Abstract: This disclosure details overmolded vehicle sheet metal structures that included integrated attachments for achieving part integration. An exemplary sheet metal structure includes a sheet metal panel, a reinforcing structure molded on the sheet metal panel, and an integrally molded attachment structure formed within the reinforcing structure. In some embodiments, the integrally molded attachment structure may include a nut, a bracket, or both. An additional vehicle component may be attached to the sheet metal panel via the integrally molded attachment structure. The sheet metal structure may be formed in a single shot injection molding process.

Abstract: Apparatus (102) for connecting an object (104) to a part of a vehicle (106), the mounting apparatus (102) including two or more of a first mechanism (108) adjustable in a direction substantially parallel with respect to the left-right axis of the vehicle, a second mechanism (110) adjustable in a direction substantially parallel with respect to the front-to-rear axis of the vehicle, and a third mechanism (112) adjustable in a direction substantially parallel with respect to the vertical axis of the vehicle.

Abstract: A slide-out undercarriage mounted on an underside of a first trailer pulled by a highway tractor. The slide-out undercarriage is adapted for attaching a rear of the first trailer to a front of a second trailer. The slide-out undercarriage includes a fixed undercarriage frame mounted on an underside of a first trailer. A front axle with front wheels is mounted on a front axle frame and a rear axle with rear wheels is mounted on a rear axle frame. The rear axle frame includes a fifth wheel adapted for engaging a king pin on the front of the second trailer. A pair of first slide out tubes are attached to the front axle frame. A pair of second slide out tubes are attached to the rear axle frame. The first and second slide out tubes provide for allowing an operator of the first trailer to adjust the front and rear axles in various load positions under the first trailer when pulling the second trailer.

Abstract: A trailer enclosure which is very easy to load and unload, by providing a trailer platform, with an enclosure which has a closed position and a raised position, and which is raised and lowered by a lift mechanism connected to the enclosure which raises the enclosure to the raised position, and can also lower the enclosure to its closed position.

Abstract: A bicycle parking rack includes a rectangular base and at least two restriction members are connected to the base. Each restriction member includes two first sections and a connection section formed between the two first sections. Two support members are respectively connected between the at least two restriction members. Each support member includes a support portion and two connection portions which are formed on two sides of the support portion. The two connection portions are respectively connected to the two first sections of the at least two restriction members corresponding thereto. The support portion of each support member has a recess which accommodates a portion of a bicycle wheel. The restriction members of the bicycle parking rack restrict the bicycle wheel between the two restriction members.

Abstract: A rider's seat for a two-wheeled vehicle, in particular a scooter, includes a seating body and a bracket connecting the seating body to a body of the two-wheeled vehicle. The bracket is displaceable relative to the body of the two-wheeled vehicle along a longitudinal direction of the two-wheeled vehicle. The seating body is displaceable relative to the bracket at least along a vertical direction of the two-wheeled vehicle. The seating body is partially received within a guide of the bracket such that the guide of the bracket directs displacement of the seating body at least along the vertical direction of the two-wheeled vehicle. The guide of the bracket includes a curvilinear profile.

Abstract: This adjustment mechanism/assembly for a backrest/headrest includes a series of parts connected by a threaded rod with a knob on each end. The parts are arranged such that they sandwich two support members so that when the knobs are loosened the unit can easily slide up and down, changing the elevation of the backrest/headrest pad unit with respect to a seat bottom or seat back. Further, when the knobs are loose the upper member and its attached pad can be pivoted fore and aft and slide back and forth. Tightening the two knobs locks the entire unit in place.

Abstract: An ebike comprises a front wheel, a rear wheel, a frame structure supported on the front wheel and the rear wheel, a motor assembly coupled to the frame structure, and a battery assembly configured to be coupled to the frame structure. The frame structure includes a head tube, a down tube, a top tube, a seat tube, and a diagonal tube coupling the top tube with the seat tube. The battery assembly is configured to be at least partially positioned in the down tube. The ebike further includes a user interface configured to be supported by the frame structure, and further includes an electrical cable coupling the user interface with the motor assembly, the electrical cable being positioned at least partially in the diagonal tube.

Abstract: A system for adjusting the damper force on the suspension system of a bicycle is provided. Sensors are placed on the front shock and rear shock to measure the amplitude of displacement or acceleration in the time domain and generate a zenith position, velocity, force, and work based on the measured values. The system calculates a curve fit approximation curve for the relationships of zenith position versus velocity and uses the approximation curves to generate and display recommended damper settings for the front shock and rear shock. Using the data ensures that the bicycle suspension data is balanced, such that the front shock and rear shock respond similarly to the same event.

Abstract: A tilting motor cycle with at least three wheels including: a frame, at least one front wheel, a rear end comprising an engine group and a couple of rear wheels, where the rear end is hinged to the frame in order to allow a rolling of the frame around a rolling axis and a pitching of the rear end around a pitching axis, where the rear end is further connected to the frame by means of a suspension system including: a couple of uprights connected at the bottom by means of two first hinges to the engine group, at least one first crosspiece hinged at the distal ends thereof to the uprights, the center of the first crosspiece being connected to the frame directly or indirectly by means of a transmission element, the uprights or the transmission element including a suspension to dampen the rear end with respect to the frame.

Abstract: A motorcycle frame including a left side frame member, a right side frame member, and a steering head member positioned along a longitudinal center plane of the frame between the left and right side frame members. The steering head member includes a steering head portion defining a steering axis. A plurality of fastener joints are established between the steering head member, the left side frame member, and the right side frame member, the plurality of fastener joints positioned rearward of the steering head portion. A fastener joint, separate from the plurality of fastener joints, is established rearward of the plurality of fastener joints between the steering head and the left side frame member. A fastener joint, separate from the plurality of fastener joints, is established rearward of the plurality of fastener joints between the steering head and the right side frame member.

Abstract: A bicycle frame includes an antenna and is formed with the antenna as an integrated part of the frame structure, and the antenna constituting part of the outside of the bicycle frame. In a method of equipping a bicycle frame made from carbon with an antenna, the antenna is interwoven with the carbon structure of the bicycle frame as part of the production of the bicycle frame.

Abstract: A rotatable folding bicycle stem includes a stem rotatably mounted on the standpipe with defining a stem rotating axis. An upper end of the stem terminates in a forwardly projecting O-shaped loop. A distance between the stem rotating axis to a center of the O-shaped loop is smaller than a distance between the standpipe rotating axis to the center of the O-shaped loop. A space between the handlebar and the frame could be reduced or became smaller by utilizing the present invention. The smaller folded size of the folding bicycle facilitates storage by users and is beneficial in that the bicycle may be stacked or compacted more tightly when loading in a cargo car of a container for delivery, thereby reducing a shipping cost for a single bike and increasing a loading quantity in single container.

Abstract: An electrically assisted bicycle assist force calculation method includes obtaining from a pedaling force sensor an instant pedaling force applied to a pedal, obtaining a crank advance angle of a crankshaft from an advance angle sensor having a resolution of less than 90°, and determining an assist force based on at least the instant pedaling force and the crank advance angle.

Abstract: A shade system for a structure includes a pair of support posts attachable to the structure, a shade panel including a plurality of attachment points around a periphery thereof, and at least one flexible lateral support member secured to the shade panel. The plurality of attachment points includes a fixture pair securable to a fixture of the structure, a post pair securable to the pair of support posts, respectively, and a side pair cooperable with the at least one flexible lateral support member and securable to the structure.

Abstract: This invention provides improvements in the efficiency of a sailing vessel through the use of flaps, hydrofoils, or members on the keel of a sailing vessel. One or more are positioned at the top, or root of the keel of the vessel, which primarily generate a force in the windward direction to provide a counter-leeward drift force. One or more are located at the bottom, or tip of the keel of the vessel, which primarily generate a force in the leeward direction to provide a counter-heeling moment. Among other benefits, operation of these flaps, hydrofoils, or members during sailing increases the vessel's efficiency, in particular its velocity made good. Further, since they are mounted on one appendage, sailing vessels of a rudder and keel design can be equipped with counter leeward-drift and counter-heeling attributes without the need for additional appendages.

Abstract: A vessel propulsion system includes a bow thruster located at a bow of a hull, an outboard motor located on the hull and provided separately from the bow thruster, and a navigation controller. The navigation controller controls at least one of the bow thruster and the outboard motor in accordance with a state of at least one other of the bow thruster and the outboard motor.

Abstract: The present disclosure relates to an aircraft. The aircraft has a primary structural element, which extends along a main axis of the aircraft, and at least one monolithic structural component, which is produced by a three-dimensional printing method. The aircraft also has an aircraft system for carrying out an aircraft-specific function. The at least one monolithic structural component is fixed on the primary structural element by a fixing device, system, means, or mechanism. The monolithic structural component is embodied to accommodate the aircraft system. The disclosure also relates to a method for producing an aircraft.

Abstract: A cargo hold component system for a cargo hold of an aircraft, the cargo hold component system including floor elements and fixing elements. The floor elements can at least partially be fixed releasably by the fixing elements to fixing sites provided on or in the hold floor, such that in a state fixed to the fixing sites, the floor elements support a loading of the hold with cargo containers, and that in a state in which a first group of the floor elements has been removed from the fixing sites by release of the fixing elements and a second group of the floor elements has been partially removed from the fixing sites by release of the fixing elements, the hold is sealed gas-tightly.

Abstract: Integrated slat chine apparatus and methods are described. An example method comprises moving a slat relative to an airfoil between a stowed position and a deployed position. The slat is coupled to the airfoil. The slat is located adjacent a lateral surface of a chine. The chine is coupled to the airfoil. The slat is to expose the lateral surface of the chine when the slat is in the deployed position and to cover the lateral surface of the chine when the slat is in the stowed position.

Abstract: Aircraft wing assemblies are disclosed herein. An example apparatus disclosed herein includes a trailing edge of a wing of an aircraft. The trailing edge has an elastically deformable skin defining a first surface. The trailing edge has a first end to be fixed to the wing and a second end opposite the first end that is to move relative to the first end. A flap is movably coupled to the second end of the trailing edge. The flap is movable between a stowed position and a deployed position. The trailing edge is to elastically elongate when the flap moves from the stowed position to the deployed position and the trailing edge is to elastically collapse when the flap moves from the deployed position to the stowed position.

Abstract: A linkage mechanism for a flaperon includes a support structure linkage, a droop panel linkage, and a flaperon linkage. The support structure linkage is pivotally attached to a support structure of a wing of an aircraft. The droop panel linkage is pivotally attached a droop panel. The flaperon linkage is pivotally attached to a flaperon. A second end of the droop panel linkage and a second end of the flaperon linkage are pivotally attached to a connecting section of the support structure linkage. The connecting section is spaced apart from the pivot end of the support structure linkage such that the linkage mechanism transfers a pivoting motion from the flaperon into a pivoting motion of the droop panel.

Abstract: An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement. The UAVDC may also comprise a foldable propeller blade with a locking mechanism.

Abstract: A control system (200) using fixed point computation avoids overflow conditions by limiting the internal quantities ensuring that contributing calculations from various parts of the control loop never add up to an overflow. Various parts of a control loop e.g. proportional terms can be prioritised over other parts, e.g. integral and differential terms and ensuring that the overall total resulting when the separate terms are summed together never exceeds the maximum or minimum imposed limits. Variable limit calculator circuits (211,219) revise the limits according to the output of the higher priority control path(s). The revised limits cascade down through each contributor, eventually allowing the lowest priority control path the smallest authority. The control system may be applied to control of a drive motor (111) for an aircraft inceptor (103).

Abstract: An aircraft assembly, having: a reference component; a first component and a first actuator, the first actuator configured to move the first component relative to the reference component; a second component and a second actuator, the second actuator configured to move the second component relative to the reference component; a position sensor configured to measure a position of the first component, and to output a position value, the sensor being capable of outputting a plurality of non-zero position values; and a controller configured to control the movement of the second component by the second actuator based at least partially on the position value output by the position sensor.

Abstract: The present invention provides a motor for a drone, comprising: a rotary shaft; a stator including a hole in which a rotary shaft is arranged; and a rotor arranged on the outer side of the stator, wherein the rotor comprises: a cover part coupled with the rotary shaft and covering the upper part of the stator; a body part covering a side portion of the stator; and a plurality of magnets arranged on an inner circumferential surface of the body part so as to be spaced from each other, wherein the body part includes a plurality of groove portions arranged so as to be spaced from each other, thereby providing an advantageous effect of reducing the weight of a drone by reducing the weight of the rotor.

Abstract: An rotorcraft including a pilot control, a pilot control position sensor connected to the pilot control and operable to generate a position signal indicating a position of the pilot control, a flight control computer (FCC) in signal communication with the pilot control position sensor and operable to provide a tactile cue in the pilot control in response to the position signal indicating the position of the pilot control exceeds a threshold associated with an operating limit, and further operable to determine a tactile cueing value for the tactile cue according to a relationship between the position of the pilot control and the threshold, and generate a cue control signal according to the tactile cueing value, and a tactile cue element connected to the pilot control and in signal communication with the FCC and operable to control action of the pilot control in response to the cue control signal.

Abstract: A method of controlling a tail rotor system includes pivoting a swashplate of the tail rotor system about an axis passing through a diameter of the swashplate. Pivoting the swashplate causes a first linkage of a first pair of linkages coupled between the swashplate and a collective crosshead to move in a first direction and a second linkage of the first pair of linkages coupled between the swashplate and the collective crosshead to move in a second direction that is opposite the first direction. The movement of the first and second linkages causes a plane of rotation of a pair of rotors of the tail rotor system to cant relative to a centerline of a mast of the tail rotor system. A tail rotor system is also disclosed.

Abstract: An exemplary tail rotor includes a first blade assembly configured to rotate in a first direction about an axis of rotation and a second blade assembly configured to rotate in a second direction about the axis of rotation.

Abstract: Systems and methods relate to a vertical takeoff and landing (VTOL) platform that can include a stator and a rotor magnetically levitated by the stator. The rotor and stator can be annular, such that the rotor rotates about a rotational axis. The stator can include magnets that provide guidance, levitation, and drive forces to drive the rotor, as well as to control operation of rotor blades of the rotor that can be independently rotated to specific pitch angles to control at least one of lift, pitch, roll, or yaw of the VTOL platform. Various controllers can be used to enable independent and redundant control of components of the VTOL platform.

Abstract: An aeronautical apparatus is disclosed that has two pairs of wings. Each wing has a thrust-angle motor. A propeller and propeller motor are coupled to each thrust-angle motor. Propeller pitch is controlled by a propeller-pitch motor. The thrust-angle motor allows the propeller axis of rotation to be parallel to the fuselage's longitudinal axis; vertical (perpendicular to longitudinal axis, as in well-known fixed-position, four-propeller drones); and any position between as well as a given range exceeding these bounds which is used for control. An electronic control unit is electronically coupled to the thrust-angle motors, propeller motors, and propeller-pitch motors, which can be independently controlled, to provide the desired thrust and trajectory. Such an apparatus can provide efficient operation in vertical take-off/landing (hovering) and forward (translational) flight modes.

Abstract: A propulsion system for an aerial vehicle or toy aerial vehicle is disclosed. The system comprises a ducted fan or shrouded propeller drive system for driving the vehicle along ground, the ducted fan or shrouded propeller drive system operating in a plane and having a peripheral ground-engagement part or hubless wheel. The system further comprises a ducted fan or shrouded propeller comprising one or more blades rotatable about a ducted fan or shrouded propeller axis for producing thrust, wherein the ducted fan or shrouded propeller is mounted as such that it may tilt or rotate so that during ground travel it may be in the same plane as the hubless wheel and during operation of the ducted fan or shrouded propeller for flight the blades pass through the plane and inside the hubless wheel.

Abstract: The exemplary embodiments herein provide a tether for use with an airborne device, where the tether contains an elongate member having a first end for attaching to a ground attachment point and an opposing second end for attaching to the airborne device where the elongate member has a cross-sectional area which varies across the member. In some embodiments, the tether contains one or more electrically conductive elements, an optional strength element, insulation separating any adjacent electrically conductive elements, and a jacket which surrounds and protects each of the tether components.

Abstract: An unmanned aerial vehicle capable of VTOL operation can include: a vehicle body defining longitudinal and transverse directions and opposing longitudinal sides; a first support boom coupled to the vehicle body at a first transverse axis and extending outwardly from the opposing longitudinal sides; a second support boom coupled to the vehicle body at a second transverse axis positioned rearward from the first transverse axis and extending outwardly from the opposing longitudinal sides; a plurality of electric motors coupled to a one of the first and second support booms, at least two electric motors of the plurality of electric motors positioned on each of the first and second support booms, a rotation axis of each of the at least two electric motors coupled to the second support boom offset in a transverse direction from a rotation axis of each of the at least two adjacent electric motors coupled to the first support boom; a plurality of rotors; and a propulsion system.

Abstract: The rotary wing drone comprises at least one rotor carried by a drone structure, wherein the drone structure comprises a drone body and at least one group of arms comprising a plurality of arms rotatably mounted on the drone body about the same axis of rotation, between a deployed position for flight and a folded position for transport.

Abstract: Embodiments of the present invention relate to a flight direction display method and apparatus, and an unmanned aerial vehicle. The method includes: obtaining a flight direction indication of an aircraft sent by a camera system, where the flight direction indication is determined by the camera system according to a relative angle between a camera apparatus and the aircraft; and displaying the flight direction indication of the aircraft on a shooting preview screen. In this way, a flight direction of the aircraft is controlled according to the flight direction indication, so that in a shooting process, a flight direction of a fuselage of the aircraft is the same as a rotation direction of the camera apparatus, so as to shoot content wanted by the camera apparatus, thereby improving user experience.

Abstract: Systems, apparatuses, and methods are provided herein for unmanned flight optimization. A system for unmanned flight comprises a set of motors configured to provide locomotion to an unmanned aerial vehicle, a set of wings coupled to a body of the unmanned aerial vehicle via an actuator and configured to move relative to the body of the unmanned aerial vehicle, a sensor system on the unmanned aerial vehicle, and a control circuit. The control circuit being configured to: control the unmanned aerial vehicle, cause the set of motors to lift the unmanned aerial vehicle, detect condition parameters based on the sensor system, determine a position for the set of wings based on the condition parameters, and cause the actuator to move the set of wings to the wing position while the unmanned aerial vehicle is in flight.

Abstract: In one embodiment, a method includes limiting functionality of a remote controlled device during a first period of time where a user of the remote controlled device is not authenticated, receiving, from a separate authentication device, identity information of the user of the remote controlled device and information of the remote controlled device via an authentication process, authenticating the user prior to allowing full functionality of the remote controlled device, sending an indication of the identity of the user to the remote controlled device; and in response to determining during the authenticating that the user is verified as a trainee for the remote controlled device, enabling a trainer/trainee setting that allows a trainer to provide control of the remote controlled device to the trainee without functionality of the remote controlled device being limited.

Abstract: A response drone for detecting incidents within a coverage area including multiple zones is provided. With customer permission or affirmative consent, the drone may be programmed to (1) detect (or receive an indication of) triggering activity associated with one of the zones; (2) determine or receive a navigation path to that zone; (3) travel to that zone based upon the determined navigation path; (4) collect sensor data using drone-mounted sensors; and (5) transmit the collected sensor data to a user computing device associated with the coverage area for review. The response drone may be an autonomous drone in wireless communication with a smart home controller that detects triggering activity associated with an insurance-related event (e.g., fire). The autonomous drone may automatically deploy to mitigate damage to insured assets (e.g., a home or personal belongings). The autonomous drone data may be used for subsequent insurance claim handling and/or damage estimation.

Abstract: A precision delivery vehicle having a vehicle body assembly, a fixed wing system, a rotor system and a guidance system. The vehicle body assembly can retain a payload. The fixed wing system includes first and second wings coupled to the vehicle body for fixed wing flight. The rotor system includes a mast structure, a rotor hub rotatable about the mast structure and at least two rotor blades coupled to the rotor hub and rotatable with the rotor hub relative to the mast structure. The at least two rotor blades are movable between a collapsed configuration and a deployed configuration. In the collapsed configuration, the precision delivery vehicle is in fixed wing flight. Upon placement of the at least two rotor blades into the deployed configuration, the precision delivery vehicle is placed into rotative flight. The guidance system is structurally configured to direct the precision delivery vehicle to a target.

Abstract: An unmanned aerial vehicle (UAV) jettison apparatus. The UAV jettison apparatus may comprise a payload bay, fairing, ejector plate, and releasable latch. The payload bay may be mounted beneath an aircraft and may have an inner space and a top plate attached therewith. The fairing may substantially cover the inner space of the payload bay and may have an opening positioned directly below the top plate. The ejector plate, which may be spring-loaded, may substantially cover the opening and may be used to mount the UAV. The releasable latch, which may be disposed between the top plate and the ejector plate, may releasably lock and hold the UAV in a stowed position and, upon release, may allow the ejector plate to move into a launch position, such that the UAV is released and jettisoned from a larger aircraft.

Abstract: In an example, a seating system includes a seat comprising a chamber, a wall structure adjacent to the seat and defining a compartment, a door insert configured to move within the compartment between a starting position and a retracted position, wherein in the starting position, the door is adjacent to the seat and blocks access to the compartment, and in the retracted position, the door is retracted into the wall structure and provides access to the compartment, a closed channel extending from the chamber and operably connected to the door, and a piston operably coupled to the seat and positioned within the chamber, wherein when a load is applied to the seat, the piston is compressed, moving the door from the starting position to the retracted position, and when the load is removed, the piston is decompressed, causing the door to move from the retracted position to the starting position.

Abstract: A vane assembly for distribution of a stratified fluid in an aircraft is taught herein. The vane assembly includes a housing including a housing inlet and a housing outlet. The housing inlet is configured to receive the stratified fluid with the stratified fluid including a first portion and a second portion. The housing outlet is configured to exhaust the stratified fluid. The housing defines an interior housing volume between the housing inlet and the housing outlet. The vane assembly further includes a vane disposed within the interior housing volume and bisecting the interior housing volume. The vane includes a leading edge adjacent the housing inlet and a trailing edge adjacent the housing outlet. The trailing edge is angularly offset from the leading edge.

Abstract: An example apparatus includes an interface to be electrically coupled between a heating element and a power supply, where the heating element associated with an external surface of a vehicle, and where the power supply is to provide power to the heating element. The interface includes a balanced current sensor to measure a differential between a first current of an electrical power line of the heating element and a second current of an electrical return line of the heating element, and a processor to compare the differential to at least one threshold to determine a condition of the heating element.

Abstract: An ice-breaking system for an aircraft, comprising a pneumatic ice-breaking device, an air inlet adapted to receive air from the environment outside the aircraft and an air outlet adapted to discharge air into the outside environment, and a motorized valve having an air loading port connected to the air inlet and an air discharge port connected to the air outlet, the valve being configured to supply air to the pneumatic ice-breaking device in a pulsating way. When the aircraft is in motion, the kinetic energy of the air at the air inlet and originating from the relative motion between the air and the aircraft is converted into air pressure at the pneumatic ice-breaking device, and the air outlet is positioned so that when the aircraft is in motion the air pressure at the air outlet is lower than the outside ambient pressure.

Abstract: A runback system for receiving fluid from a deicing system may comprise a body and a first channel and a second channel defined by the body. A first end of the first channel may be spaced apart from a first end of the second channel. A second end of the first channel and a second end of the second channel may meet and form an outlet at an end of the body.

Abstract: An aircraft includes a compartment assembly having a blowout panel and a packboard configured to stow an evacuation system. The blowout panel may comprise a cover having a bracket mount and a bracket coupled to the bracket mount. The bracket may comprise a mating portion, a flange extending from the mating portion, a curved portion extending from the flange away from the blowout panel, and a lip portion extending from the curved portion opposite the direction of the curved portion. The packboard may comprise a slot configured to receive the bracket.

Abstract: An aircraft with an airframe and at least one thrust producing unit the at least one thrust producing unit being electrically powered by an associated electrical engine that is electrically connected to an electrical energy source via an electrical energy distribution system, wherein the airframe comprises at least one load carrying section and at least one propulsion system carrying section, wherein the at least one load carrying section and the at least one propulsion system carrying section are segregated from each other, wherein the at least one load carrying section is provided for transportation of passengers and/or cargo, and wherein the at least one propulsion system carrying section is provided for carrying at least essentially the electrical energy source and the electrical energy distribution system.

Abstract: An aircraft includes a fuselage; a propulsion system including a power source and a plurality of vertical thrust electric fans driven by the power source; and a wing extending from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing, the wing including a variable geometry assembly extending along the length of the wing and moveable between a forward thrust position and a vertical thrust position, the variable geometry assembly at least partially covering the plurality of vertical thrust electric fans when in the forward thrust position and at least partially exposing the plurality of vertical thrust electric fans when in the vertical thrust position.

Abstract: An aircraft includes a fuselage; a propulsion system including a power source and a plurality of vertical thrust electric fans driven by the power source; and a wing extending from the fuselage. The plurality of vertical thrust electric fans are arranged along a length of the wing, the wing including a variable geometry assembly moveable generally along a horizontal direction between a forward thrust position and a vertical thrust position, the variable geometry assembly at least partially covering at least one vertical thrust electric fan of the plurality of vertical thrust electric fans when in the forward thrust position and at least partially exposing the at least one vertical thrust electric fan when in the vertical thrust position.