Abstract: A vessel propulsion apparatus includes an engine that rotates a crankshaft in a forward rotation direction, a rotation speed detector that detects a rotation speed of the crankshaft, a propeller shaft coupled to a propeller, a shift switch that switches between a shift-in state and a neutral state, a shift state detector, an intake passage, a throttle valve, an intake pressure sensor, and a controller. The controller determines that the crankshaft is reversely rotating by an external force input from the propeller shaft when a predetermined reverse rotation recording condition is satisfied, and stores reverse rotation information. The reverse rotation recording condition includes a condition that an intake pressure after the shift switch switches from a neutral state to a shift-in state while the crankshaft rotates in the forward rotation direction is larger than a value equal to or higher than atmospheric pressure.

Abstract: A steering system for a marine vessel comprises a helm, a control head, and a joystick. The helm and control head may respectively provide user inputted steering commands and user inputted shift and throttle commands on a first CAN network. The joystick and the control head may respectively provide user inputted steering commands and user inputted shift and throttle commands on a second CAN network. The helm may provide user inputted steering commands on the first CAN network. The control head may provide user inputted shift and throttle commands on the second CAN network. The joystick may provide user inputted steering commands and user inputted shift and throttle commands on either the first CAN network or the second CAN network.

Abstract: A personal watercraft comprises a body including a deck and a hull, the body being provided with an engine room; an engine disposed in the engine room; a maintenance opening provided in the deck and located above the engine to in such a manner that an outside region of the body is in communication with an interior of the engine room through the maintenance opening; at least one duct mounting hole provided in the deck at a location different from a location of the maintenance opening in such a manner that the outside region is in communication with the interior of the engine room through the duct mounting hole; at least one ventilation duct fitted to the duct mounting hole to guide air from the outside region to the engine room; and an engine hood covering the maintenance opening and an air inlet of the ventilation duct.

Abstract: Disclosed are a method and system to form a contoured structure using deep rolling. The method includes using deep rolling to introduce plastic deformation to one or more portions of a work piece to form a convex contour in the work piece. The work piece, and subsequently formed contoured structure, can be metal or composite. The disclosed deep rolling systems and methods form, for example contoured aircraft panels, while also providing fatigue strength improvement and low level of work hardening during the forming process rather than as a post-production surface treatment.

Abstract: An aircraft includes a fuselage including a plurality of frame members disposed at predetermined intervals in a longitudinal direction of the fuselage and a plurality of stringers extending substantially linearly in the longitudinal direction. The fuselage defines an aircraft interior. A compartment is located in the interior of the fuselage. The compartment defines an interior area. A first window assembly is mounted to an upper portion of the fuselage for introducing daylight into the interior area. The first window assembly is flanked by adjacent frame members of the plurality of frame members and adjacent stringers of the plurality of stringers. The first window assembly includes a window pane, an inner cover and a retainer. The inner cover introduces daylight from the window pane into the interior area. The retainer secures the window pane and the inner cover to the fuselage.

Abstract: A maintenance step for a helicopter, comprising: a casing that is adapted for integration into a lateral shell of a fuselage of a helicopter, and a step member that is pivotally mounted to the casing, wherein a stirrup unit is pivotally mounted to the step member, the stirrup unit comprising at least a first and a second section, the second section being telescopically mounted to the first section.

Abstract: A system and method for restricting thermal transfer between an ambient space and a substructure include providing an inner mold line side (IML) surface to the substructure. A plurality of clevises extends upward from the IML surface. An outer mold line side (OML) surface is interposed between the ambient space and the IML surface. The OML surface includes at least one horizontally oriented wing and a plurality of horizontally oriented shoulders. The wing selectively engages at least two of the shoulders. A plurality of lugs extends downward from the OML surface. At least one aperture extends longitudinally through the OML surface to selectively permit fluid communication between the ambient space and the IML surface. A plug selectively substantially fills the aperture and is selectively secured to the IML surface. A fastener, configured to selectively secure the OML surface to the IML surface, extends horizontally through the clevises and the lugs.

Abstract: A tail boom having a structure and a protuberance, the protuberance being secure with the structure. In each section of the tail boom, the protuberance extends in elevation over an extension height (Hext) and it extends laterally over an extension thickness (EPext), the extension height (Hext) lying in the range 0.05 times the maximum thickness (EPmax) of the structure, included, to 0.5 times the maximum thickness (EPmax), included, of the section, the extension thickness (EPext) lying in the range 0 to 0.4 times the maximum thickness (EPmax), included, of the section.

Abstract: Systems and methods for determining an operating state for an aircraft are provided. In one example, a method can include accessing, by one or more computing devices located on an aircraft, a database of precomputed operating parameters associated with aircraft trim determined in a priori process. The method can further include receiving a real time measurement of one or more dyanamic parameters associated with the aircraft. An aircraft trim parameter can be determined from the precomputed operating parameters independent of the real time measurements. The method can further include determining an enhanced operating state for the aircraft based at least in part on the aircraft trim parameter and the real time measurement of the one or more dynamic operating parameters.

Abstract: A gate departure system for an aircraft includes an electric traction motor for driving a wheel of a main landing gear assembly of the aircraft on only one side of the aircraft; and a controller selectively connected to a starter-generator of an auxiliary power unit (APU) and to the traction motor to control flow of electrical power to either the starter-generator for starting of the APU or the electric traction motor for driving the wheel.

Abstract: A pneumatic taxi system of an aircraft with a rotary non-turbine air motor for driving a wheel, of an aircraft landing gear, with compressed air.

Abstract: A clutch assembly for an aircraft drive wheel drive system to move an aircraft independently on the ground is provided. The clutch is mounted within an aircraft drive wheel to be operatively engaged and disengaged to selectively actuate a roller traction or other drive system to activate a non-engine drive means to drive the wheel and the aircraft. One embodiment of the clutch assembly includes a plurality of pivoted sprag elements selectively activatable to transmit torque between inner and outer clutch members and activate the drive wheel drive system. The clutch assembly may also include mating crown gear and straight gear elements integrated with the drive system to reduce stresses on the drive system as the drive means is actuated. Various arrangements of sprags and clutch assembly components may be provided to monitor and selectively control disengagement of the clutch assembly and communicate disengagement to selectively prevent drive system actuation.

Abstract: A damper for an aircraft landing gear includes a housing with an internal cavity. A weight is slidingly disposed within the cavity and positioned between and engages a first pneumatic spring and a second pneumatic spring. The shimmy damper includes at least one mounting feature to fixedly mount the housing to a component of the aircraft landing gear.

Abstract: The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors.

Abstract: A rotary wing with a curved outer surface, inlet openings and an edge foil for use in helicopters to improve lift and efficiency, maximizing the gross weight lift and the horizontal flight speed capabilities and minimizing performance penalties and unstable, inefficient operation.

Abstract: A rotor blade rotated about a rotor hub is provided including a first section configured to mount to the rotor hub. The first section includes a spindle and an inboard torque tube surrounding a portion of the spindle. A second section of the rotor blade includes a flexbeam and an outboard torque tube attached to and surrounding the flexbeam. An inboard end of the flexbeam is rotatable coupled to a first end of the spindle. The second section is configured to rotate about a blade axis between an aligned position and a rotated position. A transitional brace configured to surround a portion of the rotor blade adjacent the coupled flexbeam and spindle is movable between a first position and a second position. When in the first position, the transitional brace limits movement of the second section about the blade axis.

Abstract: The present invention provides a drone-type smart car wash robot. The drone-type smart car wash robot may detect dirty state information and shape information of a vehicle while flying around the vehicle in an unmanned manner, and allow car wash to be intelligently and automatically performed while flying according to a flight path calculated in a customized manner to correspond to the dirty state information and shape information and a car wash operation control signal, and therefore it is possible to minimize constraints of time and place for car wash and frequently perform car wash in a simple and easy manner.

Abstract: A weapon interface system, and methods of operating the same. The weapon interface system is coupled to an electrical interconnection system of a delivery platform and a weapon system coupled to a rack system. The weapon interface system includes a translation interface configured to provide an interface between the electrical interconnection system and an inductive power and data circuit. The weapon interface system also includes a weapon coupler, coupled to the translation interface, configured to provide an inductive coupling to the weapon system to provide mission information thereto.

Abstract: A method for automatically delivering a physical mail includes receiving, by an unmanned aerial vehicle from an unmanned aerial vehicle management system, a delivery information, the delivery information includes information about a first secure mailbox and information about a second secure mailbox, the first secure mailbox being related to a first target user, delivering the physical mail to the first secure mailbox, and rerouting the unmanned aerial vehicle carrying the physical mail from the first secure mailbox to the second secure mailbox in response to the physical mail being delivered to the first secure mailbox.

Abstract: The disclosure is directed to systems and methods for autonomously picking up water in support of fire fighting missions using aerial vehicles. More particularly, the disclosure is directed to systems and methods for picking up water in support of fire fighting missions using onboard sensing and decision making processes with application of the fire retardant using unmanned aerial vehicles.

Abstract: Systems, apparatuses, and methods are provided herein for providing package release for an unmanned aerial system. An apparatus for releasing packages for retrieval by an unmanned aerial system comprises a plurality of arms configured to surround a plurality of packages stacked vertically in an extended position, a plurality of powered hinges at a base of each of the plurality of arms, and a control circuit coupled to the plurality of powered hinges. The control circuit being configured to: determine a height for a first lowered position for the plurality of arms at which the plurality arms do not obstruct an unmanned aerial vehicle from coupling with a coupling structure on a first package of the plurality of packages positioned at a top of the plurality of packages, and cause the plurality of powered hinges to pivot the plurality of arms from the extended position to the first lowered position.

Abstract: A mounting system may be installed in an aircraft, such as by installing a first plate and a second plate on either side of a sandwich panel wall in a personal space of an aircraft. The first plate and second plate may be coupled together, and a structural interface may receive a mounting accessory such that it is positioned adjacent the first plate. A personal electronic device may be mounted to the mounting accessory, thereby facilitating use of the personal electronic device on-board the aircraft. Such a mounting system may facilitate the use of personal electronic devices in lieu of costly in-flight entertainment systems. The first plate and second plate may be secured to a honeycomb core sandwich panel, such that fasteners may extend through inserts extending through the core, thereby distributing the weight of the personal electronic device and mounting accessory via the first plate and second plate.

Abstract: A lavatory unit (100) disposed in a passenger cabin of an aircraft has a box-shaped main body (105) configured from panels. A bottom of the main body (105) has a rectangular shape formed with short sides and long sides, and a door is provided on one short side. A toilet unit (110) is installed on the other slut side opposite the door. A foldable sink (200) is mounted above the toilet unit (110). Since the sink, which would typically have been provided on a panel on the long-side, is made foldable and mounted above the toilet unit, the width (W2) of the lavatory unit can be reduced.

Abstract: An improved slider for use with a parachute, particularly a ram-air type parachute, is provided. The slider includes a generally rectangular piece of material having grommets in the corners through which the suspension lines of the parachute run. At least one retaining structure is attached to or made in the slider material for securing one or more stiffening elements. The stiffening elements are flexible enough to allow for the packing of the parachute, but stiff enough to keep the material of the slider spread open in the fore/aft direction across the short axis of the slider and thereby prevent the slider from folding and flapping once the canopy has opened.

Abstract: Systems and methods for enhancing engine performance based on atmospheric rain conditions are provided. For example, a method can include selecting one or more points along a flight path of an aircraft and receiving a radar reflectivity measurement for each of the one or more points obtained using a radar device located on the aircraft. The method can further include determining an estimate of liquid water content for each of the one or more points based at least in part on the radar reflectivity measurements; and controlling at least one component of the aircraft engine (e.g., a variable stator vane) based at least in part on the estimate of liquid water content for at least one of the plurality of points.

Abstract: Systems and methods for enhancing engine performance based on atmospheric ice particles are provided. For example, a method can include selecting one or more points along a flight path of an aircraft and receiving a reflectivity measurement for each of the one or more points obtained using a device located on the aircraft. The method can further include determining an estimate of ice water content for each of the one or more points based at least in part on the reflectivity measurements; and controlling at least one component of the aircraft engine (e.g., a variable bleed valve) based at least in part on the estimate of ice water content for at least one of the plurality of points.

Abstract: A system includes a first mast torque transfer system, a second mast torque transfer system coupled to the first mast torque transfer system, and a torque limiting system. The torque limiting system includes a first sensor configured to determine a torque of the first mast torque transfer system, a second sensor configured to determine a torque of the second mast torque transfer system, and a processor configured to determine a differential torque between the torque of the first mast torque transfer system and the torque of the second mast torque transfer system and configured to control at least one of a torque input and a torque output to at least one of the first and second mast torque transfer systems as a function of the determined differential torque.

Abstract: A turbofan engine is provided. The turbofan engine includes a nacelle housing including a radially outer wall and a radially inner wall that defines an interior cavity within the nacelle housing. The turbofan engine also includes a fan assembly positioned at least partially within the interior cavity. A flow passage is defined between the radially outer wall and the radially inner wall for channeling a flow of air therethrough. The flow passage is configured to couple a portion of the interior cavity upstream from the fan assembly in flow communication with an ambient environment exterior from the radially outer wall.

Abstract: An aircraft (10) comprising a fuselage (12), the fuselage (10) comprising at least first and second inwardly tapering portions (20, 22) extending in a generally rearward direction from an aft end of the fuselage (12), each inwardly tapering portion (20, 22) comprising a boundary layer ingesting propulsor (36) mounted thereon.

Abstract: An exhaust infrared signature reduction arrangement includes an exhaust duct having a plurality of holes through a wall of the exhaust duct, and a housing surrounding at least a portion of the exhaust duct defining a cavity between the exhaust duct and the housing.

Abstract: An exhaust system for a rotary wing aircraft includes a diffuser located at an airframe of the rotary wing aircraft and operably connected to an engine of the rotary wing aircraft, and a chimney extending upwardly from a diffuser wall. A door is movably positioned at the diffuser to selectively direct an engine exhaust flow through the diffuser or through the chimney. A rotary wing aircraft includes an airframe, a rotor system positioned at the airframe and rotatable about a rotor axis, and an engine operably connected to the rotor system to drive rotation of the rotor system. The aircraft includes an engine exhaust system including a diffuser positioned at the airframe and operably connected to the engine, a chimney extending upwardly from a diffuser wall, and a door positioned at the diffuser to selectively direct an engine exhaust flow through the diffuser or through the chimney.

Abstract: A quadcopter has a fuselage and four rotors, each defining a thrust vector. An onboard camera system includes a gimbal with a roll axis and a pitch axis. Right side motors are mounted with a dihedral angle so that their respective thrust vectors intersect at a common focal point located above the fuselage. Left side motors are mounted with a dihedral angle so that their respective thrust vectors intersect at a common focal point located above the fuselage. The tilted thrust vectors provide yaw stability which allows flight yaw control to be used as yaw control of the onboard camera.

Abstract: A method of slowing an aircraft overrunning a runway, including paving an area immediately beyond the end of a runway with foamed glass bodies to define a bed, covering the bed with a layer of cementitious material to define a composite bed, and crushing at least a portion of the composite bed with an oncoming aircraft, wherein crushing the at least a portion of the composite bed removes kinetic energy from the oncoming aircraft to slow the oncoming aircraft. The composite bed is generally resistant to fire.

Abstract: An Airborne Wind Turbine (“AWT”) may be used to facilitate conversion of kinetic energy to electrical energy. An AWT may include an aerial vehicle that flies in a path to convert kinetic wind energy to electrical energy. The aerial vehicle may be tethered to an active azimuth ground station. In one aspect, the ground station has platform that is rotatable about an azimuth axis. The platform is coupled to an azimuth slewing bearing that is coupled an azimuth drive motor operable to rotate the platform about the azimuth axis. The platform may be coupled to a winch frame with an interior cavity. The winch frame may be coupled to a winch drum that is rotatable about a central axis. The winch drum may be coupled to a winch drum slewing bearing and a winch drum drive motor operable to rotate the winch drum about the central axis.

Abstract: A control moment gyroscope (CMG) module for use in a satellite comprising a CMG, the CMG comprising a flywheel assembly mounted on a gimbal assembly, the flywheel assembly comprising a flywheel rim, a flywheel spokes member and a flywheel shaft, the flywheel rim circumscribing the flywheel shaft, and the flywheel spokes member extending between the flywheel shaft and the flywheel rim. The gimbal assembly comprises at least one gimbal and a spin motor, the spin motor for rotating the flywheel assembly about a first axis. The CMG further comprises a torque shaft and a torque motor for rotating the at least one gimbal about a second axis. The CMG module further comprises a hermetic first shell housing; and a hermetic second shell housing; wherein the second shell housing is joined to the first shell housing by a hermetic seal to form an airtight interior of the CMG module, the interior of the CMG module containing the CMG.

Abstract: A system is configured to shield an interior chamber of a structure. The system may include a power source, an outer shield assembly operatively connected to the power source and coupled to an outer wall of the structure, and an inner shield assembly surrounding the internal chamber. The outer shield assembly generates a magnetic field through and around the structure. The inner shield assembly deflects radiation particles away from the interior chamber and re-directs portions of the magnetic field around the interior chamber.

Abstract: The present invention provides a seamless capsule for delivering a material inside said capsule to a destination requiring the encapsulated material includes a shell having a uni-body construction with a fill aperture in a top portion to receive a predetermined material in a cavity defined by an inner wall of the shell. The shell has an outer wall with a predetermined configuration corresponding to the intended use of the seamless capsule. Further, the seamless capsule includes a cover integrally joined to the top portion of the shell to cover fill aperture in the top portion of the shell after the material is disposed in the cavity. The present invention also provides a method for encapsulating a material for delivery to a predetermined destination requiring the encapsulated material. The method includes the steps of fabricating a seamless shell with a fill aperture in a top portion to receive a predetermined material in a cavity defined by an inner wall of the shell.

Abstract: An apparatus for filling a plurality of containers with a fluid. The apparatus including a connector configured to removably couple the apparatus to a fluid source, a flow path providing fluid communication between the fluid source and a plurality of containers coupled to the apparatus, a sealing element disposed within each of the plurality of containers, the sealing element configured to couple the container to the apparatus and automatically seal the container when the container is decoupled from the apparatus, and a retaining member affixed to each of the plurality of containers to position the sealing element in a neck of each of the plurality of containers.

Abstract: A method for packing a fish product (39), and a fish product package. The method comprises packing the fish product (39) in a vacuum package, arranging in said vacuum package an empty space (43), forming in the vacuum package by means of empty space (43) an underpressure, and maintaining the empty space (43) in the package, the underpressure generating pressure on the fish product (39).

Abstract: A filling machine (M) for filling containers (1) with fruit or vegetables products, comprising transportation means (2) for the step-by-step conveying the said containers (1) to be filled along a horizontal determined direction (D1); primary plain belt conveyor means (3,4) for products feeding parallel to said horizontal direction (D1) and adapted to realize a main bulk filling of the said containers (1); secondary belt conveyor means (5,6) for singles products feeding parallel to said horizontal direction (D1) and adapted to cooperate simultaneously with said primary belt conveyor means (3,4) so as to complete the whole final filling of the said containers (1); motion means (7) applied to both said principal (3,4) and secondary (5,6) belt conveyor means for reciprocating moving said primary (3,4) and secondary (5,6) belt conveyor means in a direction (D2) parallel to said horizontal direction (D1); and at least a weighing station (8,9) for constant weighing the containers (1) during said filling steps.

Abstract: Method of coiling a flexible elongate element (64) inside a container (80A) made from a flexible sheet material wherein at least part of the sheet material is tensioned by establishing a pressure differential between an inner surface (100) and an outer surface (92) of the sheet material and the flexible elongate element (64) is directed onto the tensioned sheet material to form a hole (98), the flexible elongate element being then fed through the hole to form a coil inside the container.

Abstract: Described is a unit (1) for feeding closing elements (34) for closing containers (2) defining capsules (3) for extraction or infusion beverages for a machine (100) for packaging capsules (3) for extraction or infusion beverages comprising: means (4) for feeding a web (5) of heat-sealable material along a predetermined path for feeding the web; a plurality of punches (6), positioned along the path for feeding the web of heat-sealable material in a region (R1) for forming the closing elements (34) and movable between an operating position (P1) wherein they make contact with the web (5) of heat-sealable material for cutting portions of the web, so as to form corresponding closing elements (34) and a non-operating position retracted relative to the web (5); a plurality of pickup units (GP1, GP2, GP3, GP4) each having a plurality of pickup means (7), each pickup unit (GP1, GP2, GP3, GP4) being movable individually along a closed path (PS2) between a pickup position (P3), wherein the respective pickup means (7) are

Abstract: An extraction device and method (1) for moving, from a pile (3), a batch (4) of stacked flat products (2) that are not connected to one another and that form the top of the pile (3), with the extraction device (1) including a frame (5), and, mounted in the frame (5), a gripping element (6) in the form of a controlled vise for firmly grasping section by section the batch (4) to be extracted. This device also includes, mounted in the frame (5), a separation element (8), separated from the gripping element (6), carrying a support surface (9) to come under the batch (4).

Abstract: In one general aspect, a system for aseptically filling a tray of pharmaceutical containers with a pharmaceutical product is disclosed, which consists of an aseptic chamber, one or more articulated arms within the chamber, a sensor aseptically disposed with respect to the chamber, and a controller. The controller determines the locations of openings of the containers based on the image information from the sensor, and automatically guides one of the arms to fill the containers with the product. In order to obtain suitable contrast for accurately identifying the openings, an illuminator illuminates the tray with substantially collimated light. The sensor images the tray and containers using collimated light reflected from a reflective surface such as a retroreflector under the tray. To this end, the sensor may be disposed at a large enough distance from the retroreflector to collect largely the retroreflected light, or the sensor may employ a telecentric lens or a Fresnel lens.

Abstract: A container is provided with a cylindrical sidewall. A top flange projects from the cylindrical sidewall in a first direction by a first distance. A bottom flange projects from the sidewall in the first direction by a second distance that is less than the first distance. The top flange and the bottom flange extend circumferentially around the sidewall. A gap is formed between the top flange and the bottom flange.

Abstract: A plastic container is provided that includes a lower supporting base portion; a sidewall portion extending upwardly from the base portion; a neck portion extending upwardly from the sidewall portion; and a closure. The neck portion includes a support flange having an upper and lower surface, threads, a tamper-evident formation, and a dispensing opening at the top of the neck portion. In an embodiment, the weight of the neck portion is 3.0 grams or less; and the vertical distance from the top of the dispensing opening to the lower surface of the support flange, including the threads and the tamper-evident formation, is 0.580 inches or less. A preform and method for making a container are also disclosed.

Abstract: Container (1) made from plastic material, provided with a body and a base (3) which extends from a lower end of the body, the base (3) including: a peripheral resting surface (5) which defines a flat annular deposition line (6) for the container (1); —a concave dome (9) which extends from the deposition line (6) to the central zone (7); a series of moulded beams (10) in the dome (9) which each radiate from the central zone (7) towards the resting surface (5), each beam (10) including a pair of radial grooves (11) which are moulded in the dome (9) and are separated by a radial rib which projects from the bases (12) of the grooves (11).

Abstract: The present description includes containers having an improved puncture design that can be punctured without substantial deformation of the container. Such containers are particularly suitable for use in preparing beverages using automatic machines, particularly those used for preparation of single serve beverages. Also provided are thermoplastic materials having improved punctureability for use in containers, containers for preparation of a beverage, and methods for preparing a beverage using such containers.

Abstract: A foldable box template includes first, second, third, fourth, and fifth segments. Each of the segments has a length, a width, and one or more flaps. The first segment is positioned at a first end of the template and the fifth segment is positioned at a second, opposing end of the template. The sum of the lengths of the first segment and the fifth segment is generally equal to the length of the third segment. As a result, the first and fifth segments form a seam on a sidewall of a box formed from the box template. In some cases, the seam formed by the first and fifth segments is offset from seams formed in top and bottom surfaces of the box. The seam formed by the first and fifth segments is offset from a corner of the box.

Abstract: The pull tab portion is formed as an area surrounded by four solid or broken line-formed incisions. The four incisions include a first incision which is formed as a boundary line of the push-in portion, a pair of second incisions each of which is continuous with the first incision and which are spaced apart from each other in the width direction of the adhesive tape, and a third incision which is continuous with each of the pair of second incisions and functions as a folding line. When those ends of the pair of second incisions which are each located opposite to the push-in portion are called tape-side incision ends, the distance between the two tape-side incision ends in the width direction of the adhesive tape is set greater than the width of the adhesive tape.