A Bluetooth plus radio frequency identification (RFID) beacon for use vehicle fleet management and geofencing system, wherein the beacon comprises a housing, and a circuit board disposed within the housing. The circuit board comprises a Bluetooth communication circuitry portion containing a unique media access control (MAC) address, and an RFID circuitry portion integrated with the Bluetooth communication circuitry portion such that the RFID circuitry portion is associated with the Bluetooth circuitry MAC address whereby the Bluetooth beacon can be identified, via the MAC address, by an RFID reader communicating with the RFID circuitry portion using the MAC address of the Bluetooth communication circuitry portion.
H04W 4/48 - Services specially adapted for particular environments, situations or purposes for vehicles, e.g. vehicle-to-pedestrians [V2P] for in-vehicle communication
H04W 4/80 - Services using short range communication, e.g. near-field communication [NFC], radio-frequency identification [RFID] or low energy communication
2.
POWER MANAGEMENT SYSTEMS FOR ELECTRICALLY DISTRIBUTED YAW CONTROL SYSTEMS
An electrically distributed yaw control system for a helicopter haying a tailboom and a power system includes one or more tail rotors including a motor rotatably coupled to the tailboom and a power distribution unit. The power distribution unit includes a power management monitoring module configured to monitor one or more flight parameters of the helicopter and a power management command module configured to allocate power between the power system and the one or more tail rotor motors based on the one or more flight parameters of the helicopter.
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 19/00 - Aircraft control not otherwise provided for
A yaw control system for a helicopter having a tailboom and a forward flight mode includes a surface coupled to the tailboom, one or more tail rotors coupled to the surface, a flight control computer implementing a yaw controller having a rudder control module and a tail rotor rotational speed reduction module and a rudder rotatably coupled to the surface. The tail rotor rotational speed reduction module is configured to selectively switch the one or more tail rotors into a rotational speed reduction mode in the helicopter forward flight mode. The rudder control module is configured to rotate the rudder in the rotational speed reduction mode of the one or more tail rotors to control the yaw of the helicopter.
B64C 19/00 - Aircraft control not otherwise provided for
B64C 27/82 - Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft
4.
METHODS AND SYSTEMS FOR PERFORMING NON-DESTRUCTIVE TESTING (NDT)
Methods and systems for performing a validation process on a part to be process are provided. An identifier associated with the part is received. A listing of at least one automated process based on the identifier is displayed. An indication of a selected automated process from the listing is received. First instructions are transmitted to an automated process device for performing an automated processing program in accordance with the selected automated process. Processing results associated with the part are received from the automated process device. Second instructions are transmitted to a validation process device for performing a validation program in accordance with a validation process associated with the selected automated process. Validation results associated with the part are received from the validation process device. The processing results and the validation results are stored in association with the identifier.
G01N 37/00 - INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES - Details not covered by any other group of this subclass
G01G 19/00 - Weighing apparatus or methods adapted for special purposes not provided for in groups
G05B 15/02 - Systems controlled by a computer electric
A weighing system includes a support, a load cell mounted to the support, and a part platform suspended from the load cell to receive a part to be weighed. The load cell is operable to generate thousands of weight values for the part per second over a period of less than twenty seconds. The load cell is operable to output a weight of the part by averaging the weight values over the period of less than twenty seconds. A method of weighing the part suspended from the load cell is also disclosed.
A cart for supporting a part to be inspected in a non-destructive testing (NDT) machine. The cart includes a base with wheels, a first support extending upright from the base, a second support extending upright from the base, and mounting fixtures being removably attachable to the first and second supports and having mounting ends engageable with the part to support the part from the first support or the second support. The base is displaceable with the wheels to enter and exit the NDT machine. The cart is lockable upon being within the NDT machine to secure the cart in position.
An electric distributed propulsion system includes one or more generators connected to a gearbox, a first and a second plurality of motors connected to the generators, each motor connected to a blade to provide thrust, a first and a second power bus electrically connected between the generators and the first and the second motors, each power bus independent of the other power bus, a first and a second controller independently connected to each of the first and second motors, each of the first and second controllers serving as a primary and a backup controller to provide redundant control to both the first and the second plurality of motors, and dual channels in communication between pilot input sensors and the first and the second controllers, each channel independent of the other channels, and the channels including an additional channel to provide redundant communication to the first and second controllers.
B64C 27/82 - Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft
An anti-torque assembly for a helicopter includes a plurality of fans pivotably mountable to the tail boom. The fans have fan blades rotatable about a fan axis. One or more of the plurality of fans is pivotable relative to the tail boom to a first configuration. The fan axes of the fans in the first configuration have an upright orientation and are operable to one or both of pitch and roll the helicopter. Different fans of the plurality of fans are operable to generate thrust to provide anti-torque to the helicopter. The anti- torque assembly is thus capable of providing both anti-torque to the helicopter and changing its attitude.
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 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
An aircraft includes a wing and a rotor pod mounted to the wing. The rotor pod includes a body having a forward end and an aft end. A propeller is mounted to the body of the rotor pod at the forward end. A control surface is mounted to the body of the rotor pod between the forward and aft ends and extends outwardly from the body. The control surface is displaceable relative to the body between a first control configuration and a second control configuration to control an attitude of the aircraft. The control surface in the first control configuration is closer to the propeller than the control surface in the second control configuration.
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 9/00 - Adjustable control surfaces or members, e.g. rudders
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
10.
CONVERTIBLE BIPLANE AIRCRAFT FOR AUTONOMOUS CARGO DELIVERY
An autonomous cargo delivery aircraft operable to transition between thrust- borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes a fuselage having an aerodynamic shape with a leading edge, a trailing edge and first and second sides. First and second wings are coupled to the fuselage proximate the first and second sides, respectively. A distributed thrust array includes a first pair of propulsion assemblies coupled to the first wing and a second pair of propulsion assemblies coupled to the second wing. A flight control system is operably associated with the distributed thrust array and configured to independently control each of the propulsion assemblies. The first side of the fuselage includes a door configured to provide access to a cargo bay disposed within the fuselage from an exterior of the aircraft with a predetermined clearance relative to the first pair of propulsion assemblies.
B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64C 39/08 - Aircraft not otherwise provided for having multiple wings
A method of forming a composite member, includes: applying pressure and heat with a compaction tool to a portion of an uncured composite member to decrease a thickness of the portion, the heat applied with the compaction tool being at a temperature less than a curing temperature of the uncured composite member; and curing the uncured composite member after applying pressure and heat.
B29C 70/34 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression
12.
LOGISTICS SUPPORT AIRCRAFT HAVING A MINIMAL DRAG CONFIGURATION
An aircraft is operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes an airframe having first and second wings with first and second pylons extending therebetween forming a central region. A two-dimensional distributed thrust array and a flight control system are coupled to the airframe. A nose cone and an afterbody are each selectively coupled to the airframe. In a cargo delivery flight configuration, the nose cone and the afterbody are coupled to the airframe such that the nose cone and the afterbody each extend between the first and second wings and between first and second pylons to form a cargo enclosure with an aerodynamic outer shape. In a minimal drag flight configuration, the nose cone and the afterbody are not coupled to the airframe such that air passes through the central region during 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 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64D 1/02 - Dropping, ejecting, or releasing articles
13.
MULTIMODAL UNMANNED AERIAL SYSTEMS HAVING TILTABLE WINGS
A multimodal unmanned aerial system includes a fuselage forming a payload bay, a control wing forward of the fuselage including a first plurality of propulsion assemblies and a primary wing aft of the fuselage including a second plurality of propulsion assemblies. The primary wing has a greater wingspan than the control wing. The multimodal unmanned aerial system includes linkages rotatably coupling the fuselage to the control wing and the primary wing. The fuselage, the control wing and the primary wing are configured to synchronously rotate between a vertical takeoff and landing flight mode and a forward flight mode. The fuselage, the control wing and the primary wing are substantially vertical in the vertical takeoff and landing flight mode and substantially horizontal in the forward flight mode.
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 door structure and method of assembling same. The door structure includes a door frame delimiting a door opening. The door frame has a latch housing portion defining a latch housing cavity extending along a length of the door frame. A door is mounted to the door frame and displaceable between an open position and a closed position. The door has a peripheral portion with an outer wall and an inner wall delimiting a cavity of the peripheral portion. A door latch assembly has a first latch member fixedly mounted to the door, and a door manipulator mounted to one of the door and the fuselage and coupled to a second latch member within the latch housing cavity of the door frame. The door manipulator is configured to be manipulated to displace the second latch member to engage and disengage the first latch member.
A method of increasing fuel capacity of a fuel tank. The method includes creating a new filling port in the fuel tank, wherein the new filling port is vertically higher than the original filling port, sealing the original filling port, and installing an expansion tank above a top of the fuel tank, wherein the expansion tank is configured to permit expansion of fuel in the fuel tank beyond a maximum fill level of the fuel tank.
An autonomous thrust vectoring ring wing pod is disclosed. A plurality of distributed propulsion element (thruster) layout within a self-articulating ring wing pod allows the pod to selectively control its thrust vector by controlling each propulsion element in the pod. This arrangement allows autonomous and independent control of the tilting of the ring wing relative to the aircraft. The ring wing pod acts as both a nacelle to house the propulsion elements as well as a lifting surface when in wing-borne flight. The autonomous thrust vectoring ring wing pod also provides superior aircraft attitude control in wing-borne flight, thus negating the need for conventional surface controls.
B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
A windowed structure includes a body having a frame with an outer wall extending between a first end and a second end. An inner wall extends from the outer wall. The inner wall is connected to the outer wall at the first end to define a proximal joint of the body delimiting a window opening extending through the body. A window element covers the window opening and defines an outer window surface and an inner window surface. The window element has an overlap segment overlaying the outer wall and attached thereto. An unobstructed portion of the window element is defined between the overlap segment and is unobstructed by the frame between the proximal joint.
A caul body for forming a composite structure comprises a laminate having at least one carbon layer and at least one silicone layer. The at least one silicone layer defines an outer surface of the laminate. The laminate has a first region and a second region. A thickness of the at least one carbon layer in the first region is greater than a thickness of the at least one carbon layer in the second region. The first region has a hardness value greater than a hardness value of the second region.
B32B 27/04 - Layered products essentially comprising synthetic resin as impregnant, bonding, or embedding substance
B32B 7/12 - Interconnection of layers using interposed adhesives or interposed materials with bonding properties
B32B 27/12 - Layered products essentially comprising synthetic resin next to a fibrous or filamentary layer
B32B 27/28 - Layered products essentially comprising synthetic resin comprising copolymers of synthetic resins not wholly covered by any one of the following subgroups
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 37/12 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
B32B 37/15 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with at least one layer being manufactured and immediately laminated before reaching its stable state, e.g. in which a layer is extruded and laminated while in semi-molten state
19.
MOLDING ASSEMBLY AND METHOD OF CO-CURING STIFFENER WITH PANEL
There is disclosed a molding assembly including a mold having a first surface and an opposed second surface. The mold defines a cavity bounded by two side walls converging toward each other from the first surface toward the second surface. Two mandrels are each removably receivable in the cavity and have a first wall, a second wall opposed to the first wall, an inner wall, and an outer wall opposed to the inner wall. The inner walls face each other and define a gap therebetween for receiving a composite material to be cured. The outer walls are angled and each slidably engage a respective one of the two side walls. A method of co-curing a stiffener and a panel is also disclosed.
B29C 70/46 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
A transmission support for securing a transmission to a rotorcraft includes two side beams each including a roof beam portion configured to be secured to structural elements of the rotorcraft cabin, and a pylon beam portion extending from the roof beam portion toward the other of the side beams. The pylon beam portion is configured to engage the transmission upon the transmission being received between the side beams. The support further has cross beams extending between and interconnecting the two side beams. The side beams and cross beams are part of a monolithic structure. A method of manufacturing the transmission support is provided.
Layers of plies of composite material are laid on a convex tool surface. A first layer is placed with a first ply of a first section having a gap edge adjacent a gap edge of a first ply of a second section, the edges being parallel and a contraction distance from each other. A second layer is placed with a second ply of the first section having a gap edge adjacent a gap edge of a second ply of the second section, the edges being parallel and a contraction distance from each other, the second ply of the second section overlapping onto the first ply of the first section by a splice distance. Consolidation and curing cause contraction of the layers toward the tool, allowing the adjacent gap edges of each layer to be in close proximity or in contact after moving toward each other during the contraction.
B32B 3/06 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by features of form at particular places, e.g. in edge regions for attaching the product to another member, e.g. to a support
B32B 5/26 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer another layer also being fibrous or filamentary
B32B 5/28 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by the presence of two or more layers which comprise fibres, filaments, granules, or powder, or are foamed or specifically porous one layer being a fibrous or filamentary layer impregnated with or embedded in a plastic substance
A stacked motor assembly for an aircraft includes a forward motor having an exhaust port and an aft motor disposed aft of the forward motor, the aft motor having an intake port. The stacked motor assembly includes an exhaust conduit originating from the exhaust port of the forward motor and disposed at least partially around the aft motor such that exhaust from the forward motor bypasses the aft motor. The stacked motor assembly also includes an intake conduit terminating at the intake port of the aft motor and disposed at least partially around the forward motor such that intake air for the aft motor bypasses the forward motor.
An unmanned aircraft system has a vertical takeoff and landing flight mode and a forward flight mode. The unmanned aircraft system includes an airframe, a rotor assembly rotatably coupled to the airframe and a propeller rotatably coupled to the airframe. The rotor assembly including at least two rotor blades having tip jets that are operably associated with a compressed gas power system. The propeller is operably associated with an electric power system. In the vertical takeoff and landing flight mode, compressed gas from the compressed gas power system is discharged through the tip jets to rotate the rotor assembly and generate vertical lift. In the forward flight mode, the electric power system drives the propeller to generate forward thrust and autorotation of the rotor assembly generates vertical lift.
A flapping control system for a proprotor assembly of a tiltrotor aircraft includes one or more sensors operable to detect one or more flight parameters of the tiltrotor aircraft to form sensor data. The sensors include a proprotor flapping sensor to detect a proprotor flapping measurement. The flapping control system includes a flapping control module in data communication with the sensors. The flapping control module includes a maneuver detection module to detect whether the tiltrotor aircraft is in a maneuver mode using the sensor data. The flapping control module identifies a maneuver flapping threshold associated with the maneuver mode. The flapping control module generates a swashplate command using the proprotor flapping measurement and the maneuver flapping threshold, and sends the swashplate command to the proprotor assembly to reduce flapping of the proprotor assembly.
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 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
B64C 27/605 - Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical including swash plate, spider or cam mechanisms
25.
METHODS OF MAKING A TUBULAR SPECIMEN WITH A PREDETERMINED WRINKLE DEFECT
ABSTRACT There is a method of making a tubular specimen with a predetermined wrinkle defect including providing a layup tool with a cavity forming member having a cavity which resembles a desired shape of the at least one wrinkle; orienting a composite material around the mandrel at a wrap angle to form a closed loop; positioning a wrinkle tool on the closed loop; and/or generating at least one wrinkle with a predetermined characteristic in a portion of the closed loop to form a tubular specimen. The predetermined characteristic is at least one of the following: wrinkle location, an outward wrinkle, an inward wrinkle, a wrinkle width, a wrinkle height, and a wrinkle length. In another aspect, there is a method of offset load testing a tubular composite specimen. In a third aspect, there is a method of determining allowable defects for a composite component. Date Recue/Date Received 2020-05-22
An aircraft including a nacelle disposed at a fixed location relative a wing member; a proprotor housing coupled to the nacelle, the proprotor housing configured to selectively rotate between a horizontal orientation and a non-horizontal orientation; a door pivotably coupled to the proprotor housing; and a linkage to connect the door and the nacelle, the linkage configured to move with the door from a closed position when the proprotor housing is in a horizontal orientation to an open position when the proprotor housing is in a non-horizontal orientation. In some embodiments, there can be a hinge member for hingedly coupling the door to the proprotor and/or nacelle. In other embodiments, the door includes a flexure portion. In some embodiments, the nacelle includes a plurality of doors. In other embodiments, proprotor includes a forward portion and a stationary aft portion; wherein the forward portion is configured to selectively pivot.
B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
B64D 29/02 - Power-plant nacelles, fairings, or cowlings associated with wings
A proprotor system for tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system includes a hub and a plurality of proprotor blades coupled to the hub such that each proprotor blade is operable to independently flap relative to the hub and independently change pitch. In the airplane mode, the proprotor blades have a first in-plane frequency greater than 2.0/rev.
B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
A transportation services method comprises receiving a request for transportation of a pod assembly. Characterized in the steps of coupling the pod assembly (70, 170) to a flying frame (12); rotating the flying frame including the at least two propulsion assemblies (36, 38, 40, 42, 44, 46, 48, 50, 136, 138, 140, 142, 144, 146, 148, 150) directly coupled to each wing (14, 16, 114, 116) relative to the pod assembly to transition the flying frame between a vertical takeoff and landing mode wherein the first wing is forward of the pod assembly and the second wing is aft of the pod assembly and a forward flight mode wherein the first wing is below the pod assembly and the second wing is above the pod assembly; and decoupling the pod assembly at the destination. The rotation to the forward flight mode allowing the slipstream from the propellers to strike the wing on its smallest dimension, thus improving vertical thrust efficiency as compared to tiltrotor aircraft.
B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
B64C 27/30 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with provision for reducing drag of inoperative rotor
B64D 1/22 - Taking-up articles from earth's surface
B64D 5/00 - Aircraft transported by aircraft, e.g. for release or reberthing during flight
29.
ROTOR ASSEMBLY HAVING THRUST VECTORING CAPABILITIES
A rotor assembly for an aircraft is operable to generate a variable thrust vector. The rotor assembly includes a mast that is rotatable about a mast axis. A ball joint is positioned about and non rotatable with the mast. A tilt control assembly is positioned on and has a tilting degree of freedom relative to the ball joint. The tilt control assembly is non rotatable with the mast. A rotor hub is rotatably coupled to the tilt control assembly. The rotor hub is rotatable with the mast in a rotational plane and tiltable with the tilt control assembly. The rotor hub includes a plurality of grips each coupled to a rotor blade. Actuation of the tilt control assembly changes the rotational plane of the rotor hub relative to the mast axis, thereby generating the variable thrust vector.
B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
An aircraft has a vertical takeoff and landing flight mode and a forward flight mode. The aircraft includes an airframe with first and second M-wings each having a pair of leading apexes with swept forward and swept back portions extending therefrom at a swept angle. A propulsion system includes a plurality of propulsion assemblies each attached to the airframe proximate one of the leading apexes. Each of the propulsion assemblies includes a rotor assembly having a tilting degree of freedom. A flight control system is operable to control the propulsion assemblies including tilting the rotor assemblies to generate variable thrust vectors that have a maximum angle that is generally congruent with the swept angles of the M-wings.
B64C 29/02 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
31.
TASK-BASED HEALTH DATA MONITORING OF AIRCRAFT COMPONENTS
Systems and methods are provided for task-based health data monitoring relating to aircraft components of aircraft within an aircraft fleet. One method includes identifying health data of an aircraft component for potential monitoring based upon a condition indicator provided by a health and usage monitoring system, establishing a Review Item for the health data of the aircraft component having an initial data review state of New Data, thereby creating a Review Task, generating images of the Review Item for display and receiving an indication to change the data review state of the Review Item from New Data to Watch Data, receiving new health data relating to the aircraft component from the health and usage monitoring system and automatically resetting the data review state of the Review Item from Watch Data to New Data responsive to the receipt of the new health data, thereby creating a new Review Task.
A torque box assembly for an aircraft wing comprises an upper skin composite assembly, a lower skin composite assembly, and an aft spar assembly attached to the upper skin composite assembly and the lower skin composite assembly. A forward spar assembly is attached to the upper skin composite assembly and the lower skin composite assembly and forward of the aft spar assembly. The forward spar assembly comprises a support beam, an upper spar flange, and a lower spar flange. The support beam has an interior surface, and an exterior surface. The upper spar flange extends generally laterally from the exterior surface and outward. The upper spar flange is attached to the-upper skin composite assembly. The lower spar flange extends generally laterally from the interior surface. The lower spar flange is attached to the lower skin composite assembly. The forward spar assembly is substantially "Z" shaped.
B64C 27/28 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
33.
COMPOSITE WING STRUCTURE AND METHODS OF MANUFACTURE
A pre-cured laminate having a total number of plies formed in a mold. The mold has a cavity having a periphery defined by a forward edge, an aft edge, and outboard ends. The laminate comprises a first plurality of resin impregnated plies that continuously extend beyond the periphery of the mold. The first plurality of resin impregnated plies comprises at least 50 percent of the total number of plies. The laminate has a second plurality of plies that do not extend beyond the forward edge and continuously extend beyond the aft edge of the cavity; a third plurality of plies that do not extend beyond the aft edge and continuously extend beyond the forward edge of the cavity; and a fourth plurality of plies that do not extend beyond the outboard ends and continuously extend beyond the forward and aft edges of the cavity.
B64C 1/12 - Construction or attachment of skin panels
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
B32B 27/04 - Layered products essentially comprising synthetic resin as impregnant, bonding, or embedding substance
B32B 37/15 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with at least one layer being manufactured and immediately laminated before reaching its stable state, e.g. in which a layer is extruded and laminated while in semi-molten state
B64C 3/26 - Construction, shape, or attachment of separate skins, e.g. panels
C08J 5/24 - Impregnating materials with prepolymers which can be polymerised in situ, e.g. manufacture of prepregs
An air vehicle, as well as a method for folding an air vehicle for storage, may include a fuselage and a wing connected to the fuselage. The wing may include two ends positioned opposite from each other, and the wing may be substantially perpendicular to the fuselage. At least one of the ends may define a space therebetween the fuselage and the wing. The space may be sized to receive a potion of the wing when the wing is wrapped around the fuselage.
An airfoil member includes a skin member defining an airfoil surface. The airfoil surface has a leading edge surface, an upper airfoil surface, and a lower airfoil surface. An abrasion resistant layer partially covers the skin member. A cermet coating exterior to the skin member covers the abrasion resistant layer. The cermet coating is configured to protect the airfoil member against erosion during operation. The cermet coating includes a ceramic material, and a metallic material. The cermet coating extends chordwise on the upper and lower airfoil surfaces beyond the abrasion resistant layer such that the cermet coating is also applied directly to the skin member.
A method for braking an electric utility vehicle including a motor and an electromechanical brake. The method includes storing a value indicative of at least one of an amount of current, voltage, and power that is commanded to a motor of the electric utility vehicle to maintain the electric utility vehicle in a stopped state; engaging a parking brake function of an electromechanical brake after the storing; disabling the motor after the engaging; commanding the at least one of the current, voltage, and power to the motor at the stored value when an accelerator pedal is depressed; and disengaging the parking brake function after the commanding.
A drive system for an electric vehicle includes a motor for providing a drive torque and an electrically actuated brake for providing a braking torque to the motor. The system includes a controller that receives a plurality of inputs which may include a battery voltage input, a throttle pedal position input, a brake pedal position input, a key switch input, a forward/neutral/reverse (FNR) input, and a brake full-stroke input in addition to the brake pedal input. The controller may generate a drive signal for the motor based on some or all of the inputs.
B60L 50/51 - Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells characterised by AC-motors
H02P 27/06 - Arrangements or methods for the control of AC motors characterised by the kind of supply voltage using variable-frequency supply voltage, e.g. inverter or converter supply voltage using dc to ac converters or inverters
patents
