42nd week of 2017 patent applcation highlights part 20 |
Patent application number | Title | Published |
20170297626 | ENERGY ABSORBING LOAD TRANSMITTAL BRACKET WITH WELD ACCESSIBILITY - A vehicle body structure includes a floor panel, a door frame, a cross-member, and a load transmittal bracket. The door frame and the cross-member are fixed relative to the floor panel. The door frame defines a door opening. The load transmittal bracket is disposed between the door opening and the cross-member. The load transmittal bracket includes a second segment welded to a first segment and to the floor panel. During a side impact of the vehicle, the load transmittal bracket transfers impact force from the door frame to the cross-member to dissipate the impact force and reduce deformation of the floor. | 2017-10-19 |
20170297627 | SIDE-BY-SIDE VEHICLE - The present invention relates to all terrain vehicles having at least a pair of laterally spaced apart seating surfaces. More particularly, the present invention relates to side-by-side all terrain vehicles having plural rows of seats. | 2017-10-19 |
20170297628 | BODY STRUCTURE OF VEHICLE - A body structure of a vehicle includes: a first panel and a second panel forming a closed cross-sectional portion; a partition panel; a first reinforcement body disposed between the first panel and the partition panel, and includes a first panel joint portion joined to the first panel, and a first flange portion joined to the partition panel; and a second reinforcement body which is disposed between the second panel and the partition panel, and includes a second panel joint portion joined to the second panel, and a second flange portion joined to the partition panel. A joint portion includes a rigid coupling portion in which the first panel and the first panel joint portion are coupled while being in contact with each other, and a flexible coupling portion in which the partition panel and the first flange portion are coupled to each other while interposing a damping member therebetween. | 2017-10-19 |
20170297629 | HOOD PANEL FOR VEHICLE - A hood panel is provided. The hood panel includes a plurality of first layers formed of a reinforced fiber and a resin and a plurality of second layers including a complex portion formed of a reinforced fiber and a resin and a resin portion formed of a resin. The first layer and the second layers form a multilayer structure. A reinforced area is formed by the first layers and the complex portions of the second layers and a shock absorption area is formed by the first layers and the resin portions of the second layers. | 2017-10-19 |
20170297630 | INTEGRATED FASTENER FOR INSTRUMENTATION CLUSTER - An integrated fastener for an instrument cluster assembly, where multiple integrated fasteners are used to connect the front cover of the assembly to the back cover. The instrument cluster assembly includes at least one fastener integrated into the back cover, a first recessed portion formed as part of the back cover, and a separation wall formed as part of the back cover in proximity to the first recessed portion. A first mounting aperture is formed as part of the separation wall, and the integrated fastener attached to the back cover and located in the first mounting aperture when the integrated fastener is in a first configuration. The integrated fastener is detached from the back cover and rotated such that the integrated fastener is placed in a second configuration, securing the front cover to the back cover. | 2017-10-19 |
20170297631 | VEHICLE UNDERBODY STRUCTURE AND VEHICLE BODY - The vehicle underbody structure ( | 2017-10-19 |
20170297632 | VEHICLE BODY STRUCTURE OF AUTOMOBILE - Since a recess | 2017-10-19 |
20170297633 | VEHICLE BODY STRUCTURE - A metallic joint | 2017-10-19 |
20170297634 | PLASMA ACTUATOR FOR VEHICLE AERODYNAMIC DRAG REDUCTION - A plasma actuator includes a first electrode disposed on a substrate, covered by a dielectric layer, and a second electrode disposed on the dielectric layer. In operation, the plasma actuator creates a plasma region, altering air flowing over the actuator. The plasma actuator in various embodiments: has no moving parts, helps to improve fuel economy by reducing aerodynamic drag, improves vehicle stability control under severe unsteady flow environments, reduces wind noise around a vehicle on which the actuator is used, and reduces emission and CO2 foot print through the fuel economy improvement. | 2017-10-19 |
20170297635 | AIR FAIRING FOR FRAMELESS TRAILER - An air fairing device is connected below the bottom a frameless trailer to improve aerodynamic efficiency and improve fuel economy. One embodiment of the air fairing device provides an air deflector positioned forward of a trolley which supports the frameless trailer at a rear end. A second embodiment of the air fairing device provides two deflectors mounted below the frameless trailer. The first deflector is attached and extends downward from an articulating arm, said arm connecting the trailer to a semi-tractor or truck. The second deflector connected to below the bottom of the frameless trailer and positioned rear of the first deflector and forward of the trolley. A third embodiment is similar to the second but further includes a third deflector positioned between two axles of the trolley. | 2017-10-19 |
20170297636 | SINGLE FORM MULTI-AIRFOIL ELEMENT REAR AERODYNAMIC WING - A multi-airfoil element wing includes a central single-airfoil element and an outer dual-airfoil element positioned outboard of each side of the central single-airfoil element. The single-piece member defines aerodynamic surfaces of the central airfoil element and both of the outer dual-airfoil elements. The single-piece member includes a carbon fiber resin hollow body forming at least a portion of the central single-airfoil element and of both outer dual-airfoil elements. | 2017-10-19 |
20170297637 | CONFIGURABLE REAR UNDERBODY AERODYNAMIC DIFFUSER - Multiple vertical panel strakes extend from a rear underbody of the automobile in a street configuration. Multiple vertical panel extensions include extension coupling elements designed to removably couple the vertical panel extensions to the plurality of vertical strakes in a track configuration. When the rear underbody aerodynamic diffuser is in the street configuration, the plurality of vertical panel extensions are uncoupled from the plurality of vertical panel strakes and the vertical panel strakes have an overall width that extends a vertical street distance. When the rear underbody aerodynamic diffuser is in the track configuration, the plurality of vertical panel extensions are removably coupled to the plurality of vertical panel strakes and the combined vertical panel strakes and vertical panel extensions have an overall width that extends a vertical track distance that is greater than the vertical street distance. | 2017-10-19 |
20170297638 | BELLOWS FOR A PASSAGE BETWEEN TWO ARTICULATED VEHICLES OR OF AN AIR PASSENGER STAIRS OR BRIDGE - A bellows for a passage between two articulated vehicles or for an air passenger stair or bridge has a plurality of folds or waves arranged behind one another. A floor region has at least one inner jacket and at least one outer jacket spaced from the inner jacket. An intermediate layer is disposed between and spaced apart from the inner and outer and is fire-retardant. | 2017-10-19 |
20170297639 | TRACTION STUD FOR ENDLESS TRACKS - A traction stud for endless tracks. The traction stud comprises a base and the base has a center point on a top surface and a center point on a bottom surface. There is an elongated shank rigidly surmounted on the top surface at the center point. The shank has a distal end. The distal end has at least one cutting flute located in it. The shank has a threaded surface. The base has, at the center point of the bottom, a means for torqueing the traction stud. | 2017-10-19 |
20170297640 | MOTORCYCLE KICKSTAND PAD - A kickstand pad is configured to provide a surface on the ground on which a kickstand of a motorcycle rests to increase the motorcycle's stability when the motorcycle is parked. The kickstand pad includes a support pad, a tether, and a hook or clip. The support pad increases the amount of level surface area on which a free end of the kickstand can rest to avoid the kickstand embedding or piercing itself into the ground or soft pavement when the motorcycle is parked, which can result in a dangerous and/or damaging fall of the motorcycle. The support pad includes notches or winding features that facilitate storage of the tether when the kickstand pad is not in use. The tether may also serve as a visual reminder to the motorcycle operator to pick up the kickstand pad before driving away. | 2017-10-19 |
20170297641 | SADDLE ADJUSTMENT SYSTEM - A saddle adjustment assembly comprising an adjustable height saddle post, the adjustable height saddle post comprising a first support and a second support, the second support configured to slidably move relative to the first support between at least a raised position and a lowered position, the first support configured to attach to a bicycle frame; a saddle angle adjustment mechanism coupled to the second support, the saddle angle adjustment mechanism comprising a rotatably coupled saddle support configured to couple to a bicycle saddle; wherein the saddle angle adjustment mechanism is configured to enable rotation of the saddle support relative to the second support as a result of the first support moving relative to the second support. | 2017-10-19 |
20170297642 | LEATHER BICYCLE SADDLE - A leather bicycle saddle includes a leather cover, an arc support supporting the leather cover and having a front end terminating in a head abutment portion and a rear end affixed to a rear bottom side of the leather cover, and an adjustment device including a screw bolt holder affixed to a front bottom side of the leather cover, an adjustment screw bolt abutted against the screw bolt holder. The adjustment seat includes a seat block defining a mounting slot and a screw hole, and a stop block. The stop block is engaged into the open end of the mounting slot and stopped at the head abutment portion of the arc support against the close end of the mounting slot. The screw hole of the seat block receives the adjustment screw bolt. | 2017-10-19 |
20170297643 | Seat Connecting Device - A seat connecting device includes a first base unit for coupling with a bicycle seat and a second base unit. The first base unit includes an extension having a first end portion with first teeth and a connecting portion. The second base unit includes a body and a connecting member. The body includes a second end portion with second teeth and a sliding groove extending through the second end portion. The connecting member extends through the sliding groove and is detachably connected to the connecting portion. The connecting member selectively presses against a side of the second end portion distant to the second teeth. The second teeth disengageably engages with the first teeth. A water bottle holder can be mounted to the body. | 2017-10-19 |
20170297644 | SYSTEMS AND METHODS FOR A HANDLEBAR INTERCONNECTOR - A handlebar mount includes a first side body and a second side body; and a central body, the central body interconnecting the first and second side bodies. The handlebar mount further includes a first elastic portion and a second elastic portion, oriented on the first and second side bodies, respectively. The handlebar mount further includes a first hook and a second hook, the first and second hooks oriented to receive the first and second elastic portions, respectively, and hold them securely. | 2017-10-19 |
20170297645 | VEHICLE WITH A SLOPING STEERING COLUMN - The invention relates to a vehicle ( | 2017-10-19 |
20170297646 | SCOOTER WITH MOVABLE PORTION - A personal mobility vehicle, such as a scooter, includes a plurality of wheels supporting a deck or other vehicle body portion. The vehicle has a movable portion that is movable relative to another portion of the vehicle. A motion transfer mechanism is operably coupled to the movable portion and causes movement of the movable portion in response to movement of the vehicle. | 2017-10-19 |
20170297647 | BICYCLE FRAME WITH A HIDDEN BATTERY PACK - A bicycle frame with a hidden battery pack has a tube member and a battery pack. The tube member is hollow and has a peripheral surface, a receiving space, and a replacement opening. The receiving space is formed inside the tube member. The replacement opening is defined in the peripheral surface of the tube member and communicates with the receiving space. The battery pack is mounted in the receiving space and has multiple batteries. Each two adjacent batteries of the multiple batteries are connected to each other and are able to rotate relative to each other. Each battery of the multiple batteries is capable of being rotated or swung to pass through the replacement opening. | 2017-10-19 |
20170297648 | Human-Propellable Vehicle - A human-propellable vehicle is described and comprises a chassis and a roller assembly mounted at or towards the rear of the chassis. The roller assembly is positioned to engage with a wheel of a second vehicle to permit the second vehicle to push the human-propellable vehicle. | 2017-10-19 |
20170297649 | BICYCLE CRANK ASSEMBLY - A bicycle crank assembly has a rotational center axis and comprises a crank member, a sprocket member, a sliding mechanism, a first stopper member, a second stopper member and a damping member. The crank member rotatably is arranged around the rotational center axis. The sprocket member is integrally and rotatably attached to the crank member. The sliding mechanism movably coupling the sprocket member in an axial direction with respect to the crank member. The first stopper member is attached to the crank member. The second stopper member is attached to the sprocket member. The damping member is attached to at least one of the first stopper member and the second stopper member. The damping member is configured to contact the other of the first stopper member and the second stopper member while the sliding mechanism is in operation. | 2017-10-19 |
20170297650 | BICYCLE PEDAL ADJUSTABLY CONFIGURED FOR USE WITH MULTIPLE SHOE CLEATS - A bicycle pedal adapted for use with a plurality of different shoe cleats each having a respective cleat configuration. The bicycle pedal includes a front hook adapted to be engageable with a first portion of a shoe cleat, a cleat contact surface coupled to the front hook and adapted to be engageable with a second portion of the shoe cleat, and a rear hook coupled to the cleat contact surface and adapted to be engageable with a third portion of the shoe cleat. The front hook, cleat contact surface, and rear hook define an engagement configuration complimentary to the cleat configuration and are configured such that the engagement configuration is selectively adjustable to conform to the cleat configuration. | 2017-10-19 |
20170297651 | BICYCLE CONTROLLER - A bicycle controller is provided that performs control in accordance with a riding condition of a bicycle. The bicycle controller includes an electronic control unit that controls a motor. The motor assists human power that is inputted to a bicycle. Upon determining a gear changer that changes a gear ratio of the bicycle is operated, the electronic control unit switches a control state of the motor from a first control state to a second control state based on a rotation phase of a crank of the bicycle and changes a timing at which the control state of the motor is switched from the first control state to the second control state based on an inclination of the bicycle in a front-rear direction. | 2017-10-19 |
20170297652 | BATTERY BRACKET FOR USE IN ELECTRICALLY ASSISTED MOVING BODY, BATTERY UNIT, ELECTRICALLY ASSISTED UNIT, AND ELECTRICALLY ASSISTED MOVING BODY - A battery bracket for attaching, to an electrically assisted moving body capable of supplementing a first driving force generated by human power with a second driving force generated by electrical power, and a battery for use in the electrically assisted moving body. This battery bracket includes an extension section extending in a prescribed direction, and a plurality of projection sections projecting from the extension section in a direction intersecting the prescribed direction. The plurality of projection sections are mutually spaced along the prescribed direction. | 2017-10-19 |
20170297653 | SELF-BALANCING VEHICLE WITH GRAVITY CONTROL - A two-wheel, self-balancing vehicle is disclosed. In one aspect, the two-wheel, self-balancing vehicle comprises a first wheel and a second wheel, the first wheel and the second wheel being spaced apart and substantially parallel to one another. The two-wheel, self-balancing vehicle further comprises a foot placement section connecting the first wheel and the second wheel. The two-wheel, self-balancing vehicle further comprises a set of position sensors in the foot placement section, the set of position sensors configured to generate inclination angle signals and velocity signals of the two-wheel, self-balancing vehicle. The two-wheel, self-balancing vehicle further comprises a first gravity sensor and a second gravity sensor in the foot placement section, the first gravity sensor and the second gravity sensor configured to generate weight signals and gravity angle signals. In addition, the two-wheel, self-balancing vehicle comprises a control logic configured to output control signals that control the movement of the two-wheel, self-balancing vehicle in response to the inclination angle signals, the velocity signals, the weight signals, and the gravity angle signals. | 2017-10-19 |
20170297654 | SELF-SUPPORTING BIMINI TOP - A self-supporting bimini top frame is independently supportable on four contact points. A main bow defines a first support member for a bimini top connectable to the bimini top frame. The main bow defines first and second contact points. A pair of stanchions are pivotably connected to the main bow and define third and fourth contact points. A primary tension bow is pivotably and slidably connected to the main bow and defines a second support member for the bimini top. A bimini top may also be secured on the bimini top frame. | 2017-10-19 |
20170297655 | RELEASE APPARATUS LOCKING SYSTEMS AND METHODS - Some embodiments provide ocean rig releases apparatus, systems and methods. In some implementations, a rig release apparatus comprises: a body having a first and second mating sections each being connected to one of two separate tethers; at least one locking shoe movably secured with the first mating section and movable between a first position configured to secure the first mating section and the second mating section together and a second position configured to allow the first mating section and the second mating section to separate; and a locking system configured to releasably lock the first and second mating sections and prevent hydrostatic pressure created by ocean depths from inadvertently unlocking, wherein the locking system comprises: a restraint system that inhibits the movement of the at least one locking shoe, and comprises a stop element that when released physically retracts to unlock the locking system allowing. | 2017-10-19 |
20170297656 | Rope Clasp - A rope clasp device for securing a rope eliminates the need for a knot in a rope by selectively clasping and encasing at least one portion of a rope in a toothed clamp. The rope clasp device comprises a base, at least one, but generally two swinging doors, and a lock. The swinging doors are pivotably coupled to the base in order to be moved between an open position and a closed position. In the closed position, a pair of channels for passage of a rope is defined between the base and the doors. The channels are defined by a plurality of clasping teeth to retain the rope therein. | 2017-10-19 |
20170297657 | FAIRLEAD INTENDED TO ENGAGE WITH AN ANCHOR CHAIN, FOR A SYSTEM FOR ANCHORING A FLOATING INSTALLATION TO THE GROUND - Disclosed is a fairlead intended to engage with an anchor chain, for a system for anchoring a floating installation to the ground. The fairlead includes two structures assembled by pivot connection of axis, one upstream, for rigidly connecting the fairlead to the floating installation, and the other downstream, including—a unit for blocking the translational movement of the anchor chain, and—a guide, for guiding a change in direction of the anchor chain. Furthermore, the downstream structure includes two lateral plates delimiting the passage of the chain, the upstream end of each of the plates including a U-shaped bearing receiving an additional arm of the upstream structure and engaging together via a journal, the guide extending between the internal branches of the two bearings. | 2017-10-19 |
20170297658 | WATERCRAFT SECUREMENT DEVICE - A watercraft securement device including a boat attachment line configured for connection to a watercraft and a dock attachment line configured for connection to an anchoring structure. A tensioning apparatus is connected to the boat attachment line and the dock attachment line. The tensioning apparatus is configured to adjust the length of one of the boat attachment line or the dock attachment line. The tensioning apparatus further includes a pulley for engaging the adjustable length and a ratcheting mechanism. The ratcheting mechanism operates to permit rotation of the pulley in only one direction when engaged, and to permit free rotation of the pulley when released. The ratcheting mechanism maintains tension as the adjustable length is pulled through the pulley. | 2017-10-19 |
20170297659 | HYDRAULIC DEVICE FOR CONTROLLING THE DEPTH OF AN IMMERSIBLE OBJECT - A hydraulic depth-control device for a submersible body comprises: | 2017-10-19 |
20170297660 | SEAT AND SEAT BACK ASSEMBLY - A seat and seat back assembly includes a seat back moveable between an upright position and a horizontal position. A support panel is connected to the seat back for pivoting movement of the support panel between a first position supporting the seat back upright, and a second position wherein the seat back is moveable into the horizontal position. A biasing mechanism serves to urge the support panel into the first position when the seat back is moved into an upright position. When the support panel is moved into the second position this allows the seat back assembly to move into the horizontal position without dropping unrestricted. | 2017-10-19 |
20170297661 | POWERED SURFBOARD FOR PRESERVING ENERGY OF A SURFER DURING PADDLING - An improvement to a conventional surfboard includes an impeller and an electric motor contained primarily within the body of the surfboard, whereby performance of the surfboard is substantially unaffected by the presence of the impeller and the electric motor. The electric motor is operatively connected to the impeller for providing a forward thrust of the surfboard. The improvement to the conventional surfboard also includes a throttle for selective control of the electric motor for operating the impeller to provide a forward thrust of the surfboard, the throttle being configured for use by a surfer lying in a prone position on the smooth top surface of the body of the surfboard. An extent of the surfer's energy that otherwise would be expended during paddling can be preserved for riding waves by using the impeller to provide the forward thrust during paddling. | 2017-10-19 |
20170297662 | FRONT LINE KITE DEPOWER SYSTEM - A front flying line kite depower system includes a line sheath that extends through a transverse opening in the control bar. A front flying line parting fitting is non-rotatably fixed to an upper end of the line sheath above the control bar. When a manual rotation force is imparted to the line sheath, the relative positioning of a first front flying line and a second front flying line is altered by the front flying line parting fitting to untangle any twisting above the line sheath. Within the line sheath, the second front flying line is off-set from a primary axis and orbits the first front flying line which is positioned on the primary axis to avoid any tangling during manual adjustment. | 2017-10-19 |
20170297663 | DEVICE AND METHOD FOR A STRUCTURE SUBJECT TO OSCILLATING MOVEMENTS - Device for a structure designed to tilt from one side to the opposite side, with the device comprising:
| 2017-10-19 |
20170297664 | Floatation Device - A floatation device for use by an individual in a body of water, comprising of an upper body covering and two fabric covered inflatable sleeve elements. The upper body covering contains multiple gussets that hide the male or female end of a clasp device. The fabric covered inflatable sleeves contain the opposite end of the clasp device which allow them to be securely fastened to the upper body covering in one or more locations. | 2017-10-19 |
20170297665 | SEMI-CLOSED CIRCUIT UNDERWATER BREATHING APPARATUS RATIO REGULATOR - An apparatus for adjusting the partial pressure of gaseous mixtures comprises a housing and piston. The housing defines a chamber coupled to an oxygen metering orifice, diluent metering orifice, vent port and gas outlet. The oxygen metering orifice provides oxygen to the chamber and the diluent metering orifice provides diluent gas to the chamber. The piston is movably positioned in the chamber and includes first and second sealing devices. The chamber is sectioned into a mixing chamber, a diluent chamber and a reference chamber located between the mixing chamber and diluent chamber. The diluent chamber receives a diluent gas referenced at ambient pressure and the reference chamber is charged with a gas having a reference pressure. The piston changes positions within the chamber depending on a force balance created by a pressure differential between the reference pressure and ambient pressure. | 2017-10-19 |
20170297666 | SYSTEM AND METHOD FOR MARINE SURVEY PAYLOAD DELIVERY - An apparatus. The apparatus includes a body and a plurality of control surfaces attached to the body. A first control surface is configured to control an ascent and descent of the apparatus, responsive to ascent/descent control information. A second control surface is configured to control a roll of the apparatus responsive to roll control information, and a third control surface is configured to control a yaw of the apparatus responsive to yaw control information. The apparatus further includes a releasable first docking fixture attached to the body, the first docking fixture configured to engage a second docking fixture on a payload. | 2017-10-19 |
20170297667 | POSITIVELY BUOYANT, VERTICAL THRUST, MANNED SUBMERSIBLE - The present invention is directed towards a fixed positively buoyant manned submersible that includes a plurality of vertical thrusters and a sealed enclosure(s) that can support one or more human passengers. The vertical thrusters can include vertically aligned propellers that are coupled to motors that control the rotational velocity of the propellers. The vertical thrusters to generate a negative vertical thrust to allow the submersible to dive within a body of water. Horizontal movement can be achieved through horizontal thrusters or directing the thrust vectoring of the vertical thrusters. | 2017-10-19 |
20170297668 | SYSTEMS AND METHODS FOR AUTOMATICALLY CONTROLLING ATTITUDE OF A MARINE VESSEL WITH TRIM DEVICES - A trim control system automatically controls trim angle of a marine propulsion device with respect to a vessel. A memory stores trim base profiles, each defining a unique relationship between vessel speed and trim angle. An input device allows selection of a base profile to specify an aggressiveness of trim angle versus vessel speed, and then optionally to further refine the aggressiveness. A controller then determines a setpoint trim angle based on a measured vessel speed. If the user has not chosen to refine the aggressiveness, the controller determines the setpoint trim angle from the selected base profile. However, if the user has chosen to refine the aggressiveness, the controller determines the setpoint trim angle from a trim sub-profile, which defines a variant of the relationship between vessel speed and trim angle defined by the selected base profile. The control system positions the propulsion device at the setpoint trim angle. | 2017-10-19 |
20170297669 | MOTORIZED WATERCRAFT SYSTEM WITH INTERCHANGEABLE MOTOR MODULE - A personal watercraft body comprises a recess configured to receive similarly shaped cassettes. A first cassette may be motorized to propel the body relative to a body of water. A second cassette may be non-motorized and may include a storage space therein for storing personal items. An insert may be disposed between the cassettes and the recess to orient and fit the cassettes within the body. | 2017-10-19 |
20170297670 | NOVEL MARINE VEHICLE ENGINE - A marine vessel engine in which moving parts found in conventional marine engines are eliminated, wherein such engine is used for the propulsion of marine vessels. In the marine vessel engine, no lubrication or cooling is required, and a column of water replaces the conventional piston in a cylinder of the engine, wherein such water column partially fills such cylinder. The marine vessel engine comprises a cylinder, a bent tube with a plurality of openings and two ends, a flapping member, at least one solenoid valve, and an exhaust. In operation of the marine vessel engine, a column of water fills the cylinder through the bent tube openings, and is purged outside from the cylinder through the flapping member. The at least one solenoid valve controls the flow of a power source into the cylinder. | 2017-10-19 |
20170297671 | Adjustable Debris Collection Apparatus For Maritime Vessels And Associated Methods - A debris collection apparatus for a maritime vessel includes a shroud and a plurality of support structures. Each of the plurality support structures include a boot defining a cavity and configured to be secured to the vessel, a foot sized to fit within the cavity, a staff cap, a stabilizer base configured to be secured to the vessel, an elevational staff section connected to the foot and the staff cap terminal, and a horizontal staff section connected to the staff cap and the stabilizer base. The foot is inserted into the boot to secure the support structures in a rigid position, and the shroud is connected to both staff caps and the vessel. The stabilizer base can include a connection loop, and the shroud can be configured to be connected to the connection loop in order to connect the shroud to the vessel. | 2017-10-19 |
20170297672 | SYSTEMS AND METHODS FOR LONG ENDURANCE AIRSHIP OPERATIONS - In one example, a long endurance airship system includes a first combined airship with a payload airship and a first logistics airship. The first combined airship is configured for stationkeeping at a predetermined station during meteorological conditions with wind speeds below a predetermined threshold. The airship system also includes a second combined airship which is a reconfiguration of the first combined airship and includes the payload airship and a second logistics airship. The second combined airship is configured for stationkeeping at the predetermined station in all meteorological conditions, including meteorological conditions with wind speeds above the predetermined threshold. | 2017-10-19 |
20170297673 | HIGH STRENGTH AEROSPACE COMPONENTS - An article that includes a structured substrate having a macro-porous structure that defines a plurality of pores, and a metallic nano-crystalline coating on at least a portion of the structured substrate, where the metallic nano-crystalline coating defines an average grain size less than about 20 nanometers. | 2017-10-19 |
20170297674 | FIBRE-REINFORCED METAL COMPONENT FOR AN AIRCRAFT OR SPACECRAFT AND PRODUCTION METHODS FOR FIBRE-REINFORCED METAL COMPONENTS - Production methods for producing a fibre-reinforced metal component having a metal matrix which is penetrated by a plurality of reinforcing fibres are provided. One method includes depositing in layers reinforcing fibres in fibre layers, depositing in layers and liquefying a metal modelling material in matrix material layers, and consolidating in layers the metal modelling material in adjacently deposited matrix material layers to form the metal matrix of the fibre-reinforced metal component. Here, the metal component is formed integrally from alternately deposited matrix material layers and fibre layers. An alternative method includes introducing an open three-dimensional fibrewoven fabric consisting of reinforcing fibres into a casting mould, pouring a liquid metal modelling material into the casting mould and consolidating the metal modelling material to form the metal matrix of the fibre-reinforced metal component. Here, the metal component is formed integrally from the consolidated metal modelling material and the reinforcing fibres. | 2017-10-19 |
20170297675 | HELICOPTER WITH A FUSELAGE AND A COMPOSITE TAIL BOOM - A helicopter with a fuselage and a composite tail boom. The composite tail boom has at least a tubular tail boom cone and a composite attachment ring segment that defines a mating face which is connected to the fuselage at an associated connection interface by means of a plurality of tension members that are oriented longitudinally with respect to a longitudinal extension direction of the composite tail boom. The plurality of tension members are distributed over a perimeter of the composite attachment ring segment | 2017-10-19 |
20170297676 | HAT SECTION DOOR FRAME WITH INTEGRAL GUSSETS - A door frame for an aircraft includes first and second beams, each having a first end and a second end. The second beam is substantially parallel to the first beam. A third beam extends from the first end of the first beam to the first end of the second beam. The third beam is substantially perpendicular to the first beam and the second beam. A first flange extends from the second end of the first beam in a direction that is away from the second beam. The first flange is substantially perpendicular to the first beam. | 2017-10-19 |
20170297677 | PROPELLER ASSEMBLY WITH AT LEAST TWO PROPELLER BLADES - A propeller assembly with at least two propeller blades that are interconnected by associated connection means, the associated connection means defining a common pitch axis for the at least two propeller blades in operation, each one of the at least two propeller blades comprising associated leading and trailing edges that define a respective chord and quarter chord line thereof, wherein the common pitch axis is arranged with a predetermined offset relative to the quarter chord line of each one of the at least two propeller blades, and wherein the associated connection means is adapted to enable, at least in operation in a non-axial inflow field, a passive pitch adjustment of the at least two propeller blades around the common pitch axis. | 2017-10-19 |
20170297678 | BLADE FOLD SYSTEM USING FLAP HINGE - A rotor system of a tail-sitter aerial vehicle configured to rotate about an axis of rotation is provided including a rotor hub which rotates about the axis of rotation and at least one rotor blade operably coupled to the rotor hub. The at least one rotor blade is configured to rotate about a folding axis between an extended position where the at least one rotor blade is substantially within a plane perpendicular to the axis of rotation and a stowed position where the rotor blade is arranged out of the plane of at an angle less than ninety degrees to the axis of rotation. | 2017-10-19 |
20170297679 | Interconnect Drive System - An interconnect drive system for an aircraft has a driveline and clutch control system. The driveline comprises a shaft for each propulsion assembly, each shaft for transferring torque to and from the associated propulsion assembly, and a clutch operably coupling the shafts and configured for selective engagement. The clutch is capable of transferring a first amount of torque between the shafts while engaged and a second amount of torque between the shafts while disengaged. The system also has a clutch control system, comprising a computer operably connected to the clutch for controlling operation of the clutch and sensors for sensing torque applied to the driveline, output from the sensors being communicated to the computer. The computer commands operation of the clutch in response to the output from the sensors, the clutch being commanded to disengage to relieve a transient torque imbalance in the driveline. | 2017-10-19 |
20170297680 | Thermally Controlled Active Flow Control System - A method and apparatus are presented. An active flow control system comprises a flow control valve, a manifold, and a temperature control system. The flow control valve is configured to control a flow of air into the manifold. The manifold is operatively connected to a number of actuators. The temperature control system is configured to heat at least a portion of the flow of air. | 2017-10-19 |
20170297681 | FLYING MACHINE, METHOD FOR USING FLYING MACHINE, AND FLYING MACHINE FRAME - A flying machine includes a flying machine body including a rotor blade; a frame including a frame body supporting the flying machine body, and a pressing section that is pressed against a target object at least at two locations separated along a direction orthogonal to a width direction of the frame body; and a detector fixed to the frame, and having a detection direction that is a direction orthogonal to a direction joining the two locations together and facing toward the target object. | 2017-10-19 |
20170297682 | Emergency Landing Stability System for Aircraft - An aircraft emergency landing stability system includes an aircraft a fuselage and landing gear, and a landing stability apparatus coupled to the fuselage, wherein the landing stability structure mitigates a nose-down pitching moment of the aircraft created in response to contact with a landing surface during an emergency landing. | 2017-10-19 |
20170297683 | NOSE GEAR STEERING APPARATUS FOR SHIPBOARD OPERATIONS - A steering assembly includes a movable anchor. Movement of the anchor in a first direction is restricted. A first linkage is coupled to the anchor and a second linkage it rotatably coupled to the first linkage. The second linkage is configured to couple to a contactor. A drive mechanism moves the second linkage relative to the first linkage. At least one of moving the second linkage and moving the anchor maneuvers the contactor to a desired position. | 2017-10-19 |
20170297684 | ACTIVE LANDING GEAR DAMPER - An active landing gear damping system and method for decelerating a vehicle during a terrain impact event, such as an aircraft landing or crash. The system monitors aircraft state data and terrain information to predict an impact of the vehicle with the terrain. The system can then determine a target damper force for each landing gear of the vehicle and a predicted damper velocity at the time of impact. Each landing gear can include an adjustable damper valve, wherein adjustment of the damper valves varies the damping coefficient of the respective dampers. The system can adjust valves of the respective dampers to provide the target force based on the predicted damper velocity. After an impact begins, the system can continuously monitor and adjust the valve to maintain the target force. | 2017-10-19 |
20170297685 | Rotor Hub Vibration Attenuator - A vibration attenuator for an aircraft has at least one weight mounted in a rotating system of a rotor hub of the aircraft, each weight being rotatable about an axis of rotation of the hub relative to the hub and to each other weight. Drive means are provided for rotating each weight about the axis of rotation at a selected speed for creating oscillatory shear forces that oppose and attenuate rotor-induced vibrations having a selected frequency. A vertically oriented vibration attenuator is configured to oppose and attenuate vertical rotor induced oscillatory forces that would otherwise travel vertical down the rotor mast and into the airframe. A vibration attenuator having weights rotating about separate axes offset from each other. | 2017-10-19 |
20170297686 | ANTI-VIBRATION MOMENT GENERATING AIRCRAFT ACTUATION SYSTEM - An aircraft is provided and includes an airframe, an engine, a drive portion driven by the engine, a rotor apparatus, which includes a rotor rotatable relative to the airframe and a fairing, a gearbox disposed to transmit rotational energy from the drive portion to the rotor to drive the rotor to rotate relative to the airframe and which generates a rotor rotation vibration, support members by which the gearbox is disposed on the airframe and an actuation system including actuation elements disposed at the fairing, the actuation system being configured to generate an anti-vibration moment using the actuation elements disposed at the fairing to counter the rotor rotation vibration. | 2017-10-19 |
20170297687 | Tandem Rigid Rotor System and Method - A tandem rigid rotor system has a first rigid rotor system and a second rigid rotor system connected by a fuselage. The fuselage has at least one framing member connected between the first rigid rotor system and the second rigid rotor system, such that the framing member is torsionally flexible for controlling yaw of the tandem rigid rotor system. In certain embodiments, multiple framing members are connected between the first rigid rotor system and the second rigid rotor system in parallel. In certain embodiments, the torsional flexibility allows up to 20 degrees of movement away from the lateral axis. In certain embodiments, framing members are vertically and laterally rigid. | 2017-10-19 |
20170297688 | INTEGRATED MAIN ROTOR HUB AND SHAFT - A main rotor system for a rotary wing aircraft is provided including a lower rotor hub to which lower rotor blades are attachable. The lower rotor hub rotates about an axis in a first direction. A hollow rotor shaft extends through the lower rotor hub. The first end of the rotor shaft couples to a component of the rotary wing aircraft for rotation about an axis. An upper rotor hub arranged at the second end of the rotor shaft includes a plurality of similar upper rotor members equidistantly spaced about a circumference of the rotor shaft to form an open center aligned with a hollow interior of the rotor shaft. An opening configured to receive an upper rotor blade is formed between adjacent upper rotor members and the upper rotor hub is configured to rotate in a second direction, opposite the first direction. | 2017-10-19 |
20170297689 | ELECTRIC PROPULSION SYSTEM FOR A ROTARY WING AIRCRAFT - A rotary wing aircraft includes an airframe, a stationary mast fixedly engaged to the airframe and extending along a first axis, and an electric motor. The electric motor includes a stator assembly engaged to the mast and a rotor assembly disposed radially outward from the stator assembly and configured to rotate with respect to the stator assembly. A plurality of rotor blades project radially outward from the rotor assembly. | 2017-10-19 |
20170297690 | HUB SEPARATION IN DUAL ROTOR ROTARY WING AIRCRAFT - An aircraft includes an airframe; an extending tail; a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly; and a translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe; wherein a ratio of (i) the hub separation between the hub of the upper rotor assembly and the hub of the lower rotor assembly to (ii) a radius of the upper rotor assembly is between about 0.1 and about 0.135. | 2017-10-19 |
20170297691 | CYLINDRICAL ELASTOMERIC BEARING WITH TAPERED SHIMS - A cylindrical elastomeric bearing including a plurality of elastomeric layers arranged about a central bore. The elastomeric layers are characterized by a middle portion having a first thickness and two outer portions having a second thickness, the second thickness being greater than the first thickness, the one or more elastomeric layers being tapered between the middle portion and the outer portions. One or more shim layers, each of the plurality of shim layers being arranged between two of the plurality of elastomeric layers. The shim layers are shaped to fit with the elastomer layers. | 2017-10-19 |
20170297692 | ROTARY WING AIRCRAFT - A rotary wing aircraft includes an airframe, one or more engines supported by the airframe, and a plurality of rotor blades operatively connected to the one or more engines. Each of the plurality of rotor blades includes a rotor lift-to-drag (L/De) ratio greater than 9 at airspeeds between about 150 KTAS and about 210 KTAS, and the rotary wing aircraft includes an aircraft lift-to drag (L/D) ratio of greater than about 4 between about 99 KTAS and about 210 KTAS. | 2017-10-19 |
20170297693 | FEED-FORWARD COMPENSATION FOR GYROSCOPIC LOADS IN A COAXIAL ROTOR - A system and method for counteracting a rotor moment of one or more rotors of a coaxial rotor helicopter includes receiving signals with a processor indicative of a displacement command from a controller during a flight maneuver; receiving one or more signals with the processor from a sensor indicative of an airspeed and air density for the helicopter; determining a commanded rate of acceleration for the helicopter during the flight maneuver; and adjusting with one or more control servos a cyclic pitch for the one or more rotors to counteract the rotor moment during the flight maneuver. | 2017-10-19 |
20170297694 | ROTOR SPEED MANAGEMENT - A flight control system for a rotorcraft includes a controller configured to receive input indicative of ambient conditions, determine a threshold rotor blade tip speed based on the input, and to output rotor control commands to prevent rotor blade tips from exceeding the threshold speed. An aircraft includes an airframe, a main rotor assembly operatively connected to the airframe, and a flight control system as described above. The flight control system is operatively connected to control the main rotor assembly. It is contemplated that the main rotor assembly can be a counter rotating coaxial main rotor assembly including an upper rotor assembly with a plurality of blades and a lower rotor assembly having a plurality of blades, wherein the flight control system is operatively connected to control both upper and lower rotor assemblies to prevent any blade tips of the upper and lower rotor assemblies from exceeding the threshold speed. | 2017-10-19 |
20170297695 | SYSTEM AND METHOD FOR ASSISTING IN ROTOR SPEED CONTROL - A method of assisting in rotor speed control in a rotorcraft can include measuring a rotor speed with a sensor; detecting a droop in the rotor speed beyond a lower droop limit; and commanding a decrease in collective in response to the rotor speed drooping beyond the lower droop limit. A system of assisting in rotor speed control in a rotorcraft, the system can include: a computer having a control law, the control law operable to generate a decrease collective command to an actuator in response to a rotor speed decreasing below a lower droop limit; wherein the lower droop limit is below a normal lower rotor speed range. | 2017-10-19 |
20170297696 | AIRCRAFT MAIN ROTOR DRAG TO AIRFRAME DRAG - An aircraft includes an airframe having an extending tail and a counter rotating, coaxial main rotor assembly disposed at the airframe including an upper rotor assembly and a lower rotor assembly. A translational thrust system is positioned at the extending tail and provides translational thrust to the airframe. An airframe parasitic drag of the airframe is greater than a main rotor assembly drag of the main rotor assembly. An aircraft includes an airframe having an extending tail and a counter rotating, coaxial main rotor assembly disposed at the airframe including an upper rotor assembly and a lower rotor assembly. A translational thrust system is positioned at the extending tail and provides translational thrust to the airframe. A main rotor assembly drag is at or between about 25% and 40% of a total aircraft drag. | 2017-10-19 |
20170297697 | ROTORCRAFT CONFIGURATION AND METHOD OF ROTORCRAFT DESIGN - A rotorcraft is provided and includes a fuselage. The fuselage includes drag generating portions, a main rotor assembly and an auxiliary propulsor having an expected propulsion efficiency. The auxiliary propulsor is disposed to ingest boundary layer flows and in wake regions associated with the drag generating portions and is provided with a corresponding increase in the expected propulsion efficiency thereof. | 2017-10-19 |
20170297698 | TILTWING AIRCRAFT - An aircraft includes a fuselage defining an aircraft attitude axis. The fuselage houses an engine fixed relative to the aircraft attitude axis. A rotor assembly is operatively connected to rotate back and forth relative to the aircraft attitude axis from a first position predominately for lift to a second position predominately for thrust. The rotor assembly includes a rotor that is operatively connected to be driven by the engine. | 2017-10-19 |
20170297699 | QUAD ROTOR TAIL-SITTER AIRCRAFT WITH ROTOR BLOWN WING (RBW) CONFIGURATION - A tail-sitter aircraft is provided and includes a fuselage having first and second axisymmetric sides, first collectively controllable prop-rotors, which are formed to define a first pair of rotor disks and which are respectively supported at the first axisymmetric side of the fuselage, and second collectively controllable prop-rotors, which are formed to define a second pair of rotor disks and which are respectively supported at the second axisymmetric side of the fuselage. | 2017-10-19 |
20170297700 | VERTICAL TAKE OFF AIRCRAFT - An aircraft includes a fuselage, a wing, a ducted fan and a controller. The wing and the ducted fan are coupled to the fuselage. The controller is operable to control the aircraft in a vertical flight mode, a horizontal flight mode, and transition the aircraft from the vertical flight mode to the horizontal flight mode. | 2017-10-19 |
20170297701 | KITE WITH CONTROLLABLE TRAILING EDGE - A kite comprises: a wing; upper and lower flaps located along at least a portion of an edge of the wing that forms the trailing edge of the wing when the wing is active; a controller configured to generate control signals; and an actuator arrangement configured to change orientations of the upper and lower flaps relative to the wing based on the control signals generated by the controller. | 2017-10-19 |
20170297702 | VIBRATION CONTROL METHOD FOR FLAPPING-WING MICRO AIR VEHICLES - The present invention provides a method for controlling the oscillation of flapping-wing air vehicle, which comprises the following steps: calculating the kinetic energy, potential energy and virtual work of the system using the flexible wing with the two-degree of freedom as the research object; establishing system dynamics model based on the Hamilton's principle; setting the boundary control rate according to said system dynamics model wherein said boundary control rate includes F(t) and M(t), said F(t) is the inputted boundary control force, and said M(t) is the inputted boundary torque; and controlling the flexible wings according to the system dynamics model in combination with the boundary control rate. The present invention establishes the system dynamics model based on the Hamilton's principle, set the boundary control rate according to said system dynamics model, sufficiently considers the situation of distributed disturbance occurring at the boundary and effectively prevents the flexible wings deformation caused by the external disturbances. | 2017-10-19 |
20170297703 | ELECTRONIC SPEED CONTROLLER ARM FOR VEHICLE - According to various embodiments, an unmanned aerial vehicle (UAV) is provided. The UAV may include a motor controller. The UAV may further include a motor connected to the motor controller. The UAV may further include an arm connected between the motor controller and the motor. The UAV may further include a plurality of electronic speed control components integrated within the arm, the electronic speed control components configured to control the speed of the motor. | 2017-10-19 |
20170297704 | Remote Controlled Aircraft - A remote controlled aircraft includes an aircraft that may be flown. A plurality of light emitters is coupled to the aircraft. A plurality of fans is coupled to the aircraft. Each of the fans may move air thereby facilitating each of the fans to urge the aircraft to fly. A control unit is coupled to the aircraft and the control unit is electrically coupled to each of the fans. The control unit includes a global positioning system. Thus, the control unit may identify a position of the aircraft with respect to Earth. A remote control is provided and the remote control may be manipulated. The remote control is in electrical communication with the control unit such that the remote control controls directional flight of the aircraft. | 2017-10-19 |
20170297705 | Multi-Rotor Aircraft Control - Flight control method and apparatus for multi-rotor aircraft that is programmed for varied control commands and conditions in the control of the aircraft in flight. | 2017-10-19 |
20170297706 | HAND-LAUNCHED UNMANNED AERIAL VEHICLE - The invention discloses a hand-launched unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. The hand-launched unmanned aerial vehicle comprises a body, a tail, at least one power source and a lens bin, wherein the body comprises a middle section, a first side section and a second side section; two sides of the middle section are respectively detachably connected with the first side section and the second side section correspondingly; the tail is fixed to the middle section; the power source is fixed to the middle section; and the lens bin is fixed to the middle section and provided with a flexible cushion. The invention overcomes the technical defects in the prior art that the body maintenance cost of the hand-launched unmanned aerial vehicle is high and the lens bin is very likely to be damaged due to collision between the lens bin of the hand-launched unmanned aerial vehicle and the ground. | 2017-10-19 |
20170297707 | UNMANNED AIRCRAFT SYSTEM (UAS) WITH ACTIVE ENERGY HARVESTING AND POWER MANAGEMENT - A method of harvesting and managing energy from air currents, by small unmanned aircraft systems (UAS) having a plurality of powered and unpowered rotors, to increase the aircraft's flight time, especially where the mission requires extensive hovering and loitering, is provided. Conventional powered rotors create lift for the aircraft. Unpowered rotors can either be: 1) Free-wheeling rotors which increase the plan form area of aircraft as they rotate, increasing lift, and reducing the power draw on the battery, and/or 2) Rotors connected to micro-generators, which serve as a brake on the unpowered rotors, create electrical power to charge the aircraft batteries or directly power the aircraft's electronics. The invention's folding rotor arm design results in a compact package that is easily transported by a single user (man portable). The aircraft can be removed from its protective tube, unfolded and launched for flight in less than a minute. Extended flight times, compact easily transported design, and ability to host flight software on a user's tablet/PC result in low total cost of ownership. | 2017-10-19 |
20170297708 | Methods for improvements of the box wing aircraft concept and corresponding aircraft configuration - Aircraft configuration by applying the following method steps for improving the conventional box wing aircraft concept: dividing both the backward swept front and the forward swept rear wings into root and tip sections, wherein the tip sections ( | 2017-10-19 |
20170297709 | MULTI- MODULAR AERIAL FIREFIGHTING CONTROL METHOD AND APPARATUS - A multi-modular aerial firefighting control method and apparatus for use by firefighters to control fire. The multi-modular aerial firefighting control method and apparatus generally includes multi-modular units that are held together to form an aerial firefighting system. The modular units may work together or independently. The multi-modular system comprises more than one modular unit, fluid, fluid conduit, reservoir, air flow generator, multi-modular unit support structure, aerial suspension system and aerial lift system. | 2017-10-19 |
20170297710 | METHOD AND APPARATUS FOR ARTIFICIAL DISTRIBUTION OF INSECTS OR SPRAY - A diffuser for distributing spray or insects from an aircraft is mounted on an aircraft and comprises a distribution tube connected to an insect source at a first end and open to the outside at a second end for distribution of the insects. A nozzle surrounds the second end and a tube cover surrounds the second end within the nozzle. The tube cover has an aerofoil, or wing-shaped, cross section. The nozzle shape sets up an air transition volume between the aircraft and ambient air designed for a maximum wind shear over any cubic centimeter volume within the air transition volume to be less than 60 km/h, and therefore allowing distribution of insects such as mosquitoes from the aircraft without damage, or allowing aerosols to be spread as large droplets. | 2017-10-19 |
20170297711 | UAV CAPTURE OF MICRO CARGO ALOFT - A system of transporting micro-cargo incorporates an unmanned aerial vehicle (UAV) having a tether capture device. A tether is connected to and suspends a micro cargo container with a suspension system to vertically extend the tether. The system having a first pickup state and a second flight state with a transition between the first and second states. The first state provides the micro-container unsuspended via the tether from the suspension system. The transition state provides engagement of the tether by the UAV, the tether positioning the micro-cargo container with respect to the capture device which secures the tether. The second state is then entered with the micro-cargo towed by the UAV in cruising flight to its destination. | 2017-10-19 |
20170297712 | SMALL UAVS WITH RADAR RECEIVERS TO BE USED AS BISTATIC RADAR LAUNCHED FROM TACTICAL FIGHTER JETS - A system for bistatic radar target detection employs an unmanned aerial vehicle (UAV) having a radar antenna for bistatic reception of reflected radar pulses. The UAV operates with a flight profile in contested airspace. A tactical fighter aircraft having a radar transmitter for transmitting radar pulses operates with a flight profile in uncontested airspace. A communications data link operably interconnects the UAV and the tactical fighter aircraft, the communications data link transmitting data produced by the bistatic reception of reflected radar pulses in the UAV radar antenna to the fighter aircraft. | 2017-10-19 |
20170297713 | Vehicle Body and Method for Assembling a Vehicle Body - A vehicle body includes a primary vehicle structure and interior vehicle fittings as well as a coupling device for fastening the interior vehicle fittings to the primary vehicle structure. The coupling device is configured to generate a magnetic field, so as to fasten the interior vehicle fittings to the primary vehicle structure without contact. Methods for assembling a vehicle body as well as an edifice are also described. | 2017-10-19 |
20170297714 | AIRCRAFT CEILING LINER ELEMENT WITH A CARRIER PLATFORM - An aircraft ceiling liner element comprises a load-bearing carrier platform, configured to form a part of an aircraft ceiling liner, and a mounting mounted on the carrier platform, connectable to a primary structure of the aircraft. An electrical connection mounted on the carrier platform is connectable to an electrical supply network of the aircraft. Furthermore, the aircraft ceiling liner element comprises a mechanical interface mounted on the carrier platform, configured to attach various interchangeable modular units detachably and in a load-transferring manner to the carrier platform, and an electrical interface mounted on the carrier platform, which interface is configured to create an electrical connection between the modular unit and the carrier platform. | 2017-10-19 |
20170297715 | TOILET SYSTEM AND METHOD OF ASSEMBLING - A toilet system that includes a waste receptacle including an outlet configured to channel waste therethrough. The system also includes a conveyor assembly including a housing that includes an inlet and at least one outlet. The inlet is coupled in flow communication with the outlet of the waste receptacle. The conveyor assembly also includes a transport mechanism positioned within the housing, and the transport mechanism is operable to actively transport the waste from the inlet towards the at least one outlet of said housing. | 2017-10-19 |
20170297716 | CONDENSATE REMOVAL SYSTEM OF AN AIRCRAFT COOLING SYSTEM - An aircraft includes a cooling compartment and an evaporative chiller configured to cool the cooling compartment. The evaporative chiller includes a compressor, an evaporator having airflow to the cooling compartment, and a condenser. The condenser has an exhaust airflow to cool the condenser. The evaporative chiller has a condensate removal system removing condensate produced by the evaporator using the exhaust airflow of the condenser to discharge the condensate. | 2017-10-19 |
20170297717 | CONVERTIBLE CHILLED STOWAGE COMPARTMENT IN AN AIRCRAFT - An aircraft includes a cabin wall defining a cabin and a convertible monument in the cabin adjacent the cabin wall. The convertible monument has a plurality of monument walls defining sides, a front and a rear of the monument surrounding a chamber defined by the monument walls. The convertible monument has a closet component positioned in the chamber for supporting non-perishable items in the chamber. The chamber has a convertible area convertible between a cooling compartment and an uncooled compartment. A chiller is positioned in the chamber proximate the convertible area. The chiller is configured to supply cool air to the cooling compartment when operated for cooling perishable items stowed in the cooling compartment. The convertible area is used as an uncooled compartment for stowing non-perishable items when the chiller is inactive. | 2017-10-19 |
20170297718 | INTEGRATED SINK AND DISPOSAL UNIT - Embodiments of the present invention provide systems and methods for disposal of liquid and food into a sink basin. The disclosed system cooperates with and delivers the received waste material to the main waste system on-board the vehicle. This is typically an aircraft waste tank. The system does not require a manual flush, but includes a sensor system that activates drainage of the holding line when the liquid and/or other waste material reaches a certain level therein. The disclosed system combines the functionalities of a common galley sink and a galley waste disposal unit, but occupies only the space envelope of an existing galley sink. The use of an existing galley sink means that no additional space on the countertop is required. | 2017-10-19 |
20170297719 | PAIRED HERRINGBONE HIGH DENSITY BUSINESS CLASS SEATING ARRANGEMENT - Described are seating arrangements having at least one set of columns that include an aisle column of seating units positioned adjacent a wall column of seating units. The aisle column is positioned adjacent an aisle, and the wall column is positioned adjacent an exterior wall. Each seating unit has a bed position having a head end and a foot end, wherein at least a height-limited portion of the foot end is less than a delineating height that separates a lower portion of the aisle from a upper portion of the aisle. The seating units in the adjacent columns are longitudinally aligned and positioned adjacent one another, as well as being angled with respect to each other. The height-limited portion of the foot ends in the aisle column is positioned adjacent the aisle, and the height-limited portion of the foot ends in the wall column is positioned within a concave portion of the exterior wall. | 2017-10-19 |
20170297720 | OVERRIDE BYPASS ASSEMBLY FOR A SEAT LOCKING MECHANISM - An override bypass assembly comprises a cable and a pulley wheel operably connected to the cable. The cable in operation rotates the pulley wheel when tension is applied to the cable. The override bypass assembly also comprises a telescoping cylinder assembly operably connected to the pulley wheel. The pulley wheel in operation moves the telescoping cylinder assembly to an unlocked position. The override bypass assembly further comprises a biasing mechanism operably connected to at least one of the pulley wheel and the telescoping cylinder assembly. The biasing mechanism in operation moves the telescoping cylinder to a locked position when tension applied to the cable is relieved. | 2017-10-19 |
20170297721 | ROTATIONAL BRAKE ASSEMBLY FOR A SEAT LOCKING MECHANISM - A rotational brake assembly comprises: a swivel disc having an outer diameter and a plurality of locking holes proximate the outer diameter; a cam having an angled slot; a lifting pin located within the angled slot of the cam; and a rotational brake pin operably connected to the lifting pin. The cam in operation moves to at least one of a locked position and an unlocked position based on an input. The lifting pin in operation moves along the angled slot when the cam moves. The rotational brake pin in operation moves due to motion of the cam. The rotational brake pin in operation moves from an engaged position with the swivel disc to a disengaged position, when the cam moves from the locked to the unlocked position. The rotational brake pin in operation moves to the engaged position, when the cam moves to the locked position. | 2017-10-19 |
20170297722 | ARMREST FOR AIRCRAFT SEAT, ASSOCIATED SEAT AND PROCESS - Armrest for aircraft seat, associated seat and process are provided. The armrest includes a stationary part ( | 2017-10-19 |
20170297723 | SEAT RAIL COVER FOR COVERING A SEAT RAIL IN A VEHICLE FLOOR AND METHOD FOR MANUFACTURING A SEAT RAIL COVER - A seat rail cover includes a retaining section, configured to be introduced at least partially into a part of the seat rail, and a cover section, configured to cover the seat rail when the retaining section is introduced into the seat rail. At least the cover section of the seat rail cover is formed in one piece by 3D printing. Geometry, surface texture, color composition and/or color pattern of at least a visible part of the cover section in the installed state of the seat rail cover are matched to a surface and/or a floor covering of a floor element next to a seat rail to which the seat rail cover is connectable. Furthermore, a floor element with a seat rail and a seat rail cover as well as an aircraft with such a floor element. A method for manufacturing a seat rail cover by 3D printing. | 2017-10-19 |
20170297724 | RISER RELEASE FLARING SYSTEM FOR PARAFOILS - Described herein are features for a riser release flaring system for parafoils and other descent flight vehicles for controlled descent and landing of the flight vehicle. The descent flight vehicle may have a payload suspended by a canopy. The descent flight vehicle may be released from a high altitude lighter-than-air (LTA) system, from another system, or may not be associated with any other flight system. The riser release auto flare system is used with the descent system, such as the parafoil, for controlled and safe landing of the payload. Riser lines are released at a controlled rate and for a fixed distance to automatically cause the payload to pull control lines to flare the parafoil and slow a descent and/or forward speed of the vehicle. The riser lines may be released in response to the descent system satisfying a landing criterion, such as altitude. | 2017-10-19 |
20170297725 | MULTIPLE AIRCRAFT SEAT EJECTION MODE SELECTOR - A system for selecting an ejection mode on an aircraft may include an egress actuator, a ballistic signal system operatively connected to the egress actuator, and a processor operatively connected to the ballistic signal system and the egress actuator. The processor may be configured to receive, from an aircraft controller, a flight characteristic, and select, based on the flight characteristic, an ejection mode from two ejection modes. The processor may be further configured to receive a pilot egress command from the ballistic signal system, and transmit, to the egress actuator, a signal to actuate the ejection mode from the two ejection modes. | 2017-10-19 |