Abstract: An method for ice fishing using a submersible vehicle assembly and underwater powered observation system using a camera and source of light of a green laser to be directed to the underside of ice so as to locate the vehicle assembly and allow the user to cut a hole in the ice at or near fish. In this manner the vehicle assembly may be utilized for the underwater tasks of locating fish and/or observing fish under the ice. Additional features include identifying water temperature and depth information that may be displayed on the control unit, a hydrophobic coating preventing ice buildup, and a stand adaptable for resting on the bottom during use.

Abstract: A power steering system for a marine steering includes a hydraulic cylinder, an actuator block that is mounted on an outer end of a ram of the cylinder, and valving. In one embodiment, the valving is located in the hydraulic cylinder and includes at least one flow limiting valve that, through an initial portion of a stroke thereof, limits fluid flow rates through the valve to a generally constant, relatively low level. This limits the rate of extension or retraction of the ram out of or into the barrel and prevents valve chatter. In another embodiment the valving includes ball-type check valves that are located within the actuator block and that are actuated by a rocker arm assembly in the actuator block.

Abstract: In described embodiments, a motor mount includes a track with guide rails defining a channel, a sled within the channel, first and second end blocks between the guide rails at first and second ends, and a rotatable rod between the end blocks. The first end block has a rack formed thereon, and the guide rails form an opening adjacent to the first end block. Top and bottom plates of the sled have corresponding ends fixed with a hinge, the top plate fastened about the rod, the bottom plate have a gear formed around the hinge, and the hinge facing toward the first end block. Rotating the rod moves the hinge toward the first block and when the gear of the bottom plate engages the rack, the bottom plate rotates about the hinge through the opening and extends inverted over the first end block to an extended position.

Abstract: A control system to optimize response time of a plurality of engines of a machine is provided. The control system includes a controller configured to determine a first engine group and a second engine group based on data regarding response time characteristics of the plurality of engines, control the first engine group to increase output power of the machine when the output power of the machine is below a predetermined power output threshold, and control the second engine group to increase output power of the machine responsive to the output power of the machine reaching the predetermined power output threshold. A response time of the first engine group is faster than a response time of the second engine group when the output power of the machine is below the predetermined power output threshold.

Abstract: A marine engine quick drain system is provided having multiple drainage tubes connecting each drainage point on the marine engine to a water removal device. The water removal device is operable to drain water from all drain ports within the engine simultaneously, routing all drain ports to single point drain which is preferably connected to vacuum for evacuating fluids from the marine engine. Fittings are provided to connect each drainage tube to each drainage point on the marine engine. Integrated within each fitting is a fluid sensor which indicates the presence of water in each part of the engine. Each sensor is connected back to a central control console having a microprocessor which will control the water removal device and verify that the marine engine has been drained properly or if there is water in the marine engine.

Abstract: A flexible steering fin and passive cambering keel for sailboats having fundamental simplicity yet enhanced performance and superior operation in terms of design and components. The steering fin is a relatively short and elongated flexible blade with its leading edge fixed beneath the hull. A rod passing through the hull functions as a simple lever controlling the trailing edge of the blade, which provides both tilt and curvature for unique handling and ease of use. A separate flexible keel provides the function of tilting the keel as it is cambered, for greater lift. A unique pivoting resilient steering assembly is incorporated, along with a rotational circular hull section, frame and cam assembly to control the keel.

Abstract: A trimmable rudder system for a marine vessel such as a planing power boat, the system including a pair of rudder assemblies, each of which includes a rudder blade movably coupled to the hull by way of a ball-and-socket joint. Each rudder assembly includes a rudder shaft that extends from the rudder blade through the ball-and-socket joint and can be rotated for rotating the rudder blade to steer the power boat. Each rudder shaft may be operably coupled to a pair of actuators configured to control trim and camber positions of the rudder blade so that the pair of rudder blades can collectively achieve a desired hull trim change, including listing control and planing control of the power boat. Steering position, trim position, and camber position of the rudder blades may be simultaneously changed.

Abstract: Systems and methods for securing an emergency exit door on an armrest of a seat are provided. A system includes a latch connected to an armrest of a seat of a vehicle. The latch is moveable relative to the armrest between a stowed position and a deployed position. The latch is structured and arranged to engage an edge of a door that is associated with an exit of the vehicle to hold the door on the armrest.

Abstract: An aircraft wing comprises a fixed wing and a wing tip device at the tip thereof. The wing tip device is configurable between: a flight configuration for use during flight and a ground configuration for use during ground-based operations to reduce the span. The wing comprises an actuation assembly for moving the wing tip device. The actuation assembly is arranged to move the wing tip device in a two-stage movement comprising a first stage in which the wing tip device is translated away from the flight configuration in a linear movement only, and a second, subsequent stage, in which the wing tip device is rotated to the ground configuration.

Abstract: An aircraft comprising a fuselage; a main wing provided on a fuselage lower side and including a center wing and an outer wing; and a fairing covering at least a lower surface of the center wing, and a seal interposed between an end edge in a right-left direction of the fairing and an outer wing lower surface. In the aircraft, a most outboard fitting located on a most outboard side out of fittings respectively provided at a plurality of positions in the right-left direction of the fairing, and an outer wing fitting provided on the outer wing are pin-coupled via a pin or pins extending along a front-rear direction. The outer wing fitting is coupled to the outer wing at a position on an inboard side with respect to the end edge and other than a position of a joining structure for joining the center wing and the outer wing.

Abstract: A flap support structure for an aircraft wing having a trailing edge flap, the flap support structure comprising: a flap support beam including an aerodynamic fairing; and a drive unit including a universal support structure which rotatably receives a drive shaft connected to a drive arm for moving the trailing edge flap, wherein the universal support structure also forms part of the flap support beam and supports the aerodynamic fairing.

Abstract: Systems and methods according to one or more embodiments are provided for a Krueger flap assembly with dual Krueger seal assemblies. In certain embodiments, the dual Krueger seal assemblies may seal a space between a Krueger flap main body and an aircraft engine. Further seals may be provided to seal any gaps between the dual Krueger seal assemblies. In certain embodiments, one or both of the dual Krueger seal assemblies may include centrally grounded springs. The dual Krueger seal assemblies may include a plurality of springs supporting each Krueger seal assembly.

Abstract: Multi-directional control using upper surface blowing systems is described herein. One disclosed example method includes a flow director of an aircraft, where the flow director is to cause an exhaust stream of an upper surface blowing system to attach to a fuselage of the aircraft, and a controller to control the flow director to affect one or more of a pitch, a yaw or a roll of the aircraft by varying a degree of the attachment of the exhaust stream to the fuselage.

Abstract: An improved performance propeller employs a single propeller blade having an axis of rotation and a centripetal force about the axis. A pitch control unit is mounted opposite the single propeller blade and has a compensating centripetal force with respect to the single propeller blade about the axis.

Abstract: Air vehicles, fly-by wire systems, and method for preemptive mitigation of turbulence are provided. An air vehicle includes a flight control surface, a sensor, and a controller. The sensor is configured to determine a velocity of an air mass that is separated from the air vehicle by a predetermined distance. The controller is communicatively coupled with the sensor and is configured to determine whether the air mass will disturb smooth flight of the air vehicle. The controller is further configured to manipulate the flight control surface in response to determining that the air mass will disturb smooth flight of the air vehicle.

Abstract: An aircraft includes a first rotor assembly, a second rotor assembly, and a rotor phase angle control system. The system includes a phase adjustor operably associated with the first rotor assembly and the second rotor assembly. The method includes sensing vibrations exerted on the aircraft and offsetting a phase angle of the first rotor assembly and the second rotor assembly to minimize the vibrations.

Abstract: The lift, propulsion and stabilizing system for vertical takeoff and landing aircraft of the invention consists of applying during vertical flight on, below or in the interior of the fixed-wing aircraft one or more rotors or large fans each one with two or more horizontal blades, said rotors are activated by means of turboshafts, turbofans or turboprops with a mechanical, hydraulic, pneumatic or electrical transmission, and the respective motors. Using lifting and/or stabilizing and/or controlling fans and/or oscillating fins and/or air blasts. Placing the horizontal lifters near at least one end of the longitudinal axis and of the transverse axis of the aircraft. Generally said stabilizing elements form 90° with one another and with the central application point of the rotor or application of that which results from the lift forces.

Abstract: According to one embodiment, a linear control motor includes a first permanent magnet, a coil, a first magnetic material, a shaft, and a first non-magnetic material. The first non-magnetic material is disposed between at least one of the movable components and at least one of the static components and operable to prevent physical contact between at least one of the movable components and at least one of the static components.

Abstract: This disclosure describes a configuration of an unmanned aerial vehicle (UAV) that includes a frame that provides both structural support for the UAV and protection for foreign objects that may come into contact with the UAV. The UAV may have any number of lifting motors. For example, the UAV may include four lifting motors (also known as a quad-copter), eight lifting motors (octo-copter), etc. Likewise, to improve the efficiency of horizontal flight, the UAV may also include one or more pushing motor and propeller assemblies that are oriented at approximately ninety degrees to one or more of the lifting motors. When the UAV is moving horizontally, the pushing motor(s) may be engaged and the pushing propeller(s) will aid in the horizontal propulsion of the UAV.

Abstract: A UAV is provided to cancel background noise from audio data collected by the UAV. The UAV is provided with one or more background microphones in a proximity of one or more background noise-producing components. The UAV is also provided with one or more audio source collecting microphones. The audio data collected by the background microphones may be used to reduce or cancel interfering background noise from the audio signal detected by the audio source collecting microphone. The target audio may be captured or recorded with little or no background noise.

Abstract: This disclosure relates generally to Unmanned Aerial Vehicle (UAV), and more particularly to system and a method for landing of an Unmanned Aerial Vehicle (UAV). In one embodiment, the method includes estimating a 3-dimensional (3D) location of at least one media sensor mounted on the UAV relative to a marker representative of a landing location of the UAV. The marker comprises a recursive geometrical pattern. The landing of the UAV on the marker at the landing location is facilitated based on the 3D location of the at least one media sensor mounted on the UAV relative to the marker.

Abstract: Aspects include a system for transferring a payload between drones. The system includes a first drone having a first member and a first controller, the first member having a first coupling device on one end, the first member being configured to carry a payload, the first controller being configured to change a first altitude and orientation of the first drone. A second drone includes a second member and controller, the second member having a second coupling device on one end, the second member being configured to receive the payload, the second controller being configured to change a second altitude and orientation of the second drone. The controllers cooperate to change at least one of first and second orientations to operably engage the first coupling device to the second coupling device for transferring the payload from the first member to the second member.

Abstract: A wearable device that is wearable by a user and connectable with one or more aircraft related systems, a device system comprising a plurality of such wearable devices, and an aircraft comprising such a device system. The wearable device that is connectable to one or more aircraft related systems comprises a system interface via which the wearable device is connectable to one or more aircraft related systems, and a control unit configured to communicate with at least one of the one or more aircraft related systems via the system interface.

Abstract: An aircraft galley cart bay door includes a door main structure having an inwardly facing peripheral inner edge with an inner surface, and a surface seal on the inner surface of the inwardly facing peripheral inner edge of the inner wall. A substantial majority of the main structure of the door is formed from a high strength molded carbon fiber composite material. The door main structure may optionally define a recess, and insulation material can be disposed in the recess defined by the main structure of the door.

Abstract: A forward concave trapezoidal seating system and methods are presented. Trapezoidal seats comprise a front side smaller than a rear side. The trapezoidal seats are aligned in a forward arc from a straight seat to a most-angled seat. A straight side of the straight seat is configured to substantially align with a center line of an aircraft fuselage. A most-angled side of the most-angled seat is angled inboard relative to the straight side, and the most-angled seat is outboard of the straight seat. A side unit is coupled to the most-angled side and supports the trapezoidal seats.

Abstract: Structure mounted airbag assemblies and associated systems and methods are described herein. An airbag system configured in accordance with an embodiment of the present disclosure can include, for example, a housing having a cavity and an opening in communication with the cavity, an airbag assembly within the cavity, and an inflator operably coupled to the airbag assembly. The airbag assembly can include an airbag configured to deploy through the opening of the housing during a crash event. The airbag system can further include a door removably positioned across the opening and configured to move away from the opening during airbag deployment. The housing can be affixed to an interior portion of an aircraft, forward of and offset from an aircraft seat.

Abstract: A system includes an inlet line configured to receive a medium flowing from a low-pressure location of an engine to a chamber, a plurality of heat exchangers configured to receive the medium from the inlet line, and a valve located upstream from the plurality of heat exchangers. The valve is configured to divide in parallel the medium across at least a first heat exchanger and a second heat exchanger of the plurality of heat exchangers. A recirculation air system is configured to supply a recirculation.

Abstract: An environmental control system includes an air supply system coupled to an aircraft. The air supply system includes an external air supply device coupled to the aircraft and a supply duct coupled in flow communication to the external air supply device. An air supply outlet is coupled in flow communication to the supply duct and in flow communication with an occupancy zone and/or a floor distribution section. An air recirculation system is coupled to the floor distribution section. The air recirculation system includes a recirculation supply device coupled to the aircraft and a recirculation duct coupled in flow communication to the recirculated supply device and coupled to the floor distribution section. A recirculation outlet is coupled in flow communication to the recirculation duct and in flow communication with the recirculation zone and/or the floor distribution section.

Abstract: Apparatuses for and methods of deicing aircraft surfaces, engine inlets, windmill blades and other structures. Deicing apparatuses can comprise at least one standoff coupled with an actuator and a first region of an inner surface of a skin. A standoff can act as a moment arm and can create efficient, tailorable skin bending and acceleration, breaking an ice to skin bond. Integral as well as modular leading edges can comprise deicing apparatuses.

Abstract: A system and method for resisting an uncontrolled descent or uncontrolled flight condition of an aerial vehicle, the system including a parachute having shroud lines attached to a canopy, a housing to store the parachute, an inflatable tube that attaches to and is stored in the housing, the tube having a distal end with a connector that connects to the shroud lines, and a source of fluid that couples to the tube and selectively introduces fluid into the enclosed interior of the inflatable tube to inflate the tube and force the distal end of the tube and the attached parachute out of the housing and away from the aerial vehicle, wherein the tube tethers the parachute to the aerial vehicle.

Abstract: In order to optimize the bulk of a primary structure of an aircraft engine attachment pylon, and to favor the installation of the engine as close as possible to the wing element, the disclosure herein provides an aircraft assembly comprising a wing element, a turbofan engine and an engine attachment pylon, the engine comprising a rear part arranged under the wing element equipped with a wing structure, the pylon comprising a primary structure for transmitting loads from the engine to the wing structure, this primary structure comprising a pylon box, and the assembly also comprising an attachment for attaching the primary structure to the engine. According to the disclosure herein, the wing structure comprises two wing boxes that follow one another in a wingspan direction of the wing element, and the pylon box is arranged between these boxes and fixed to each of the latter.

Abstract: In order to allow better introduction of forces into the box section of an aircraft engine attachment pylon, the subject matter herein discloses a pylon including a primary structure forming a box section on the outside of which a body of the engine attachment is arranged, the latter also being equipped with shackles that are articulated on the body and can be articulated on the engine. According to the disclosure herein, the body has, at at least one of its ends, a one-piece fitting including a first joining portion on which one of the shackles can be articulated, and also a second joining portion that is fixed to the box section and passes into the latter.

Abstract: An aircraft controller includes a memory for storing instructions. The instructions are operable to cause the controller to perform a thrust balancing method and ensure a balanced thrust output from the aircraft. The thrust balancing method includes comparing an aircraft control surface setting in a cruise flight mode with the aircraft control surface setting in a flight idle mode of operations, thereby isolating an asymmetric thrust component of the aircraft control surface settings and determining an asymmetric thrust bias based on the isolated asymmetric thrust component of the aircraft control surface settings.

Abstract: An intake for feeding air to an engine of an aircraft includes an opening for sucking in air, which opening faces in the direction of movement of the aircraft; and an air duct between the opening and the engine, which air duct is curved such that an impact region is arranged in the air duct after the opening in relation to the direction of movement of the aircraft. An object flying into the opening contacts the impact region. The impact region has a penetration region, which is designed to be penetrated by the impinging object.

Abstract: Display systems, controllers, and methods are provided. A display system for an aircraft includes a display unit, an input device, and a controller. The controller is communicatively coupled with the display and the input device and is configured to retrieve an electronic checklist that includes a plurality of tasks including an annotated task associated with at least one of a note, a warning, a caution, and task information. The controller is further configured to hide from view the at least one of the note, the warning, the caution, and the task information in an image of the electronic checklist based at least in part on viewing criteria. The controller is further configured to generate a signal that causes the display unit to visually present the image.

Abstract: An improved aircraft display system and method that generates an aircraft orientation cue are provided. The aircraft orientation cue may be displayed in a variety of panoramic and landscape displays, and on head up and on head down display. The aircraft orientation cue has a symbolic form sufficient to visually convey, simultaneously, and in a predetermined manner, each of the AOA, roll, and yaw of the ownship A/C.

Abstract: A ground illumination aircraft light unit has an operating light emission distribution for illuminating a ground area below an aircraft, wherein the ground illumination aircraft light unit is configured to be mounted to an underside of an aircraft fuselage, and wherein the operating light emission distribution includes a straight downward emission direction normal to the ground area and covers a solid angle of illumination around the straight downward emission direction, wherein the solid angle of illumination is at least 1.3 ? sr.

Abstract: A method of producing an assembly tool (60) for assembling an assembly (6), the method comprising: providing at least a portion of a jig frame (62); fixing support plates (65) to the jig frame (62); machining the one or more support plates (65) such that a surface of each of the support plates (65) lies in a common plane (130); positioning the jig frame (62) such that the machined surfaces of the support plates (65) contact with a supporting surface (138); fixing pickup device mounting plates (140a, 140b) to the jig frame (62); machining, with respect to the supporting surface (138), the pickup device mounting plates (140a, 140b) such that a surface of each mounting plate (140a, 40b) has a respective predetermined position and orientation with respect to the supporting surface (138); and fixing, to the machined surfaces of the mounting plates (140a, 140b), a respective pickup device (66-72).

Abstract: A spacecraft operating in a low earth orbit having an altitude in the range of 160 to 800 km has a main body that includes heat dissipating electrical equipment and an earth-facing payload. Control surfaces on the spacecraft are articulated so as to: provide three-axis attitude control to the spacecraft main body using aerodynamic drag effects, such that the earth-facing payload is maintained in a selected orientation with respect to the earth; and control one or both of orbit altitude and period by articulating the control surfaces so as to regulate an amount of aerodynamic drag. The control surfaces include a first control surface disposed, in an on-orbit configuration, on a boom, the boom being mechanically coupled with the main body, and with one or both of a solar array electrically coupled with the electrical equipment and a thermal radiating array thermally coupled with the electrical equipment.

Abstract: A heat transfer assembly (HTA) includes an equipment panel having a first longitudinal length and a first radiator panel that is coupled to one of an east end and a west end of the equipment panel. The first radiator panel is longer in the longitudinal direction than the equipment panel and has least one longitudinal heat pipe. The HTA also includes at least one flexible heat pipe having a first rigid tube coupled to the equipment panel, a second rigid tube thermally coupled to the first longitudinal heat pipe, and a flexible tube coupled between the first and second rigid tubes. The equipment panel is configured to retain an equipment module in thermal contact with the first rigid tube.

Abstract: A core element for use with an inflatable or expandable spacecraft is claimed. The core element has a plurality of panels connected by hinges so that the core element can be packed into a smaller volume for loading into a launch vehicle. Upon deployment in space, the core element can be unpacked and can enclose a larger volume than that in the packed state. Multiple core elements can be used to cover a spacecraft to a desired degree.

Abstract: Dosing heads for apparatus for dispensing a defined amount of dry powder concurrently to a plurality of spaced apart dose receiving containers include a plurality of spaced apart elongate channels having a channel length with an upper end defining an entry orifice and a lower end defining an exit port. In use, the dosing heads are aligned with a dry powder bed residing above and in communication with the dosing head and at least one vibration source in communication with the dosing head channels configured to controllably apply a vibration flow signal. When the vibration flow signal is applied to the dosing head channels, dry powder from the dry powder bed flows through the elongate channels and out the exit port and when the flow signal is removed, dry powder does not flow through the dosing head elongate channels.

Abstract: The invention relates to a method and to a packaging plant which allows for a high degree of automatization of the packaging of individual product packages into shipment containers of different sizes and which is at the same time highly reliable and according to this method, each one of the product packages is assigned a conveyance tracking clock information, including information about the type of product package, its respective conveyance track, its conveyance speed, and its predetermined position and orientation within the shipment container for the specific shipment order.

Abstract: A method and apparatus for packaging patties or other similarly shaped items into a flexible pouch. The method comprising the steps of stacking a plurality of patties by a stacker, the patties stacked on top of one another, lowering the plurality of patties into a flexible pouch, vacuuming the air out of the flexible pouch to seal the pouch, the vacuum creating an air tight seal and forming a pair of frangible or solid seals in the pouch, the frangible seals positioned adjacent to the plurality of patties. The apparatus for packaging patties into a flexible pouch, the apparatus comprising a stacker, a patty holder, a vacuum is further positioned adjacent to the patty holder, the vacuum operable to remove the air from the flexible pouch. A frangible seal creator is also provided operable to create a frangible seal on the flexible pouch.

Abstract: An oral pouch product having a soft edge includes an inner filling material enclosed inwardly of at least one seam between opposed layers of porous pouch wrapper. The at least one seam is separated from the periphery of the porous pouch wrapper by an unbonded area of the opposed layers so as to form a soft edge of the pouch wrapper.

Abstract: A drug packaging device is provided in which both sheets are easily connectable to each other with a simple construction. A working plate having a first portion for temporarily fixing an end portion of a sheet remaining at a drug filling unit side, and a second portion for temporarily fixing an end portion of a new sheet are provided. The end portions of the respective packaging sheets which are temporarily fixed at the first portion and the second portion are connectable to each other.

Abstract: A tool and method for puncturing a lid of a vacuum sealed bottle to release the vacuum and allow easy opening. A point extends down from the tool, and force may be exerted against the tool by the palm or thumb of a user causing the point to penetrate the lid. The point preferably extends between 3/16 inches and 1/16 inches down from the handle, and more preferably about 3/16 inches. In some embodiments the tool is mushroom shaped having a wider round or oval upper portion for grasping and a narrower lower portion centered under the upper portion of the handle, the point extending down from the lower portion.

Abstract: Tight seal system for the packaging of products comprising a transverse welding station (14) of packaging sheets comprising: a first pair of discs (100) connected centrally to a first axis (101); said first pair of discs (100) rotating about said first axis (101); at least one first bar (102, 103) is positioned peripherally between said first pair of discs (100); a first welding jaw (111) is associated with said at least one first bar (102, 103); said first bar (102, 103) rotating so that said first jaw (111) is always facing in the same direction; a second pair of discs (130) connected centrally to a second axis (131); said second pair of discs (130) rotating about said second axis (131); at least one second bar (132, 133) is positioned peripherally between said second pair of discs (130); a second welding jaw (136) is associated with said at least one second bar (132, 133); said second bar (132, 133) rotating so that said second jaw (136) is always facing in the same direction; said first jaw (111) and said

Abstract: A machine for applying tubular film to products includes a mandrel assembly about which tubular film is passed and a film cutter for cutting the tubular film into sleeves sized for application to containers. The mandrel assembly includes a sleeve section located below the film cutter and about which a sleeve length portion of the tubular film extends prior to each film cutting operation of the film cutter to produce a cut sleeve. A sleeve ejection arrangement includes a rotatable ejector wheel disposed along the sleeve section of the mandrel assembly.

Abstract: A fuel additive bottle has a neck and thread pattern that allows insertion into a capless fuel system so the bottle's contents can be poured by gravity into a fuel tank. The neck of the bottle is elongated and has a diameter of approximately 0.854?, and the novel thread pattern includes thread interruptions that form at least one threadless path. In use, the spring loaded tabs of a capless fuel system are depressed by the threadless path portion of bottle, thereby triggering the self-sealing mechanism to open, so the fluid receiving aperture is exposed. The use of the threadless paths facilitates the safe and easy entry and removal of the bottle from the capless fuel system.