Layered products essentially comprising metal all layers being exclusively metallic
B21D 53/92 - Making other particular articles other parts for aircraft
B21D 13/10 - Corrugating sheet metal, rods or profiles, or bending sheet metal, rods or profiles into wave form into a peculiar profiling shape
In an embodiment, an aircraft includes a drive system, a main engine coupled to the drive system to provide first power, and a supplemental engine coupled to the drive system to provide second power additive to the first power. The aircraft also includes a control system to control the main engine and the supplemental engine to optimize usage of the supplemental engine. The control system is operable to maintain the supplemental engine in a reduced power state at least until a determination is made that supplemental power is needed to satisfy a total power demand of the drive system. The control system is also operable to determine that supplemental power is needed to satisfy the total power demand of the drive system. The control system is further operable to increase a power level of the supplemental engine in response to the determination that supplemental power is needed.
In an embodiment, a method includes: collecting usage and maintenance data for a rotorcraft at a computer of the rotorcraft; sending the usage and maintenance data to a fleet management server; generating individualized equipment data for the rotorcraft according to the usage and maintenance data at the fleet management server, the individualized equipment data including a lightweight digital representation of the rotorcraft and technical publications for the rotorcraft, the lightweight digital representation including mesh-based 3D visualizations of each component of the rotorcraft, the technical publications having views referencing the mesh-based 3D visualizations; sending the individualized equipment data to the computer of the rotorcraft; and persisting the individualized equipment data at the computer of the rotorcraft.
A pneumo-mechanical landing gear deployment system includes a dual-stage handle operatively connected to a pressurized tank, a nose landing gear pneumatically connected to the pressurized tank, and a main landing gear pneumatically connected to the pressurized tank. Actuation of the dual-stage handle to a first position opens the pressurized tank thereby deploying the nose landing gear. Actuation of the dual-stage handle to a second position causes further opening of the pressurized tank thereby deploying the main landing gear. The system may be employed as a backup landing gear deployment system in the case of a primary landing gear system failure.
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.
In an embodiment, a battery connector includes: power terminals configured to be coupled to a load having an input capacitance; power pins electrically coupled to the power terminals; a charge pin, the charge pin being longer than each of the power pins; and an antispark circuit electrically interposed between the charge pin and the power terminals, the antispark circuit including: a dissipation circuit configured to charge the input capacitance of the load in response to a battery being coupled to the charge pin; and a delay circuit configured to delay charging of the input capacitance of the load for a predetermined duration after the battery is coupled to the charge pin.
G01K 7/22 - Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat using resistive elements the element being a non-linear resistance, e.g. thermistor
G05D 1/08 - Control of attitude, i.e. control of roll, pitch, or yaw
H01R 43/20 - Apparatus or processes specially adapted for manufacturing, assembling, maintaining, or repairing of line connectors or current collectors or for joining electric conductors for assembling or disassembling contact members with insulating base, case or sleeve
47.
Persistent lubrication systems for aircraft gearboxes
A drive system for an aircraft such as a tiltrotor aircraft. The drive system includes first and second gearbox assemblies in mechanical communication with each other. A first lubrication system is associated with the first gearbox assembly and includes a bifurcated tank configured to contain a lubricant in an operating chamber including a lower sump and in an emergency chamber including an upper sump. A second lubrication system is associated with the second gearbox assembly. An emergency pump is in fluid communication with the emergency chamber. The emergency pump is configured to supply the lubricant to the first gearbox assembly from the emergency chamber responsive to a failure in the first lubrication system. In addition, the emergency pump is configured to supply the lubricant to the second gearbox assembly and to the operating chamber from the emergency chamber responsive to a failure in the second lubrication system.
A latch positioning mechanism for an aircraft door includes one or more locking members configured to be partially driven into a frame around the door via rotation of a pivot pin. A frame bumper extends outside of the door in a pre-catch position for contacting the frame. A catch bellcrank is operatively coupled to the frame bumper, and a biasing member biases rotation of the catch bellcrank to bias the frame bumper into the pre-catch position. The catch bellcrank is configured to contact a catch cam when the catch bellcrank is biased into the pre-catch position such that the catch cam prevents release of the one or more locking members for locking the door. Upon the frame bumper contacting the frame when the door is closed, the catch cam is released enabling the one or more locking members to be moved into a locked position.
The present invention achieves technical advantages as an aircraft having an augmented reality flight control system integrated with and operable from the pilot seat and an associated pilot headgear unit, wherein the flight control system is supplemented by flight-assisting artificial intelligence and geo-location systems. The present invention includes an augmented reality flight control system incorporating real-world objects with virtual elements to provide relevant data to a pilot during aircraft flight. A translucent substrate is disposed in the pilot's field of view such that the pilot can see therethrough, and observe virtual elements displayed on the substrate. The system includes a headgear that is worn by the pilot. A flight assistance module is configured to receive data related to the aircraft and provide predictive assistance to the pilot during flight based on the received data based in part on a pilot profile having preferences related to the pilot.
B64D 43/00 - Arrangements or adaptations of instruments
A42B 3/30 - Mounting radio sets or communication systems
G06F 3/01 - Input arrangements or combined input and output arrangements for interaction between user and computer
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
A tandem split divergent winglet for an aircraft includes a forward sail extending from an outboard end of a wing of the aircraft having a cant angle in a first direction, and an aft sail extending partially from the forward sail and partially from the outboard end of the wing. The aft sail has a cant angle in a second direction opposite the first direction. For aircraft having a low wing, the forward sail includes an upwards cant angle and the aft sail includes a downwards cant angle. For aircraft having a high wing, the forward sail includes a downwards cant angle, and the aft sail includes an upwards cant angle. Light emitted from an integrated light formed within the aft sail is blocked from reaching a cockpit window of the aircraft by the forward sail.
A flag mechanism for an aircraft door includes a first arm and a second arm each having a flag on a first end and a catch on a second end. A first cam is operatively coupled to a first latching member and a second cam is operatively coupled a second latching member. The first and second latching members are each configured for latching the aircraft door, which are locked when the first and second cams are rotated to a locked position. A first stud extends from a side of the first cam and a second stud extends from a side of the second cam. The first and second studs are each configured to be received by a respective catch of the first and second arms while the first and second cams are rotated, thereby moving each respective flag from a first position to a second position for simultaneous visual inspection.
A lockout system for an aircraft having a rotor assembly. The lockout system includes a drive shaft coupled to and rotatable with the rotor assembly, a nonrotating airframe structure disposed proximate the drive shaft and a lock assembly having first and second lock members. The first lock member is rotatable with the drive shaft and includes a plurality of bearing assemblies. The second lock member is coupled to the nonrotating airframe structure and includes a cradle having a plurality of asymmetric slots each with a leading ramp and a trailing stop. The lock assembly has a disengaged position in which rotation of the drive shaft is allowed and an engaged position in which each of the bearing assemblies is seated within one of the asymmetric slots to prevent rotation of the drive shaft. The lock assembly is actuatable between the engaged and disengaged positions.
A load sensor includes a compressible body positionable between two surfaces. The compressible body has a plurality of aligned layers including first and second outer shims with a middle shim positioned therebetween and with a resilient material interposed between each adjacent shim. The second outer shim has a gap that exposes an unsupported area of the middle shim. A strain gauge is coupled to the middle shim in the unsupported area. When the compressible body is uncompressed, the resilient material interposed between the first outer shim and the middle shim has a substantially uniform thickness. When the compressible body is compressed between the two surfaces, the resilient material aligned with the unsupported area and interposed between the first outer shim and the middle shim has a nonuniform thickness such that the middle shim deflects away from the first outer shim in the unsupported area, thereby deforming the strain gauge.
G01L 1/22 - Measuring force or stress, in general by making use of electrokinetic cells, i.e. liquid-containing cells wherein an electrical potential is produced or varied upon the application of stress using resistance strain gauges
A transition duct assembly includes a shared connector, and a plurality of primary cooling pathways for cooling one or more systems or components. Each primary cooling pathway includes a transition duct in fluid communication with the shared connector, and a transition connector in fluid communication with the transition duct.
One embodiment is an aircraft comprising a rechargeable main battery for providing power to a system load of the aircraft; power source for providing at least one of a voltage and a current for recharging the rechargeable main battery; and a controller module connected to the rechargeable main battery, the controller module configured to control a process of recharging the rechargeable main battery using the at least one of the voltage and the current according to a battery type of the rechargeable main battery without removing the rechargeable main battery from the aircraft.
B60L 53/62 - Monitoring or controlling charging stations in response to charging parameters, e.g. current, voltage or electrical charge
H02J 7/00 - Circuit arrangements for charging or depolarising batteries or for supplying loads from 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]
B60L 58/16 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries responding to battery ageing, e.g. to the number of charging cycles or the state of health [SoH]
B60L 58/24 - Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries for controlling the temperature of batteries
B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
H01M 10/0525 - Rocking-chair batteries, i.e. batteries with lithium insertion or intercalation in both electrodes; Lithium-ion batteries
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 10/42 - Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
56.
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 vertical takeoff and landing and stationary flight, and substantially in a direction of a forward flight in a forward flight mode.
B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
B64D 31/00 - Power plant control; Arrangement thereof
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
An electric temperature control system for unpressurized aircraft and methods for operating are disclosed. The electric temperature control system may be electrically powered and used on all-electric aircraft or hybrid aircraft. The electric temperature control system may comprise a vapor cycle cooling system for cooling air and an electric heater for heating air. The electric heater may be a PTC electric heater with individually-controllable heating elements. Various input devices may be disposed in the aircraft allowing an operator to set a compartment temperature, an air source, and a fan speed. A controller controls operations of the electric temperature control system based on feedback received from a plurality of feedback devices and the operator inputs.
B64D 13/08 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being conditioned the air being heated or cooled
A mower includes a frame, at least one cutting unit, and a lifting unit. The lifting unit is connected to the at least one cutting unit and includes a yoke assembly, a first arm assembly, a second arm assembly, and a third arm assembly. The yoke assembly is connected to the cutting unit. The first arm assembly is pivotably mounted to the vehicle frame about a first pivot axis. The second arm assembly is pivotably mounted to the first arm assembly about a second pivot axis and to the yoke assembly about a third pivot axis with the second pivot axis and third pivot axis being non-parallel to the first pivot axis. The third arm assembly includes a first end pivotally connected to the frame and a second end pivotally connected to the second arm assembly.
A01D 34/66 - Mowers; Mowing apparatus of harvesters characterised by features relating to the type of cutting apparatus having rotating cutters having cutters rotating about a vertical axis mounted on a vehicle, e.g. a tractor, or drawn by an animal or a vehicle with two or more cutters
An oil level measurement system for an aircraft engine includes a magnetic float disposed in the aircraft engine, a first sensor ladder configured for sensing a position of the magnetic float, and a second sensor ladder configured for sensing a position of the magnetic float. A controller is configured to determine an oil level of an engine based on an engine status signal, a first signal from the first sensor ladder, and a second signal from the second sensor ladder. An oil level sensing method for measuring an oil level within an aircraft engine when the aircraft engine is off includes comparing a first signal from a first sensor ladder with a second signal from a second sensor ladder, indicating a fault when the first signal is different from the second signal, and determining an oil level of an aircraft engine when the first signal matches the second signal.
G01F 23/72 - Indicating or measuring liquid level or level of fluent solid material, e.g. indicating in terms of volume or indicating by means of an alarm by floats of the free float type using magnetically actuated indicating means
H01H 36/02 - Switches actuated by change of magnetic field or of electric field, e.g. by change of relative position of magnet and switch, by shielding actuated by movement of a float carrying a magnet
A fluid level sensing system includes a mounting strip and fluid sensing nodes coupled to the mounting strip. Each fluid sensing node is switchable between a fluid present state and a fluid absent state. Each fluid sensing node includes a prism, a photoemitter and a photoreceptor. The photoemitter and photoreceptor are interposed between the prism and the mounting strip. In the absence of fluid around the prism, the photoreceptor receives greater than a threshold amount of light from the photoemitter internally reflected by the prism to switch the fluid sensing node to the fluid absent state. When the prism is covered in fluid, the photoreceptor receives less than the threshold amount of light from the photoemitter to switch the fluid sensing node to the fluid present state. A processor determines a fluid level based on the fluid detection states of the fluid sensing nodes.
A method of assembling an aircraft gearbox. The method includes mounting an outer race and a plurality of rollers of a roller bearing in an opening of a gearbox housing, mating a cylindrical guide sleeve having a lead-in chamfer with a gear assembly having a gear and a cylindrical shaft such that a trailing shoulder of the guide sleeve is positioned proximate a leading shoulder of the shaft, the shaft including an inner race of the roller bearing, axially passing the lead-in chamfer of the guide sleeve through the plurality of rollers, radially outwardly urging the rollers toward the outer race with the guide sleeve, axially passing the leading shoulder of the shaft through the plurality of rollers, positioning the inner race relative to the plurality of rollers to form the roller bearing and removing the guide sleeve from the gear assembly.
A technique provides a field service tool (FST) that allows customers to view and store engine performance data, including faults, in a convenient manner. The technique allows customers to gain insights into performance anomalies while preventing customers from changing engine parameters except for a limited set of parameters selected to avoid the need for service visits while having no effect on safety or compliance.
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
63.
HYBRID PROPULSION DRIVE TRAIN SYSTEM FOR TILTROTOR AIRCRAFT
The present invention includes a hybrid propulsion system for an aircraft comprising: an engine disposed within a fuselage of the aircraft, two electrical generators disposed within the fuselage and connected to the engine, and two nacelles. Each nacelle comprises a proprotor, and each nacelle houses two electric motors connected to the proprotor. Each electrical generator is connected to the two electric motors in each nacelle. The proprotors provide lift for vertical takeoff and landing in a helicopter mode. A fan is coupled to the fuselage and connected to two additional electric motors. Each additional electric motor is connected to one of the two electric generators. The fan provides thrust for forward flight during an airplane mode. The airplane mode includes increasing power to the fan while decreasing power to the proprotors to zero.
A vehicle transaxle comprising a plurality of mounting flanges fixedly mountable to an axle tube of the vehicle absent any additional structure for mounting the transaxle to the vehicle. The axle tube houses a wheel axle to which the transaxle is operably couplable. The transaxle additionally comprises a transaxle mounting collar that is fixedly mounted to or integrally formed with a housing of the transaxle. The mounting collar is structured and operable to have a prime mover of the vehicle mounted thereto and to support the weight/mass of the prime mover such that the prime mover is mountable to the vehicle via only the mounting collar absent any additional structure for mounting the prime mover to the vehicle such that the prime mover can be cantilevered from (e.g., suspended from) the transaxle, e.g., the prime mover is ‘free floating’.
Tail rotor control system is described for helicopters. A pedal position sensor operable by a pilot yields greater tail rotor RPM relative to the main rotor RPM, giving the pilot increased control over the vehicle. This proves especially useful in certain situations, such as high altitude, where increasing tail rotor speed from main rotor speed can give a pilot increased maneuverability and stability.
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
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
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 plant using steam, electricity, or spring force
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
Various implementations described herein are directed to a device having a puller tool assembly for removing a wear sleeve from a tail-rotor hub assembly of a rotorcraft. The puller tool assembly may have an interior shaft slidably engaged within an exterior cylindrical body. The puller tool assembly may have a restraint cap coupled to the interior shaft at a first end of the exterior shaft with a fastener. The puller tool assembly may have a mandrel coupled to the interior shaft at a second end of the exterior shaft. The exterior cylindrical body may be inserted within the wear sleeve between the restraint cap and the mandrel. The mandrel may expand to grasp the wear sleeve when the exterior shaft is tightened so as to pull the wear sleeve toward the restraint cap.
B25B 27/06 - Hand tools or bench devices, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for connecting objects by press fit or detaching same inserting or withdrawing sleeves or bearing races
A method of verifying operation of an aircraft in a pre-defined flight mode includes operating the aircraft in a first flight mode, commanding the aircraft to transition to a second flight mode, evaluating a plurality of motor performance parameters, and based on values of the plurality of motor performance parameters, determining whether the aircraft has successfully transitioned to the second flight mode.
An aircraft includes a fuselage and a wing assembly that is rotatable between a substantially perpendicular orientation relative to the fuselage in flight modes and a substantially parallel orientation relative to the fuselage in a wing stowage mode. The wing assembly includes a wing that is pivotable between forward flight and VTOL orientations by a pivot angle. A distributed thrust array is coupled to the wing that includes outboard and inboard propulsion assemblies, each propulsion assembly having an axis of rotation that has a fixed angle relative to a chord axis of the wing. In a VTOL flight mode, the axis of rotation of each propulsion assembly is substantially vertical and the wing is in the VTOL orientation. In a forward flight mode, the wing is in the forward flight orientation and the axis of rotation of each propulsion assembly is tilted forward from the vertical by the pivot angle.
A method of operating a multi-engine drive system of an aircraft includes driving a main rotor of the aircraft by a main engine of the multi-engine drive system at an operating speed of the main engine, operating a supplemental engine of the multi-engine drive system at approximately 80% of an operating speed of the supplemental engine, wherein, during the operating step, a clutch interoperably coupled to the supplemental engine is interoperably decoupled from the main rotor and, responsive to a command to interoperably engage the clutch, if the clutch successfully engages such that the clutch is interoperably coupled to the main rotor, providing, by the supplemental engine, power to the main rotor.
B64D 31/12 - Initiating means actuated automatically for equalising or synchronising power plants
B64D 35/08 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission being driven by a plurality of power plants
71.
Devices and Methods to Verify Main Rotor Swashplate Positioning
A device to verify main rotor swashplate positioning includes an inner surface of a first section and a gradient surface of a second section. The gradient surface of the second section may have a plurality of graduation indications. In one implementation, the inner surface of the first section at least partially defines a travel arc that is parallel to and concentric with the inner surface. In such an implementation, the device may be configured to move along the travel arc as it rotates about a collective sleeve to contact a swashplate lug.
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 universal assembly platform for lightweight vehicles, wherein the platform comprises a main vehicle chassis structure, a front suspension system connected to the main vehicle chassis structure and to which one or more front wheel assembly is mountable, and a rear suspension system connected to the main vehicle chassis structure and to which one or more rear wheel assembly is mountable. The rear suspension system is connected to the main vehicle chassis structure such that when the one or more rear wheel assembly is mounted to the rear suspension system a rear wheel of the one or more rear wheel assembly defines the distal end of an overall length of the vehicle.
B62D 21/02 - Understructures, i.e. chassis frame on which a vehicle body may be mounted comprising longitudinally or transversely arranged frame members
A universal assembly platform for lightweight vehicles, wherein the platform comprises a main vehicle chassis structure, a front suspension system connected to the main vehicle chassis structure and to which one or more front wheel assembly is mountable, and a rear suspension system connected to the main vehicle chassis structure and to which one or more rear wheel assembly is mountable. The rear suspension system is connected to the main vehicle chassis structure such that when the one or more rear wheel assembly is mounted to the rear suspension system a rear wheel of the one or more rear wheel assembly defines the distal end of an overall length of the vehicle.
B62D 21/02 - Understructures, i.e. chassis frame on which a vehicle body may be mounted comprising longitudinally or transversely arranged frame members
An aircraft includes a fuselage, a pylon, a wing positioned between the fuselage and the pylon, and a plurality of drive shafts located inside the wing and adapted to drive a rotor associated with the pylon.
B64D 35/08 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission being driven by a plurality of power plants
B64D 27/02 - Aircraft characterised by the type or position of power plant
B64D 27/26 - Aircraft characterised by construction of power-plant mounting
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
A modular battery system includes an array of battery modules arranged in at least one stack. Each battery module includes a plurality of battery cells, a first side having positive and negative receptacles and a second side, that is opposite of the first side, having positive and negative plugs. The receptacles and plugs are configured such that adjacent battery modules in a side-by-side relationship are electrically coupled together via plug and receptacle connections and such that the battery modules are electrically coupled together in parallel. An interconnection electrically couples each stack of battery modules together via plug and receptacle connections with one of the battery modules in each stack such that the stacks of battery modules are electrically coupled together in parallel. Each of the battery modules includes a thermal conditioning system configured to thermally isolate the battery module from the other battery modules.
B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
B60L 50/64 - Constructional details of batteries specially adapted for electric vehicles
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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
H01M 10/42 - Methods or arrangements for servicing or maintenance of secondary cells or secondary half-cells
H01M 50/249 - Mountings; Secondary casings or frames; Racks, modules or packs; Suspension devices; Shock absorbers; Transport or carrying devices; Holders specially adapted for aircraft or vehicles, e.g. cars or trains
H01M 50/209 - Racks, modules or packs for multiple batteries or multiple cells characterised by their shape adapted for prismatic or rectangular cells
A fixture configured to secure a component in a vehicle includes a panel separating an internal cabin from an external compartment. The panel has a first side facing the internal cabin and a second side facing the external compartment. A hole is disposed within the panel. The component is configured for mounting to the panel via the hole. The component includes a flange configured for abutting the first side of the panel and a coupling feature configured to extend through the hole into the external compartment. A fastener is configured to removably couple with the coupling feature and abut the second side of the panel for fastening the component to the panel.
An aircraft includes a fuselage and a wing system having first and second oppositely disposed wings that extend laterally from the fuselage. A tiltable propulsion system is rotatably coupled to the fuselage between the first and second wings. The tiltable propulsion system includes a frame system having four diagonally extending arms each having a propulsion assembly coupled thereto. A flight control system is configured to independently control each of the propulsion assemblies and the orientation of the tiltable propulsion system. In a VTOL flight mode of the aircraft, the tiltable propulsion system is substantially perpendicular to the aircraft's yaw axis in a vertical thrust orientation such that the propulsion assemblies are configured to provide vertical thrust. In a forward cruise flight mode of the aircraft, the tiltable propulsion system is substantially perpendicular to the aircraft's roll axis in a forward thrust orientation such that the propulsion assemblies provide forward thrust.
A method for automatically decoding aircraft Cockpit Voice Recorder (CVR) encoded data includes loading a definitions class and a decoder class into a memory via a driver class, loading configuration files into the memory via the definitions class, receiving from an aircraft CVR one or more hex files that include the CVR encoded data into the memory, generating via the decoder class and the configurations file one or more decoded objects based on the one or more hex files, respectively, and displaying the one or more decoded objects in a human readable format. A system to automatically decode aircraft CVR encoded data includes a user interface, a processor, and a memory having a computer program configured to generate one or more decoded objects based on one or more hex files of CVR encoded data, and to display the one or more decoded objects in a human readable format.
One embodiment is a navigation system for an aircraft including a positioning system to generate information related to a position of the aircraft, a group of cameras mounted to a body of the aircraft, each camera of the group of cameras to simultaneously capture images of a portion of an environment that surrounds the aircraft, and a processing component coupled to the positioning system and the group of cameras, the processing component to determine a current position of the aircraft based on the information related to the position of the aircraft and the images.
An electrochemical machining assembly for boring a passage in an electrically conductive workpiece. The electrochemical machining assembly includes an electrochemical machining tool having a telescoping collar with an articulating head coupled thereto. The telescoping collar is hydraulically actuatable between a contracted configuration and an extended configuration responsive to fluid pressure provided by an electrolyte fluid circulated by the electrochemical machining assembly to advance the telescoping collar stepwise in the passage. The articulating head is tiltable relative to the telescoping collar to determine a direction of the passage. The electrochemical machining assembly is configured to remove material from the workpiece upon application of a voltage between the articulating head and the workpiece via the electrolyte fluid to lengthen the passage.
An electrochemical machining assembly for boring a passage in an electrically conductive workpiece. The electrochemical machining assembly includes an electrochemical machining tool having a telescoping collar with an articulating head coupled thereto. The telescoping collar is actuated between a contracted configuration and an extended configuration to advance the telescoping collar stepwise in the passage. The articulating head is tiltable relative to the telescoping collar to determine a direction of the passage. The electrochemical machining assembly is configured to remove material from the workpiece upon application of a voltage between the articulating head and the workpiece via a circulating electrolyte fluid to lengthen the passage.
Disclosed is an electronics device holder made to be mountable on an aircraft control stick arrangement. The holder enables two dimensions of rotation. Rotation clockwise and counterclockwise is provided by a disk on which the holder is mounted. The disk edges are trapped underneath a containing plate. Friction enables the disk, and thus, the holder to be held in different circular positions. A friction hinge is used to establish and hold different pitch positions for the electronics device.
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
F16M 11/10 - Means for attachment of apparatus; Means allowing adjustment of the apparatus relatively to the stand allowing pivoting around a horizontal axis
F16M 11/20 - Undercarriages with or without wheels
83.
Anti-Roll Oscillation Landing Wheel Rims for Rotorcraft
A landing wheel assembly for a rotorcraft having a light on gear phase during takeoff and landing includes a tire and an anti-roll oscillation rim. The tire has first and second side walls and forms a center aperture. The anti-roll oscillation rim includes a center disc disposed in the aperture of the tire, a first side wall support plate protruding from the center disc and extending at least 25 percent of the vertical length of the first side wall of the tire and a second side wall support plate protruding from the center disc and extending at least 25 percent of the vertical length of the second side wall of the tire. The first and second side wall support plates support the first and second side walls, respectively, to stiffen the tire in the light on gear phase of takeoff and landing, thereby reducing roll oscillations of the rotorcraft.
A fuel-cell system for powering an electrical load, the system having first and second fuel cells, each having a positive node and a negative node. The positive node of the second fuel cell is electrically coupled to the negative node of the first fuel cell, and the positive node of the first fuel cell and the negative node of the second fuel cell are electrically coupled to the electrical load. Each fuel cell is electrically coupled to the electrical load without a power converter.
A method of producing an article of manufacture includes printing a break-wire conductive-material pattern via an additive-manufacturing process and applying the break-wire conductive-material pattern to a surface of a component. A shape of the break-wire conductive-material pattern fits the surface of the component.
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]
H01B 13/00 - Apparatus or processes specially adapted for manufacturing conductors or cables
B33Y 80/00 - Products made by additive manufacturing
An apparatus for introducing a test load to a rotor blade test specimen for fatigue testing includes a body extending along a longitudinal axis in a first direction from a first end to a second end, and the body having an internal cavity with an opening at the second end configured to dispose a tip portion of the rotor blade test specimen.
A golf car canopy extension panel that is connectable to a canopy main panel, wherein the extension panel comprises a first extension longitudinal water channel that is fluidly connectable to a first main longitudinal water channel main panel, and a second extension longitudinal water channel that is fluidly connectable to a second main longitudinal water channel of the main panel, wherein the first and second extension longitudinal water channels each comprise a termination end structured and operable to direct water to exit the respective extension longitudinal water channel at an end of a sidewall of the respective extension longitudinal water channel.
A telescoping tail assembly for use on an aircraft that has a fore-aft length. The telescoping tail assembly includes a housing extending in an aftward direction and a tailboom slidable along the housing into various positions including an extended position and a retracted position. A jackscrew is coupled to the tailboom. An actuator is coupled to the jackscrew and is configured to selectively rotate the jackscrew to translate the tailboom between the plurality of positions. The tailboom has one or more control surfaces coupled thereto. The tailboom increases the fore-aft length of the aircraft in the extended position and decreases the fore-aft length of the aircraft in the retracted position.
B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
B64C 39/04 - Aircraft not otherwise provided for having multiple fuselages or tail booms
A bearing raceway for a shaft includes a tubular sleeve comprising a raceway section and a clamp section, the raceway section having a hardened outer surface and a first, axially linear, inner surface, and the clamp section having first threads and a second, axially non-linear, inner surface, where the first threads are configured to mate with second threads on a nut to clamp the tubular sleeve to the shaft.
A system includes a chip detector that includes a magnet, the chip detector operable to collect a plurality of chips in a lubricant flow. The system also includes a radiation sensor associated with the magnet and operable to detect radiation emitted by at least some of the plurality of chips collected by the magnet.
A technique provides power-limiting regenerative braking to a utility vehicle. The technique involves detecting that the utility vehicle is moving in a forward direction at a first speed. The technique further involves applying a first regenerative braking power level to the utility vehicle in response to detecting that the utility vehicle is moving in the forward direction at the first speed. The technique further involves detecting that the utility vehicle is moving in the forward direction at a second speed which is less than the first speed. The technique further involves applying a second regenerative braking power level to the utility vehicle in response to detecting that the utility vehicle is moving in the forward direction at the second speed. The second regenerative braking power level is lower than the first regenerative braking power level.
An all-terrain vehicle is provided comprising a chassis, four wheels and a passenger compartment that includes a passenger seating structure. The vehicle additionally comprises a drivetrain operatively connected to at least one of the wheels comprising at least one drive shaft and at least one torque transfer device. Furthermore the vehicle includes a prime mover that is mounted to the chassis entirely forward of a front edge of the seating structure and operatively connected to the drivetrain. The prime mover is structured and operable to provide motive force to at least one of the wheels.
B60K 17/22 - Arrangement or mounting of transmissions in vehicles characterised by arrangement, location, or type of main drive shafting, e.g. cardan shaft
B60K 5/02 - Arrangement or mounting of internal-combustion or jet-propulsion units with the engine main axis, e.g. crankshaft axis, substantially in, or parallel to, the longitudinal centre line of the vehicle
B60K 17/344 - Arrangement or mounting of transmissions in vehicles for driving both front and rear wheels, e.g. four wheel drive vehicles having a transfer gear
B60K 17/348 - Arrangement or mounting of transmissions in vehicles for driving both front and rear wheels, e.g. four wheel drive vehicles having differential means for driving one set of wheels, e.g. the front, at one speed and the other set, e.g. the rear, at a different speeds
B60K 17/16 - Arrangement or mounting of transmissions in vehicles characterised by arrangement, location, or kind of gearing of differential gearing
A wing for an aircraft includes a first end, a second end, and a skin extending longitudinally from the first end to the second end. The wing also includes at least one channel positioned within the skin and extending longitudinally between the first and second ends. The at least one channel defines a longitudinal translation path for translating at least one electrical power source longitudinally between the first and second ends.
A compression-force spike reduction system for a strut includes a first chamber and a second chamber, an orifice plate disposed within the strut between the first chamber and the second chamber, a hydraulic fluid disposed within the first chamber and the second chamber, and a compressible portion disposed in the second chamber. The orifice plate includes at least one orifice configured for the hydraulic fluid to flow through. During compression or extension of the strut, hydraulic fluid is exchanged between the first chamber and the second chamber. The compressible portion contains a compressible medium configured to buffer spikes in compression force of the strut. A compression-force spike reduction method includes filling the second chamber partially with the incompressible hydraulic fluid, and filling a remaining portion of the second chamber with a compressible medium.
F16F 9/06 - Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium using both gas and liquid
95.
Rotor system with belt driven propulsion and stowing
A vehicle includes a first rotor system having a rotor blade having an axis of rotation, a rotatable inboard drive component, and a rotatable outboard drive component. The first rotor system further includes a flexible closed loop component associated with each of the inboard drive component and the outboard drive component. Movement of the closed loop component can selectively cause at least one of rotation of the rotor blade about the axis of rotation and movement of the axis of rotation.
B64C 39/02 - Aircraft not otherwise provided for characterised by special use
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
A stowable entry handle includes a handle having a first end and a second end opposite the first end, a shaft mechanically coupled with the handle, a protrusion extending from an end of the shaft opposite the handle, and a mounting structure for mechanically coupling to a side wall adjacent a doorway. The shaft includes a cylindrical member that extends perpendicularly from the first end. The mounting structure includes a tube configured to receive the shaft. The tube includes a first slot at a first position within the tube and a second slot at a second position within the tube. The protrusion is configured to insert into the first slot for stowing the handle inside the doorway and the second slot for deploying the handle outside the doorway.
A stairway for aircraft is disclosed which includes first and second stair halves, one which nests in the other. The first half is hinged to the doorway and the second half is hinged to the first half. A mechanical resistance system uses different devices to allow for the airstair to be damped when switching between modes. A retracting arrangement is also disclosed.
An aircraft stair system is provided with flexible bumpers configured to prevent abrupt impact of the first structure against the second. Each of the bumpers has a flexible body, a base portion, and a lever arm extending out over the base to create a gap and an open mouth.
A table is incorporated into an aircraft staircase design. The table can be deployed when the stairs are stowed inside the aircraft cabin area. The table is upwardly biased such that when it is released from a locking mechanism the table flips up to horizontal.
Opposing magnets are used to hold two hinged stairway portions together by including the magnets into opposing surfaces in an aircraft stairway arrangement. The relative position of one of the magnets relative to the other is used to establish a desired holding force.
patents
