04th week of 2020 patent applcation highlights part 17 |
Patent application number | Title | Published |
20200023902 | HITCH ASSIST SYSTEM - A hitch assist system is provided herein that includes a sensing system configured to detect a trailer proximate a vehicle. A steering system is configured to alter a path of the vehicle. A transmission system has one or more gears therein. A controller is disposed within the hitch assist system and is configured to control the steering system of the vehicle along a path to align a hitch ball with a coupler of the trailer, detect a fault of the steering system or a gear change in the transmission system and pausing the control of the vehicle, and monitor the coupler during repositioning of the vehicle. | 2020-01-23 |
20200023903 | APPARATUS AND METHOD FOR DISPLAYING REAR IMAGE OF VEHICLE - Disclosed are an apparatus and method for displaying a rear image of a vehicle. The apparatus for displaying a rear image of a vehicle includes a rear camera configured to capture a rear image of the vehicle, a steering angle sensor configured to sense a steering angle of a steering wheel, a display unit, and an image processing unit configured to convert the rear image captured by the rear camera when the vehicle moves backward into an image in a direction where the vehicle is to move backward according to the steering angle of the steering wheel that is sensed by the steering angle sensor, and display the converted image in the direction where the vehicle is to move backward through the display unit. | 2020-01-23 |
20200023904 | CROSS MEMBER OF VEHICLE BODY AND METHOD OF MANUFACTURING CROSS MEMBER - A cross member includes a plate member. The plate member constitutes a portion of a vehicle body frame, extends in a vehicle width direction, and is formed of metal. The plate member is provided with a level difference portion on a first surface of the plate member, and a cut mark portion on a second surface of the plate member. The second surface is on the opposite side of the first surface of the plate member. The plate member is provided with a thick plate portion on a first side of the plate member in a direction in which the plate member extends, and a thin plate portion on a second side of the plate member in the direction in which the plate member extends, with the level difference portion interposed between the first and second sides. | 2020-01-23 |
20200023905 | VEHICLE BODY SIDE SECTION STRUCTURE - Floor cross members provided above a floor panel are disposed so as to form a gap between each of the floor cross members and rockers. A floor cross extension that is set with a lower withstand strength than the floor cross members connects between each of the floor cross members and the corresponding rocker. | 2020-01-23 |
20200023906 | CLOAKING DEVICES WITH CONVERGING LENSES AND A HEXAGONAL PRISM AND VEHICLES COMPRISING THE SAME - A cloaking device assembly comprises an object-side, an image-side, a reference optical axis extending from the object-side to the image-side, a cloaked region positioned between the object-side and the image-side and a cloaked article positioned within the cloaked region. An object-side converging lens is positioned on the object-side, an image-side converging lens is positioned on the image-side, and a hexagonal prism is positioned within the cloaked region between the object-side converging lens and the image-side converging lens. Light from an object positioned on the object-side of the cloaking device and obscured by the cloaked region propagates through the object-side converging lens, the hexagonal prism, and the image-side converging lens to form an image of the object on the image-side of the cloaking device such that the cloaked region and the cloaked article within the cloaked region do not appear to be positioned between the object and the image. | 2020-01-23 |
20200023907 | STRUCTURE FOR FRONT PART OF VEHICLE - Provided is a structure for a front part of a vehicle, including a vehicle main body, a pair of suspension support portions, and a cowl member connected to the pair of suspension support portions. The cowl member has: an inner part connection portion which has a shape extending continuously in a vehicle width direction between the pair of suspension support portions and which interconnects respective inner parts of the pair of suspension support portions in the vehicle width direction; and a water drain portion which is provided backward of the inner part connection portion in a front-rear direction of the vehicle and drains water toward a side part of the vehicle in the vehicle width direction. The inner part connection portion has a thickness larger than a thickness of the water drain portion. | 2020-01-23 |
20200023908 | INTEGRATED VEHICLE HOOD - A hood of a vehicle includes a rear beam, a front end module or grill opening reinforcement, a thermoplastic central cover extending between the rear beam and the front end module, the thermoplastic central cover comprising reinforcements along sides of the thermoplastic central cover between the rear beam and the front end module, the reinforcements extending longitudinally between the front end module and the rear beam, with a flange extending from a side of the reinforcement and fenders connected to the front end module and thermoplastic central cover, wherein each fender extends over a reinforcement and connects to a top surface of the thermoplastic central cover. | 2020-01-23 |
20200023909 | REAR SPOILER DEVICE FOR A UTILITY VEHICLE - A rear spoiler device for a utility vehicle has: a first roof air-guiding element for attaching to a first rear door and a second roof air-guiding element for attaching to a second rear doo. The two roof air-guiding elements are adjustable between a folded-in basic position and a driving position for the aerodynamic extension of the contour of a roof surface. A manual adjustment device for adjusting the first roof air-guiding element between the basic position and driving position. A coupling device is provided for coupling the pivoting movements of the roof air-guiding elements. The coupling device carries along the second roof air-guiding element during the adjustment of the first roof air-guiding element. The coupling device may be an overlapping element. | 2020-01-23 |
20200023910 | SYSTEM FOR IMPROVING THE AERODYNAMICS OF A LAND VEHICLE - The invention relates to a system for a land vehicle ( | 2020-01-23 |
20200023911 | AERODYNAMIC TRACTOR-TRAILER - A tractor-trailer is disclosed, with associated apparatuses. A tractor may include a tractor air duct disposed underneath a cab. The tractor air duct may extend between a front opening at a front of the tractor and a rear opening at a rear of the tractor. A trailer may include a duct system that receives airflow from the rear opening of the tractor air duct and directs the airflow to a location behind a cargo compartment. An air distributor may be disposed behind the cargo compartment. An air distributor may include a fairing with openings, so that airflow from the duct system enters a space between the cargo compartment and the fairing, and exits the openings behind the trailer. | 2020-01-23 |
20200023912 | TANK TRAILER WRAP - An aerodynamic wrap for use with a tank trailer illustratively includes opposing first and second side assemblies. In an illustrative embodiment, each side assembly includes an upper panel pivotably supported by the tank trailer, and a lower panel pivotably supported by the upper panel. A lower connecting member illustratively couples the lower panels of the first and second side assemblies under the belly of the tank trailer. | 2020-01-23 |
20200023913 | SELF-STABILIZING VEHICLE AND CONTROL METHOD THEREOF - A self-stabilizing vehicle includes a mass gyroscope which is fixed at an occupant compartment chassis corresponding to a portion where occupants sit. The occupant compartment portion may tilt outwards in response to the centrifugal force. If the vehicle has three or more wheels, the load is evenly distributed on the left wheel and the right wheel which move oppositely up and down about an effectively centrally-mounted shaft pin. Further, the present disclosure proposes a method for operating the self-stabilizing vehicle. According to the self-stabilizing vehicle and the operating method thereof, a vehicle having a narrow body may be used. When the vehicle undergoes external forces such as the centrifugal force and the crosswind, the occupant compartment can maintain the vertical stability even though the wheels may slide sideways. | 2020-01-23 |
20200023914 | LINK ASSEMBLY WITH THREADED MASTER PIN - A master link box for use with a link assembly of a work machine is disclosed. The master link box may include first and second master links with first and second threaded pin bores and first and second threaded passages, a master link pin with threads on the outer circumferential surface along a distal portion, and first and second fasteners. The master link pin may be inserted into the master link box through one of the first or second pin bores. The fasteners may be secured in the threaded passages such that the first fastener abuts a proximal portion of the master link pin and the second fastener abuts a distal portion of the master link pin. | 2020-01-23 |
20200023915 | MOTORIZED APPARATUS INCLUDING ARTICULATED BODY - A motorized apparatus includes an articulated body assembly, a plurality of wheels coupled to the articulated body assembly, and at least one maintenance device coupled to the articulated body assembly. The articulated body assembly includes a first body and a second body. The articulated body assembly includes a joint coupling the first body to the second body. The first body is pivotable relative to the second body about a pivot axis extending through the joint. At least one wheel is transitionable between a first position and a second position. The motorized apparatus also includes a motor drivingly coupled to the plurality of wheels and configured to move the articulated body assembly relative to a surface. The motorized apparatus further includes at least one magnet coupled to the at least one wheel. | 2020-01-23 |
20200023916 | MODULAR MILITARY VEHICLE - A modular military vehicle and a method for using a modular military vehicle is disclosed. The modular military vehicle can comprise a vehicle hull; a crew module removably mounted to the vehicle hull; a plurality of wheels mounted to the vehicle hull, the plurality of wheels comprising at least one driven wheel; and an electric drive system configured to drive the at least one driven wheel. | 2020-01-23 |
20200023917 | Bicycle Inductive Lock - A bicycle inductive lock included a housing, a lock body, and a control circuit device. An annular latch and the lock body are disposed in the housing. A back cover is configured to close the housing. The annular latch has a first engaging groove, a second engaging groove and a third engaging groove. The lock body includes a first baffle that can be engaged in the first engaging groove or the second engaging groove, a second baffle that can be engaged in third engaging groove, and a speed reduction motor having a lever. The lever includes an angle control block and an eccentric paddle. The control circuit device includes an induction unit and a key fob. The key fob is configured to generate induction with the induction unit for transmitting a signal. With the above configuration, the bicycle inductive lock can sense the signal to be locked or unlocked. | 2020-01-23 |
20200023918 | FLUID FLOW CONTROL STRUCTURE FOR A TELESCOPIC APPARATUS OF A HUMAN POWERED VEHICLE - A fluid flow control structure is provided for a telescopic apparatus of a human powered vehicle. The fluid flow control structure basically comprises a first tube, a second tube and a positioning structure. The second tube is telescopically coupled to the first tube to move in an axial direction. The positioning structure includes first, second and third fluid chambers, and a valve that defines a port that is selectively opened and closed. The valve includes a valve body that is movable relative to a valve seat in the axial direction to change a valve state between a closed state and an open state. The valve body fluidly separates the first and second fluid chambers in the closed state and to fluidly connect the first and second fluid chambers in the open state. The third fluid chamber includes a compressible fluid. | 2020-01-23 |
20200023919 | BICYCLE SEAT AND METHOD FOR PRODUCING A BICYCLE SADDLE - A bicycle saddle is provided that has a saddle shell, saddle frame, a seat cushion, a support element, and an elastomer body. The seat cushion is on an upper side of the saddle shell. The support element is connected to the saddle frame is also provided. The elastomer body is between the saddle shell and the support element in order to decouple the saddle shell from the support element. | 2020-01-23 |
20200023920 | MOTORIZED VEHICLE COMPRISING A CONNECTED FORK CROWN - A motorized vehicle including: a front fork; a steering shaft able to rotate inside a steering column; at least one fork crown coupled to the steering shaft and to the front fork; and at least one electronic component intended to collect and/or transmit data relating to the operation of the motorised vehicle. The fork crown has a body in which there is formed a cavity closed by a cover and an electronic board housed in the cavity and able to centralize and/or process the data supplied by the at least one electronic component. | 2020-01-23 |
20200023921 | Motorcycle Handlebar Featuring Active Vibration Damping - A handlebar for a motor vehicle, in particular a motorcycle or a motorcycle-type vehicle, has a vibration damping mechanism designed to dampen a first vibration of the handlebar. The vibration damping mechanism is designed to detect the first vibration and is equipped with at least one actuator which is effectively coupled to the handlebar in a vibration-transmitting manner and which, in response to the detected first vibration, can be actuated to introduce a second vibration into the handlebar. | 2020-01-23 |
20200023922 | APPARATUS AND SYSTEM FOR REPAIRING IMPACT DAMAGE - An apparatus for repairing an impact damage on a hull includes a body having a through hole along a center axis thereof, an anchor unit provided on one side of the body and configured to be inserted into the hull through the impact damage and to be hooked on an inner wall of the hull, and an elastic member inserted into the through hole and having a first side fixed to the anchor unit and a second side fixed to the body. | 2020-01-23 |
20200023923 | Upending Device for Upending an Elongate Support Structure - The present invention relates to an offshore structure comprising an upending device for upending an elongate support structure from a substantially horizontal loading position on a deck of the offshore structure to a substantially vertical launch position outboard of the offshore structure. The upending device comprising a pivot axis situated near a side of the offshore structure for pivoting the upending device between the loading position and the launch position, a first end of the upending device having a connector member for pivotally connecting to the elongate support structure, the connector member in the launch position is in a position outboard from the side of the offshore structure, and a second end of the upending device is attached to a pulling device that is located on the deck of the offshore structure. The upending device is within reach of one or more hoisting means for lifting the elongate support structure. | 2020-01-23 |
20200023924 | METHOD AND SYSTEM FOR PREVENTING FOULING OF SURFACES - A method of anti-fouling of a surface while said surface is at least partially submersed in an liquid environment, comprising: providing an anti-fouling light; distributing at least part of the light through an optical medium comprising a silicone material and/or UV grade fused silica; emitting the anti-fouling light from the optical medium and from the surface. | 2020-01-23 |
20200023925 | VESSEL HULL CLEANING APPARATUS AND METHOD - The invention relates to an apparatus and related method for cleaning vessel hulls and other subsea structures at sea. In an embodiment, a hull cleaning system comprises a housing defining an interior void; a multifunction bar; a propulsion system; a power system; a positioning system; a water pump operatively connected to the power system; a high flow manifold operatively in fluid communication with the water pump; a hull cleaner; and a suction device configured to selectively adhere the hull cleaning system to a hull. In a further embodiment, a remotely operated work class vehicle, which is typically able to be deployed from any platform outfitted to accept its launch, recovery and support equipment and which may further be innately unstable when not adhered to an underwater structure such as when flying through open water, comprises a frame; an inspection sensor; a hydraulically powered, high pressure water jet pump; a predetermined tooling set connected to the housing; and a propulsion system, which includes a suction device, configured to propel the remotely operated work class vehicle about a surface. | 2020-01-23 |
20200023926 | SYSTEM FOR DANGEROUS CURRENT IDENTIFICATION, CHARACTERIZATION, ALERTING AND FOR DISTRESSED SWIMMER LOCATION AND ASSISTANCE - A vessel includes a body, such as surfboard, that floats in water. One or more thrusters, and one or more sensors are provided on the body. A controller is configured to selectively activate the thrusters to cause the vessel to move along a path through the water, receive sensor data from the one or more sensors while the vessel is moving along the path, determine, based on the sensor data, whether a dangerous condition is present in the water; and output a warning when the dangerous condition is present in the water. For example, the collected sensor data may relate to locations and directions of currents in the water, the dangerous condition may relate to a rip current, and the warning may identify at least one attribute of the rip current. A map identifying a location of the dangerous condition may be generated and forwarded to other devices. | 2020-01-23 |
20200023927 | BUOYANCY GARMENT - Described herein is a garment (e.g., pants, underpants, shorts, headgear, a skullcap, a glove, socks, shoes, a vest, a jacket, a shirt, an undershirt, an undergarment, or a full body suit) that can be worn by a wearer (e.g., military or civilian law enforcement personnel, an emergency first responder, or a dog) that includes inflatable bladders. When activated, the bladders of the garment inflate, thereby providing an increase in buoyancy to the wearer of the garment, e.g., while swimming. | 2020-01-23 |
20200023928 | FLOTATION SYSTEM - A flotation system includes a crotch support and a vest. The crotch support includes a central body, a first pad, a second pad, and first and second elastic bands extending from the first pad. The vest includes a lower torso support and an upper torso stabilization system. The lower torso support can include a flexible body, and first and second flanks extending from the flexible body. The stabilization system can include first and second arms, each having a proximal end extending from the lower torso support, and a distal end. An extension may extend from each distal end to engage the first or second flank. Each of the central body, pads, flexible body, and arms can include a buoyant body. The elastic bands can wrap around the lower torso support such that a compressive force is applied along a circumference defined by a torso of a user. | 2020-01-23 |
20200023929 | FLOTATION SYSTEM - A flotation system includes a crotch support and a vest. The crotch support includes a central body, a first pad, a second pad, and first and second elastic bands extending from the first pad. The vest includes a lower torso support and an upper torso stabilization system. The lower torso support can include a flexible body, first and second flanks extending from the flexible body, and torso grip attached to one of the first and second flanks. The stabilization system can include first and second arms, each having a proximal end extending from the lower torso support, and a distal end. A male or female component of linking system is attached to the lower torso support proximate to the torso grip, and a female or male component is attached to the crotch support. Each of the central body, pads, flexible body, and arms can include a buoyant body. | 2020-01-23 |
20200023930 | BLADE COMPONENT FOR A PROPELLER - The invention relates to a blade component for a propeller. The blade component comprises a base which is attachable to a portion of a propeller hub to at least partially enclose the hub and form at least one open ended passage in the hub to permit flow there through. At least one propeller blade extends substantially radially outwardly from the base, and the at least one blade includes a blade face, a blade back, a leading edge, a trailing edge, and a root section connected to the base. An inlet opening is configured on the base which permits flow from the outside to the inside of the enclosed hub. The base or the hub further include a compartment which sub-divides the open ended passage and forms a further water flow passage when the base is attached to the hub, wherein the operatively forward end of the compartment is closed, and the opposing end is open such that water enters the water flow passage through the inlet opening and is directed to flow there through and exit the rear end of the enclosed hub. The inlet opening is configured to run substantially parallel to the axis of the hub, and the inlet opening is further located in register with the water flow passage there below and substantially adjacent to one side of the compartment. | 2020-01-23 |
20200023931 | Control Lever Unit for Azimuth Thruster - The present disclosure relates to a control lever unit for an azimuth thruster. The control lever unit comprises a base plate, a main body rotatably connected to the base plate, and a handle movably connected to the main body. The handle includes a first handle portion extending away from the main body, and a second handle portion extending as a protrusion away from the first handle portion. The two handle portions may visually and haptically indicate the direction of thrust of the azimuth thruster to the operator. | 2020-01-23 |
20200023932 | METHOD FOR MANUFACTURING RESIN SHEET, RESIN SHEET, METHOD FOR MANUFACTURING STRUCTURAL BODY, STRUCTURAL BODY, AND AIRFRAME OF AIRCRAFT - A method for manufacturing a resin sheet includes a coating step; a heating step; and a pressurizing step. In the coating step, linear metal nanomaterial is coated on a surface of a resin film having thermal plasticity. In the heating step, the resin film having the linear metal nanomaterial coated on the surface thereof is heated and softened. In the pressurizing step, the resin film having the linear metal nanomaterial coated on the surface thereof is pressurized to press the linear metal nanomaterial along a direction orthogonal to the surface on which the linear metal nanomaterial is coated. Thus, the coated linear metal nanomaterial penetrates the resin film to obtain the resin sheet containing the linear metal nanomaterial. | 2020-01-23 |
20200023933 | PRESSURE BULKHEAD AND METHOD OF INSTALLATION - A pressure bulkhead of an aircraft and an associated method of installation are disclosed. The pressure bulkhead comprises an upper bulkhead portion sealingly separating a first pressurized compartment disposed above a floor of the aircraft from an unpressurized zone of the aircraft, and a lower bulkhead portion sealingly separating a second pressurized compartment disposed below the floor of the aircraft from the unpressurized zone of the aircraft. The method of installation can comprise installing the lower bulkhead portion before the upper bulkhead portion in order to facilitate the installation of other components. | 2020-01-23 |
20200023934 | COMPOSITE FUSELAGE ASSEMBLY AND METHODS TO FORM THE ASSEMBLY - A method for manufacturing a composite rear section assembly having a continuous skin solution including obtaining a vertical tail plane tooling that has intermediate tooling for tooling intermediate preforms of a vertical tail plane ( | 2020-01-23 |
20200023935 | DOOR FRAME STABILIZATION - A stabilization assembly for a door frame secured to a fuselage skin of an aircraft and positioned about an opening defined in the fuselage skin including a strap, wherein a first end portion of the strap is secured to the fuselage skin with a first fastener which extends through the first end portion of the strap and through at least a portion of the fuselage skin. A second end portion of the strap is coupled to the door frame and a third portion of the strap extends between the first and second end portions of the strap and spaced apart from the fuselage skin. | 2020-01-23 |
20200023936 | MODULAR CABIN FLOOR INSTALLATION METHOD - A method and apparatus for installing an aircraft cabin floor module inside an aircraft fuselage is disclosed. The cabin floor module is attached to the fuselage with a plurality of linkages having a spherical bearing at each end to allow for the alignment and adjustment of the cabin floor module, and a second joint which includes a lug having a double eccentric bushing which will allow the fastening apertures at the second interface point to line up with precision. | 2020-01-23 |
20200023937 | Deployment System for an Airfoil High Lift Leading Edge Device - Deployment system for adjusting a leading edge high lift device, in particular a slat, between a retracted position, in which, in use, the high lift device is retracted with respect to an airfoil, and at least one deployed position, in which, in use, the high lift device is deployed with respect to the airfoil, comprising at least one actuation unit that is configured to actuate the high lift device between the retracted position and the at least one deployed position, at least one guidance unit that is configured to guide the high lift device during adjustment between the retracted position and the at least one deployed position along an adjustment path, wherein the guidance unit is independent from the actuation unit. | 2020-01-23 |
20200023938 | METHOD AND A CONTROL UNIT FOR CONTROLLING ACTUATION OF A FOLDABLE WING TIP SECTION OF A WING OF AN AIRCRAFT - A method to control folding of a wing tip section about a fixed base wing section by a control system that automatically determines whether: (i) a command signal is received to fold the wing tip section, (ii) a first condition indicating signal indicates that the aircraft is on the ground; (iii) the current speed of the aircraft is no greater than a preset maximum speed, and (iv) the aircraft is not at gate in an airport. | 2020-01-23 |
20200023939 | CONNECTION ASSEMBLY FOR TRANSMITTING LOADS BETWEEN TWO WING ELEMENTS - A C-shaped connection assembly transmits loads in a load plane between a first and a second wing element. The connection assembly comprises a first and a second L-shaped load-bearing device. Each load-bearing device comprises a joint region and two legs extending parallel to the load plane and away from the joint region towards respective end regions. One leg of the first load-bearing device extends parallel to one leg of the second load bearing device. These legs are connected to one another. Two coupling portions which connect the connection assembly to the second wing element are formed in the respective joint regions of the load-bearing devices. Two further coupling portions which connect the connection assembly to the first wing element are formed in respective free end region of the load-bearing device and the joint region of the second load-bearing device. | 2020-01-23 |
20200023940 | METHOD OF IMPROVING A BLADE SO AS TO INCREASE ITS NEGATIVE STALL ANGLE OF ATTACK - A method of improving a blade and also an improved blade and a advancement propeller including the improved blade. The radius of the initial leading edge circle of each airfoil of the blade is increased, and its leading edge is moved away from a pressure side half-airfoil towards a suction side half-airfoil, thereby modifying the airfoil of each cross-section of the blade and modifying the camber of each airfoil. Consequently, the absolute value of the negative stall angle of attack of the blade is increased, thus making it possible to increase the aerodynamic performance of the blade under a negative angle of attack compared with a blade that is not modified, and without significantly degrading its aerodynamic performance under a positive angle of attack. | 2020-01-23 |
20200023941 | System and Method for Controlling Rotorcraft - In an embodiment, a rotorcraft includes: a flight control computer configured to: receive a first sensor signal from a first aircraft sensor of the rotorcraft; receive a second sensor signal from a second aircraft sensor of the rotorcraft, the second aircraft sensor being different from the first aircraft sensor; combine the first sensor signal and the second sensor signal with a complementary filter to determine an estimated vertical speed of the rotorcraft; adjust flight control devices of the rotorcraft according to the estimated vertical speed of the rotorcraft, thereby changing flight characteristics of the rotorcraft; and reset the complementary filter in response to detecting the rotorcraft is grounded. | 2020-01-23 |
20200023942 | CONTROL SYSTEM FOR AN AIRCRAFT - An aircraft includes a first leading edge defining the forward edge of a left aircraft wing, a second leading edge defining the forward edge of a right aircraft wing, a plurality of plasma actuators disposed along the first and second leading edges, a control processing unit communicatively coupled to each plasma actuator, and at least one flight stability sensor communicatively coupled to the control processing unit. The control processing unit commands at least one plasma actuator to generate plasma in response to a signal from the flight stability sensor. | 2020-01-23 |
20200023943 | FLOW FENCE FOR AN AIRCRAFT WINGLET - A wing of an aircraft that includes a wing leading edge, a wing trailing edge, and a wing surface defined by a wing upper surface and a wing lower surface is described herein. The wing extends from the wing root to the wingtip, and the wingtip has a wingtip chord. A winglet extends from the wingtip and has a winglet leading edge, a winglet trailing edge, a winglet inboard surface, a winglet outboard surface, a winglet root having a winglet root chord, and a winglet tip. A flow fence is disposed on the wing surface inboard from the winglet and overlapping with the winglet. The flow fence is adapted to delay and/or prevent airflow separation on the winglet inboard surface at high angle of sideslip, increasing lateral stability and linearizing aircraft behavior at high angle of sideslip. | 2020-01-23 |
20200023944 | WINGTIP DEVICE - A wingtip device may be attached to a baseline wing of an aircraft. The wingtip device may comprise a vertical portion coupled to the baseline wing. The vertical portion may comprise a leading edge and trailing edge. The leading edge and trailing edge may be nonlinear shapes. For example, compound curves, smooth continuous higher order polynomials, or combinations thereof. The leading edge and trailing edge may be shaped as to locate the wingtip device further aft than a conventional winglet design. | 2020-01-23 |
20200023945 | AERODYNAMIC SURFACE OF AN AIRCRAFT - An aerodynamic surface of an aircraft comprises a main part having a leading and a trailing edges and having an airfoil section. The aerodynamic surface also having at least two vortex generators in the form of teeth having edges along the length thereof. The teeth are mounted on the leading edge of the main part so as to be capable of generating two vortex cores on one tooth. The edges of a tooth adjoin the leading edge of the main part of the aerodynamic surface. The radius of an edge of each tooth along the length of the vortex generator is five times less than the radius of the leading edge of the main part. The main part of the aerodynamic surface has a cambered airfoil section, wherein the teeth are mounted with a deflection towards the smallest degree of curvature of the airfoil section of the main part. The invention is intended for reducing an aerodynamic drag at low angles of attack while maintaining an increased load hearing capacity of the aerodynamic surface by generating vortex cores adjoining one of the sides thereof. | 2020-01-23 |
20200023946 | Tiltrotor Aircraft having Rotatable Wing Extensions with Winglets - A pylon assembly for a tiltrotor aircraft includes a rotor assembly rotatably coupled to a fixed pylon and operable to rotate between a vertical takeoff and landing orientation and a forward flight orientation. The rotor assembly includes a proprotor operable to produce a slipstream. A wing extension is rotatably disposed to the outboard end of the fixed pylon such that the rotor assembly and the wing extension are separated by at least a portion of the fixed pylon. The wing extension has a forward edge and an outboard end. A winglet is coupled to the outboard end of the wing extension and has a forward edge. The wing extension and the winglet are configured to rotate in synchrony with the rotor assembly such that the forward edges of the wing extension and the winglet remain in the slipstream of the proprotor. | 2020-01-23 |
20200023947 | TILTING LANDING GEAR SYSTEMS AND METHODS - Systems and methods for mechanically rotating an aircraft about its center-of-gravity (C | 2020-01-23 |
20200023948 | AIRCRAFT LANDING GEAR ASSEMBLY - An aircraft landing gear assembly having a main strut and a bogie beam pivotally coupled to the main strut via a coupling assembly. The coupling assembly is arranged to define a bogie beam pivot axis which is spaced from the landing gear assembly. The coupling assembly includes an arcuate handle portion defined by a first one of the bogie beam and the main strut, and an arcuate passage defined by the other one of the bogie beam and main strut. The arcuate handle portion is slidably housed within the arcuate passage, and the arcuate handle portion and the arcuate passage each define a respective centre point, the respective centre points being coaxial to define the bogie beam pivot axis. | 2020-01-23 |
20200023949 | ANTISKID OPERATION DURING DEGRADED OPERATION - A braking system may include a controller, a first wheel and a second wheel. The first wheel may be laterally displaced from the second wheel by a first distance. A first wheel speed sensor may be coupled to the first wheel and a second wheel sensor may be coupled to the second wheel. The controller may be configured to determine at least one of a slip ratio, a coefficient of friction, or a braking pressure of the second wheel in response to failure of the first wheel speed sensor. The controller may be configured to calculate a consistency value of the at least one of the slip ratio, the coefficient of friction, or the braking pressure. The controller may be configured to adjust a braking pressure of the first wheel speed sensor based upon the consistency value and the first distance. | 2020-01-23 |
20200023951 | Variable Hub-to-Hub Phasing Rotor System - An aircraft includes a first rotor assembly, a second rotor assembly, and a rotor phase angle control system. The system includes a phase adjustor operably associated with the first rotor assembly and the second rotor assembly. The method includes sensing vibrations exerted on the aircraft and offsetting a phase angle of the first rotor assembly and the second rotor assembly to minimize the vibrations. | 2020-01-23 |
20200023952 | Propelling System with Variable Aerodynamic Controls - A propelling system with variable aerodynamic controls is a system used to generate and control the flight forces of an aircraft. The system includes a stator, a rotor, a plurality of propelling units, and a control system. The stator serves as the stationary connection to the aircraft. The rotor revolves the propelling units about a central rotation axis. The control system enables the control of the propelling units. The propelling units generate the flight forces for the aircraft in the desired direction. In addition, each of the propelling units include a blade body, a shaft channel, a spar shaft, and at least one aileron assembly. The shaft channel receives the spar shaft within the blade body. The spar shaft connects the blade body to the rotor. The blade body passively corrects its angle of attack and supports the aileron assembly. The aileron assembly adjusts the pitch of the blade body. | 2020-01-23 |
20200023953 | METHOD OF DETERMINING AN INITIAL LEADING EDGE CIRCLE OF AIRFOILS OF A BLADE AND OF IMPROVING THE BLADE IN ORDER TO INCREASE ITS NEGATIVE STALL ANGLE OF ATTACK - A method of determining an initial leading edge circle for airfoils of a blade and of improving a blade, and also an improved blade and a advancement propeller including the improved blade. The radius of the initial leading edge circle of each airfoil of the blade is determined and then increased, and its leading edge is moved away from a pressure side half-airfoil towards a suction side half-airfoil, thereby modifying the airfoil of each cross-section of the blade and modifying the camber of each airfoil. Consequently, the absolute value of the negative stall angle of attack of the blade is increased, thus making it possible to increase the aerodynamic performance of the blade under a negative angle of attack compared with a blade that is not modified, and without significantly degrading its aerodynamic performance under a positive angle of attack. | 2020-01-23 |
20200023954 | COMPOSITE YOKE FOR ROTOR SYSTEM USING A COMBINATION OF BROAD GOODS AND CHOPPPED FIBER LAYUP - A composite yoke includes a plurality of packs of unidirectional plies and at least one pack of chopped fibers disposed between two adjacent packs of unidirectional plies. A method of manufacturing a composite yoke includes arranging a plurality of plies of unidirectional fibers to form a first pack of unidirectional plies, arranging a layer of chopped fibers on the first pack of unidirectional plies, arranging a plurality of plies of unidirectional fibers on to form a second pack of unidirectional plies on the layer of chopped fibers, curing the composite yoke to form a cured composite yoke, and cutting excess material from the first pack of unidirectional plies, the layer of chopped fibers, and the second pack of unidirectional plies to form a plurality of arms. | 2020-01-23 |
20200023955 | System and Method for Rotorcraft Flight Control - A rotorcraft including a fly-by-wire control system also includes a flight control computer (FCC) operable to control flight of the rotorcraft by sending control signals to flight control elements of the rotorcraft. The rotorcraft includes a flight director system coupled to the FCC and configured to send a target signal to the FCC. The target signal indicates a desired flight characteristic of the rotorcraft. The FCC is configured to receive the target signal from the flight director system, determine control signals based on the target signal, and send the control signals to the flight control elements of the rotorcraft to control the flight of the rotorcraft based on the target signal. | 2020-01-23 |
20200023956 | PITCH CONTROL SYSTEM - A pitch control system configured to vary a pitch angle of at least one of a plurality of propeller blades of a propeller system is provided including a switch movable between a neutral position and a plurality of non-neutral positions. Movement of the switch to a first non-neutral position generates a command to move the propeller blades in a first direction. Movement of the switch to a second non-neutral position generates a command to move the propeller blades in a second direction. Movement of the switch to a third non-neutral position generates a command to move the propeller blades to a zero thrust position. | 2020-01-23 |
20200023957 | Systems and Methods for Acoustic Radiation Control - Disclosed is a system, method, and aircraft for controlling acoustic radiation from an aircraft comprising a plurality of rotor systems and a noise controller configured to regulate acoustic radiation from the plurality of rotor systems. The noise controller can be configured to regulate a commanded flight setting from the flight control system and to output a regulated flight setting to the plurality of rotor systems. Based on the regulated flight setting, the plurality of rotor systems are configured to generate, individually and in aggregate, acoustic radiation having a target acoustic behavior. In certain aspects, the noise controller can change the directionality of acoustic radiation from the plurality of rotor systems, or otherwise tune the acoustic radiation to reduce detectability or annoyance. | 2020-01-23 |
20200023958 | ROTORCRAFT ANTI-TORQUE SYSTEMS AND METHODS THEREFOR - A method of providing an anti-torque force in a rotorcraft with an anti-torque system comprised of a primary ducted tail rotor system mechanically connected to an engine, and a secondary ducted tail rotor system electrically connected to an electric power supply. The method includes receiving an indication of a change in the operating condition of the anti-torque system based upon a change in a rotorcraft condition input, a feedback input associated with a primary ducted tail rotor system and/or a secondary ducted tail rotor system, and/or a pilot input; responsive to the indication of the change, determining, by a control system, an anti-torque control input including at least a secondary output command for controlling the secondary ducted tail rotor system; and transmitting the secondary output command to the secondary ducted tail rotor system to energize at least one ducted tail rotor assembly therein to provide the second anti-torque force. | 2020-01-23 |
20200023959 | LIFT FAN WITH DIFFUSER DUCT - A lift fan apparatus includes: a rotor having at least one rotatable hub carrying at least one row of blades; a duct surrounding the rotor, the duct including spaced-apart peripheral walls extending between an inlet and an exit, the peripheral walls collectively defining a flow channel which includes a diffuser disposed downstream of the rotor, in which a flow area at the exit is greater than a flow area at the rotor; and a plurality of spaced-apart splitters disposed in the diffuser, each of the splitters having opposed side walls extending between an upstream leading edge and a downstream trailing edge, wherein the splitters divide the diffuser into a plurality of side-by-side flow passages. | 2020-01-23 |
20200023960 | Vertical Takeoff and Landing (VTOL) Air Vehicle - A flight control apparatus for fixed-wing aircraft includes a first port wing and first starboard wing, a first port swash plate coupled between a first port rotor and first port electric motor, the first port electric motor coupled to the first port wing, and a first starboard swash plate coupled between a first starboard rotor and first starboard electric motor, the first starboard electric motor coupled to the first starboard wing. | 2020-01-23 |
20200023961 | Devices And Methods For Modifying Width Of Rotor Aircraft During Operational Flight - Devices, systems, and methods are provided in which a wing of a tiltrotor aircraft is rotated during operational flight, for example from a position perpendicular to the aircraft's fuselage through an angle of 30° or more in the direction of flight. This effectively narrows the maximum width of the aircraft, and facilitates maneuvering through closely spaced obstacles. | 2020-01-23 |
20200023962 | VERTICAL TAKE-OFF AND LANDING AIRCRAFT - An aircraft defining longitudinal, lateral and vertical directions the aircraft comprising: | 2020-01-23 |
20200023963 | VERTICAL TAKE-OFF AND LANDING AIRCRAFT - An aircraft defining longitudinal, lateral and vertical directions the aircraft comprising:
| 2020-01-23 |
20200023964 | SYSTEM OF PLAY PLATFORM FOR MULTI-MISSION APPLICATION SPANNING ANY ONE OR COMBINATION OF DOMAINS OR ENVIRONMENTS - A vehicle is described haying an aerodynamically contoured lifting body comprising a plurality of cooperating body modules, wherein at least two of the modules are displaceably secured to each other. The modules include a trust vectoring module operatively coupled to a propulsive mechanism. The thrust vectoring module is dynamically controlled to affect positioning and actuation of the propulsive mechanism to attain a desired positioning of the vehicle and at least one of a plurality of modes of operation thereof. The thrust vectoring module includes a nacelle module carrying the propulsive mechanism thereon and rotatably displaceable about one or more axes extending from the lifting body. The propulsive mechanism is positioned externally, internally, or in combinations thereof of the nacelle module and is tiltably displaceable about one or more axes of the nacelle module. | 2020-01-23 |
20200023965 | AIRCRAFT FLOAT - An aircraft float includes a float body configured to provide buoyancy to an aircraft. The float body includes a skin. A longitudinally extending structural member is located internal to the skin, and the longitudinally extending structural member is coupled to an upper portion of the skin. | 2020-01-23 |
20200023966 | ANTI-PERSONNEL AUTONOMOUS VEHICLE - An anti-personnel autonomous vehicle (APAV) system has a fuselage formed by a directional fragmentation weapon (DFW). An unmanned aerial vehicle (UAV) assembly is engaged to the DFW, the UAV assembly having a plurality of lift units positioned to provide balanced lift on the DFW. A control module integrated in the UAV assembly has a wireless transmitter/receiver communicating with a remote controller. | 2020-01-23 |
20200023967 | AIRCRAFT AND METHOD OF CONTROLLING THE SAME - An aircraft includes: an aircraft body including rotating wings and motors that rotates the rotating wings; wheels arranged on both sides of the aircraft body and rotatably supported around an axis that extends in a left and right direction of the aircraft body; rollers that protrude forward and upward with respect to each of the wheels when the aircraft body is in a horizontal state, and are rotatably supported around an axis that extends in a tangential direction of each of the wheels; and a controller that controls a rotation speed of the motors such that, when the aircraft body is moved in the left and right direction along a vertical wall surface, the aircraft body is inclined forward to bring the rollers into contact with the vertical wall surface, and the aircraft body is inclined to a side where the aircraft body moves in the left and right direction. | 2020-01-23 |
20200023968 | METHOD FOR CONTROLLING UNMANNED AIRCRAFT, SERVER, AND REMOTE CONTROL DEVICE - A method for controlling an unmanned aerial vehicle (“UAV”) includes receiving locking instruction information from a user terminal for locking the UAV. The method also includes transmitting a locking command to a remote control device of the UAV based on the locking instruction information, to instruct the remote control device to lock the UAV based on the locking command. | 2020-01-23 |
20200023969 | METHOD OF FLYING UNMANNED AERIAL ROBOT IN UNMANNED AERIAL SYSTEM AND APPARATUS FOR SUPPORTING THE SAME - A method of analyzing a propeller status of a wireless aerial robot can include measuring status information related to the propeller status by a sensor of a propeller; determining whether an operation of the propeller is abnormal based on the status information; transmitting the status information and operation information regarding whether an operation of the propeller is abnormal to a control unit using short range wireless communication; and analyzing, by the control unit, a flight status of the wireless aerial robot based on the status information and the operation information regarding whether the operation of the propeller is abnormal. | 2020-01-23 |
20200023970 | Electric JetPack Device - The Electric Jetpack Device has multiple electric ducted or clustered electric jets to create enough/sufficient controlled thrust with battery power alone. It is a lightweight vertical take-off with the electrical power of rechargeable batteries for a safe, vertical lift off vehicle. It is capable of carrying an average human or equivalent payload and flying for several minutes per charge. Motors and propellers are powered by the batteries and managed through an Electronic Speed Controller and a flight controller. The Flight Controller balances thrust and limits roll from side to side. By moving the control handles connected and mounted to an aluminum frame, the device and craft is directed. The pivots tilt the cluster of jetpacks slightly forward or back. The frame is connected to a harness, in which the pilot is strapped. The craft is modular and can be connected to another craft creating a “quadcopter” set-up. | 2020-01-23 |
20200023971 | Personal Flight Vehicle - A personal flight vehicle including a platform base assembly that provides a surface upon which the feet of an otherwise free-standing person are positionable, and including a plurality of axial flow propulsion systems positioned about a periphery of the platform base assembly. The propulsion systems generate a thrust flow in a direction substantially perpendicular to the surface of the platform base assembly, where the thrust flow is unobstructed by the platform base assembly. The thrust flow has a sufficient intensity to provide vertical takeoff and landing, flight, hovering and locomotion maneuvers. The vehicle allows the pilot to control the spatial orientation of the platform base assembly by the movement, preferably direct, of at least part of his or her body, and the spatial movement of the vehicle is thus controlled | 2020-01-23 |
20200023972 | DRONE PAYLOAD RELEASE ASSEMBLY - A payload release assembly is disclosed. The payload release assembly includes a body defining a plurality of fingers each defining an opening. A plurality of payload retention pockets are defined between adjacent fingers of the plurality of fingers. A release pin is dimensioned to be received within the openings defined by the plurality of fingers. A motor is adapted to drive the release pin into engagement and out of engagement with the openings defined by the plurality of fingers, such that payloads secured within the payload retention pockets are released from the payload release assembly when the motor drives the release pin out of engagement with a respective opening defined by the plurality of fingers. | 2020-01-23 |
20200023973 | UAV Operation Route Planning Method, UAV Pesticide Spreading Method and Device - The present disclosure provides a UAV operation route planning method, a UAV pesticide spreading planning method and device for providing improvements on the operation accuracy of UAV. The UAV operation route method comprises steps of: obtaining a plurality of sub-areas of an operation area of a UAV; exhausting operation orders of the sub-areas and waypoint sequences in each of the sub-areas, respectively; planning routes according to the operation orders of the sub-areas and the waypoint sequences in each of the sub-areas to obtain all routes in the operation area; and determining a route in all the routes having a total voyage meeting a preset constraint condition as an optimal operation route. | 2020-01-23 |
20200023974 | CABIN AIR INLET MODULE AND CABIN AIR SYSTEM - The invention relates to a cabin air inlet module ( | 2020-01-23 |
20200023975 | DE-ICING APPARATUS - A de-icing apparatus configured to remove ice from a surface part of an aircraft, the de-icing apparatus comprising a heating layer and a conductive surface extending over, and in heat conductive contact with, the heating layer. The conductive surface defines at least a part of the surface part of the aircraft or an aircraft component. The heating layer comprising heating elements defining substantially closed contour zones, each comprising a periphery formed by the heating elements within which an area is defined; the heating layer and the conductive surface configured such that when power is provided to the apparatus the heating elements which fragment ice formed on the surface part of the aircraft according to the shape of the peripheries of the substantially closed contour zones. | 2020-01-23 |
20200023976 | ELECTRICALLY CONDUCTIVE MATERIALS FOR HEATING AND DEICING AIRFOILS - Composite airfoils of the present disclosure comprise a root section including a first surface. The airfoils comprise an intermediate section having a first surface and coupled with the root section at a first end. The airfoils comprise a tip section having a first surface and coupled at a first end with a second end of the intermediate section. The airfoils comprise a conductive material layer adjacent at least one of the first surface of the root section, the first surface of the intermediate section, and the first surface of the tip section. The conductive material comprises a first polymer, a second polymer, and a sulfonic acid. | 2020-01-23 |
20200023977 | METHODS AND SYSTEM FOR DEICING A SURFACE - A method of an embodiment includes receiving data from a sensor that is configured to supply data related to an ice layer thickness on a skin surface, calculating the ice layer thickness, comparing the ice layer thickness to a threshold thickness, vibrating the skin surface using at least one mechanical element for a sufficient duration, sufficient frequency, and sufficient displacement to result in removal of a first portion of the ice layer thereby resulting in at least a partially deiced skin surface, and heating the partially deiced skin surface using at least one heating element. The method of an embodiment further includes heating from a leading edge of the skin surface to a trailing edge of the skin surface and heating the surface to result in a sufficient temperature increase in the skin surface for removal of a second portion of the ice layer. | 2020-01-23 |
20200023978 | PARACHUTE INLET CONTROL SYSTEM AND METHOD - A parachute inlet control system is configured to provide an improved inflation profile for solo and/or clustered parachutes. An inlet parachute is coupled to a main parachute via a plurality of inlet control suspension lines and/or reefing rings. The inlet control suspension lines may be passed through the reefing rings and coupled to an anchor point below the main parachute. The inlet parachute is located in the inlet area of the main parachute, and causes the inlet of the main parachute to rapidly form a desirable shape. The inlet parachute and inlet control suspension lines function as a reefing system to prevent full inflation of the main parachute until a reefing cutter has functioned. In this manner, parachute failures, such as those due to leading and/or lagging parachutes in a parachute cluster, may be reduced or eliminated. | 2020-01-23 |
20200023979 | EMERGENCY VISION SYSTEM WITH FIXED AND HAND-HELD ENCLOSURES - An emergency vision system includes a housing; an inflatable main enclosure having an inflated state and a deflated state, the main enclosure in the deflated state is disposed in the housing, the main enclosure in the inflated state is configured to be stationarily disposed between a user and a source of information required to be seen by the user during a smoke emergency; and a movable hand-held enclosure having an inflated state and a deflated state, the hand-held enclosure in the deflated state is disposed in the housing, the hand-held enclosure in the inflated state is configured to be used by the user to view a second source of information not visible through the main inflatable enclosure. | 2020-01-23 |
20200023980 | REUSABLE EVACUATION SYSTEM RESTRAINT - A releasable restraint for an inflatable slide is disclosed, in accordance with various embodiments. The releasable restraint may comprise a first mating portion having a receptacle. The releasable restraint may comprise a second mating portion having a protrusion. The protrusion may be configured to fit within the receptacle. An adjustment fastener may be coupled to the receptacle and configured to adjust a coupling strength of the releasable restraint. | 2020-01-23 |
20200023981 | PYLON SHAPE WITH GEARED TURBOFAN FOR STRUCTURAL STIFFNESS - A gas turbine includes a mounting structure for mounting the engine to a pylon. A propulsor section includes a fan having a fan diameter. A geared architecture drives the fan. A generator section includes a fan drive turbine that drives the geared architecture. A turbine to fan diameter ratio is substantially less than 45%. | 2020-01-23 |
20200023982 | AIRCRAFT HYBRID PROPULSION FAN DRIVE GEAR SYSTEM DC MOTORS AND GENERATORS - An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear system, a first fan driven by the first gear system, a first generator supported on the first input shaft and a fan drive electric motor providing a drive input to the first fan, a second gas turbine engine including a second input shaft driving a second gear system, a second fan driven by the second gear system, a second generator supported on the second input shaft and a second fan drive electric motor providing a drive input to the second fan and a controller controlling power output from each of the first and second generators and directing the power output between each of the first and second fan drive electric motors. | 2020-01-23 |
20200023983 | DISTRIBUTED ENERGY STORAGE SYSTEM - A modular energy storage system within a vehicle, wherein the energy storage system comprises a plurality of discrete energy storage units which are movable within the vehicle and selectively securable in a variety of positions. | 2020-01-23 |
20200023984 | GAS TURBINE ENGINE MOUNT ARRANGEMENT - A mounting arrangement for mounting an aircraft gas turbine engine to an aircraft includes an engine nacelle with a distal assembly including a part annular engine cowl, a gas turbine engine core housing surrounded by the cowl and a distal bifurcation extending between the engine core housing and engine cowl in a first direction to define a first axis. The mounting arrangement includes a proximal assembly having a mount configured to mount the proximal assembly to the engine core housing. The proximal assembly includes a pylon configured to mount the proximal assembly to mounting location such as a wing of the aircraft at an engine mounting location. The pylon extends in a line between the wing and the engine core housing to define a second axis which is normal to a distal surface of the wing at the engine mounting location and is non-parallel to the vertical axis. | 2020-01-23 |
20200023985 | PRESSURE RECOVERY DEVICE FOR AN AIRCRAFT ENGINE AIR INTAKE - An aircraft includes a fuselage, an engine exhaust port extending through the fuselage, an air intake extending through the fuselage forward from, and adjacent to, the engine exhaust port, and an air cleaning assembly positioned over the air intake. The aircraft also includes a pressure recovery device including an outer wall positioned above the air cleaning assembly. A distance from a forward edge of the outer wall to the air cleaning assembly is greater than a distance from an aft edge of the outer wall to the air cleaning assembly. An inlet flow axis is defined normal to a cross-sectional flow area of the pressure recovery device at the forward edge, and is oriented upward at an acute angle relative to a longitudinal axis of the aircraft. | 2020-01-23 |
20200023986 | SUPERSONIC AIRCRAFT TURBOFAN ENGINE - Engine has core compressor, combustor and turbine, fan located upstream of core and supersonic intake for slowing down incoming air at inlet formed by intake, bypass duct surrounding engine core, fan generates airflow to engine core and bypass airflow through bypass duct. Engine has mixer for exhaust gas flow exiting engine core, bypass airflow exiting bypass duct, thrust nozzle for discharging mixed flows, and controller for thrust produced by engine. To change level of engine thrust between transonic push operation and supersonic cruise operation, controller adjusts one or more components which vary relative areas available for hot exhaust gas flow and cold bypass airflow at mixer while holding fan inlet non-dimensional mass flow w √{square root over ( )} T/P substantially constant, where w is mass flow of incoming air at fan inlet, T is stagnation temperature of incoming air at fan inlet and P is stagnation pressure of incoming air at fan inlet. | 2020-01-23 |
20200023987 | FLUIDIC PROPULSIVE SYSTEM AND THRUST AND LIFT GENERATOR FOR AERIAL VEHICLES - A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector. | 2020-01-23 |
20200023988 | Apparatus for Boundary Layer Air Inlet Utilization - A boundary layer utilization apparatus for intake of air to a high speed aircraft, comprises a first air inlet adjacent an exterior surface of a fuselage of the aircraft and offset from the fuselage enough to integrate a second air inlet in the offset space to ingest and divert the boundary layer air flowing next to the fuselage into the aircraft for a useful purpose such as cooling the engine compartment. The second air inlet is disposed aft of the first air inlet to minimize hot gas re-ingestion. | 2020-01-23 |
20200023989 | HYDROGEN AFTER BURNER - Generally, a vehicle comprising at least one hydrogen releasing element is provided. The vehicle can include at least one hydrogen releasing element coupled to a body of the vehicle. The vehicle can include a hydrogen combustion region positioned adjacent to a predetermined portion of the vehicle body. The vehicle can include at least one ignition element positioned within the hydrogen combustion region that can inflame hydrogen within the hydrogen combustion region. The vehicle can include a housing surrounding the hydrogen combustion region. The housing can form combustion chamber thereby providing additional thrust to the vehicle. In some embodiments, the vehicle is an airborne vehicle. | 2020-01-23 |
20200023990 | SYSTEM AND EQUIPMENT FOR PURGING A RESERVOIR AND ASSOCIATED PURGE AND ASSEMBLY PROCESSES - A system for purging an aircraft fuel reservoir includes a body ( | 2020-01-23 |
20200023991 | LOCKING AND UNLOCKING MECHANISM - A locking mechanism for releasably locking a lock bolt against axial movement includes a solenoid assembly arranged, in use, in proximity to an axially moveable lock bolt. The solenoid assembly includes: a solenoid, a solenoid bias spring and a solenoid plunger having a plunger tip. When the solenoid is energised, the bias spring causes the solenoid plunger to move to bring the plunger tip into locking engagement with the lock bolt to prevent axial movement thereof, and when the solenoid is not energised, the solenoid bias spring causes the solenoid plunger to move to bring the plunger tip out of locking engagement with the lock bolt thus permitting axial movement thereof. | 2020-01-23 |
20200023992 | NETWORK FOR MANAGING AN AIRCRAFT MINIMUM EQUIPMENT LIST - Methods and systems are provided for managing a minimum equipment list (MEL) for an aircraft. The method comprises first generating a MEL that is specific to the aircraft. Next, the performance parameters of the aircraft are monitored. MEL faults are detected by continually comparing the performance to the MEL during operations of the aircraft. A MEL network is notified of the detected MEL faults. The MEL network includes parties affected by the detected MEL faults. | 2020-01-23 |
20200023993 | METHOD AND A DEVICE FOR PREDICTIVE DETERMINATION OF PARAMETERS CHARACTERISTIC OF THE OPERATION OF A ROTARY-WING AIRCRAFT IN ORDER TO PERFORM A PREDETERMINED MANEUVER - A method of predictive determination of a power needed by a rotary-wing aircraft to perform hovering flight in order to land. After measuring the current atmospheric pressure and the current temperature outside the aircraft, the method serves to estimate a predicted atmospheric pressure and a predicted temperature at the altitude where the hovering flight is to be performed. Thereafter, both a maximum power available from a power plant of the aircraft once the aircraft has reached the point where the hovering flight is to be performed, and also a power needed from the power plant in order to perform the hovering flight are calculated. Finally, the present invention serves to display the available maximum power and the power needed on an instrument of the aircraft and thereby warn the pilot of the aircraft when the power needed is close to or even greater than the maximum power available. | 2020-01-23 |
20200023994 | METHOD AND SYSTEM FOR DETERMINING A DESCENT PROFILE - A method and system of determining or estimating a descent profile includes receiving a final approach fix for a target destination, repeatedly back-calculating a set of subsequent models, determining a descent profile based on the repeated back-calculating the set of subsequent models, and operating the aircraft in accordance with the descent profile. | 2020-01-23 |
20200023995 | UNMANNED AERIAL VEHICLE - An unmanned aerial vehicle (UAV) includes a fuselage and an object avoidance device connected to the fuselage. The object avoidance device includes an image sensor. An axis of the image sensor is oblique with respect to the fuselage. | 2020-01-23 |
20200023997 | RUNWAY ARRANGEMENT - A runway arrangement comprising: a first runway section ( | 2020-01-23 |
20200023998 | APPARATUS FOR STORING AIRPLANES - An apparatus for storing airplanes includes a first airplane parking floor at a first elevation, a second airplane floor at a second elevation, and an elevator. The first airplane parking floor defines a vacant region within a notional circle circumscribing the first airplane parking floor and defining a notional circumcenter. The first floor is rotatable about the circumcenter for selective angular alignment of one of several first airplane parking floor regions or the vacant region with a fixed sector of the circle. The second airplane parking floor is rotatable, at the second elevation, about the circumcenter for selective angular alignment of one of several second airplane parking floor region with the vacant region. When so aligned, the second airplane parking floor region may be vertically translated by the elevator between the second elevation and the vacant region at the first elevation. | 2020-01-23 |
20200023999 | METHOD FOR CHARGING BATTERY OF UNMANNED AERIAL ROBOT AND DEVICE FOR SUPPORTING SAME IN UNMANNED AERIAL SYSTEM - The present invention provides a method for charging a battery of an unmanned aerial robot at a station. More specifically, the station monitors a voltage of the battery and charges the battery using wired charging or wireless charging when the voltage of the battery is a threshold voltage value or less. The station controls the unmanned aerial robot such that the unmanned aerial robot performs a specific operation to lower the voltage to a predetermined voltage or less when the voltage is higher than a specific level. The specific level is the specific level is one of a plurality of levels classified according to whether or not the voltage is lowered to the predetermined voltage or less through the specific operation within a first specific time and the specific operation is changed according to each of the plurality of levels. | 2020-01-23 |
20200024000 | SYSTEMS AND METHODS FOR ATTITUDE CONTROL OF TETHERED AEROSTATS - A control system for a tethered aerostat is provided, where at least one rotational and at least one translational degree of freedom are controlled to setpoints through the variation of tether lengths by an actuator system. The term tether includes a single tether, a tether group or a sub section of tether controlled by an individual actuator. Accurate rotational and translational control is essential for the successful operation of an aerostat under several applications, including surveillance, weather monitoring, communications, and power generation. For a given use case, the controller can be constructed and arranged to manage the tradeoff between several key performance characteristics, such as transient performance, steady-state pointing accuracy, tether tension regulation, and power generation. | 2020-01-23 |
20200024001 | AUTONOMOUS OPERATION PLANNING SYSTEM FOR ARTIFICIAL SATELLITE AND OPERATION PLANNING APPARATUS THEREFOR - In a satellite side, there are provided a satellite-side operation parameter storage and an operation planning unit; and on a ground side, there are provided a ground-side operation parameter setting unit, a ground-side operation parameter storage to store operation parameters the same as stored in the operation parameter storage of the satellite-side, and an operation plan estimation unit having the same function as that of the operation planning unit of the satellite side. The ground-side operation parameter setting unit determines operation parameters to be used for the operation plan; and when necessary, the ground-side operation parameter setting unit saves them to the ground-side operation parameter storage and uploads them to the satellite-side operation parameter storage. The ground-side operation plan estimation unit and the satellite-side operation planning unit each produce operation plans according to the same operation parameters. | 2020-01-23 |
20200024002 | ENERGY EXTRACTION AND STORAGE, AND PROPULSION SYSTEMS FOR SPACE VEHICLES - A space vehicle may extract and store energy, and also include a propulsion system. The space vehicle includes one or more wings connected to a body of the apparatus. Each of the one or more wings includes a propellant system configured to eject mass away from the apparatus, the ejection of the mass causes the apparatus to move from a first position to a second position. | 2020-01-23 |
20200024003 | SATELLITE WITH INTEGRAL THRUSTERS - A satellite has thrusters that are integral parts of its frame. The frame defines cavities therein where thrusters are located. The thrusters may include an electrically-operated propellant and electrodes to activate combustion in the electrically-operated propellant. The frame may be additively manufactured, and the propellant and/or the electrodes may also be additively manufactured, with the frame and the propellant and/or the electrodes also being manufactured in a single process. In addition the thrusters may have nozzle portions through which combustion gases exit the thrusters. The thrusters may be located at corners and/or along edges of the frame, and may be used to accomplish any of a variety of maneuvers for the satellite. The satellite may be a small satellite, such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg. | 2020-01-23 |