Abstract: A suspension assembly adapted for use in a snowmobile having a closed-loop track includes at least one ground contact engaged with the closed-loop track. An elongated swing arm is angularly disposed in the closed-loop track and extends between a front end portion adapted to be coupled to the chassis, and a rear end portion coupled to the at least one ground contact. A front resilient member is disposed in the closed-loop track and has an upper end pivotably coupled to the front end portion of the swing arm, and a lower end pivotably coupled to the at least one ground contact. A rear resilient member is disposed in the closed-loop track and has an upper end adapted to be pivotally coupled to the chassis, and a lower end pivotally coupled to the at least one ground contact. A pivot arrangement is connected to the swing arm for permitting at least rotation of the swing arm about a pivot axis extending longitudinally of the at least one ground contact.

Abstract: A fluid shield assembly for preventing fluid from entering a bow of a boat includes a panel that has an outer edge extending between a front side and a back side of the panel. The panel has a pair of slots each extending downwardly from a top side of the outer edge of the panel. The slots are evenly spaced apart from a middle of the top side of the outer edge of the panel to define the door portion of the panel. Each of a plurality of first fasteners engages a boat such that the panel is retained on a bow of the boat. The panel inhibits a fluid from entering the bow of the boat. The door portion of the panel is positioned over a door in the boat to selectively cover and expose the door in the boat.

Abstract: A system and method for offshore loading of large cargo vessels, or motherships. The system includes a plurality of mooring stations, which may be mooring buoys, positioned in an offshore mooring field proximal an onshore cargo loading facility. A mothership is positioned within the mooring field and moored via bow and stern lines to two or more different mooring stations. Environmental data, including wind, wave, and current data, as well data regarding the physical characteristics of the mothership and movement (roll/pitch/heave) of the mothership are collected by remote transmitting and sensing devices. This data is processed by numerical analysis in a digital processor, namely a computer, to determine optimum mooring line length and tension, and mooring station locations, in order to minimize mother ship movement and create an optimum “lee” loading area adjacent the mothership. Cargo is transferred to the mothership by a trans-shipper moored to the mothership.

Abstract: A recovery system and method for recovering a deployed vessel having a rotatable support coupled with a stored recovery assembly, including a release unit, line, deployment weight, and drag device on the deployed vessel. A recovery vessel can have a hoist with a coupling element, such as a grapple. For recovery, the recovery assembly can be deployed from the deployed vessel. The drag device can assist in floating and/or maintaining a taut line, especially when the vessel is downwind of the drag device. The coupling element from the recovery vessel can couple with the taut line. Once coupled, the recovery vessel can raise the coupling element with the line, which can rotate the rotatable support to a lifting position above a center of gravity of the deployed vessel. The recovery vessel can then lift the deployed vessel vertically out of the water to a storage position.

Abstract: A frame of a water jet propulsion unit arranged to be installed and sealed into an installation opening of a boat. The water-jet propulsion unit includes an impeller and the boat has a counter-sealing surface to which the frame is attached. The frame includes a flow channel to guide water to the impeller. The flow channel has a top with a maintenance opening. The maintenance opening is positioned to permit servicing the impeller. A first sealing surface forms a first closed loop to attach the water-jet propulsion unit tightly to the counter-sealing surface of the boat. A second sealing surface forms a second closed loop arranged to attach the water-jet propulsion unit to the boat. The first and second closed loops permit the maintenance opening of the frame to be alternatively locatable respectively outside or inside the stern of the boat in dependence on alternative configurations of the installation opening of the boat.

Abstract: An improved barge system comprises a barge with a connecting system built into the barge. The connecting system includes several recessed areas about the periphery of the barge with upper and lower rails about the peripheral edges of the barge. A vertical post having a lower connecting member and an upper connecting member is attached within the recessed area for rotation into position to connect the upper and lower connecting members to adjacent upper and lower rails on the adjacent barges. Wedge blocks attached outwardly on adjacent rails each receive a wedge in the gap between the respective wedge block and a connecting member. Spacer blocks improve parallel alignment of the connected barges.

Abstract: A universal vertical storage and display system for multiple types, sizes and shapes of sport boards. The embodiment is wall or other vertical surface mounted. The display system comprises prefabricated bracket components which through their various arrangement, configuration and orientation exhibit sport boards in a vertical position with the primary deck face parallel to the wall, oriented inward or outward. The embodiment displays sport boards as a work of art in a safe and aesthetically pleasing manner. The display system is suitable for indoor or outdoor applications.

Abstract: A ship drive having a drive machine, a transmission, a propeller shaft that is driven by the transmission and a mounting arrangement by which the ship drive can be secured to a hull of a ship. The drive machine and the transmission are connected to one another by a connecting flange and are arranged inside the hull of the ship. A first mounting point, which is designed as a pivot bearing relative to the rotational axis of the propeller shaft, is arranged in such a manner that a bending moment, produced by the propeller thrust and by the weight of the drive machine and the transmission, is optimized at the connecting flange.

Abstract: This invention relates to a device and method of reducing the azimuthal torque acting on a pulling pod unit or azimuth thruster (1) having a rotary pod housing (2) with a substantially vertical slewing axis (3) and a fixed downwardly directed first fin (4) carried by the pod housing (2) abaft the slewing axis (3), wherein said first fin is in the form of an elongated strip-shaped vane (4) and extends abaft the slewing axis (3) along the pod housing (2) to the vicinity of a rear end (5) thereof.

Abstract: Embodiments of the present invention provide mechanical sail systems, methods, apparatus, and code which allow use of the Magnus effect to provide thrust to a ship. In some embodiments, a mechanical sail system is provided which includes a silo, positioned below a deck level of a ship, a lift carriage, mounted within the silo, and supporting a first sail cylinder and a second sail cylinder, and at least a first drive motor coupled to a control system for selectively positioning the lift carriage within the silo, the control system operable to control the at least first drive motor to position the lift carriage at a top position within the silo to deploy the first and second sail cylinders.

Abstract: A hand grip is disclosed. The hand grip has a cross-sectional profile and an axial extent delimited by opposing ends thereof, in which a resilient extension portion is provided at one side of the cross-sectional profile, and which extends substantially the length of the axial extent.

Abstract: A vessel propulsion apparatus includes a water pump that is driven by an engine, and supplies water from an water inlet to the engine via a cooling water supply passage. The vessel propulsion apparatus includes an auxiliary cooling passage branching from the cooling water supply passage to extend to an oil pan. A water pressure control valve disposed at a branch position from the cooling water supply passage to the auxiliary cooling passage limits the flow rate of water flowing to the auxiliary cooling passage when a water pressure inside the cooling water supply passage is less than a set pressure. The water pressure control valve is configured to allow a portion of the water inside the cooling water supply passage to flow to the auxiliary cooling passage when the water pressure inside the cooling water supply passage is the set pressure or more to maintain the water pressure to be less than the set pressure while supplying water to the oil pan via the auxiliary cooling passage.

Abstract: A lift assembly for use during inflation of a balloon envelope is provided. The lift assembly includes a plate structure that has a set of cavities. Each cavity includes one or more openings passing through the plate. One or more pistons are coupled to the plate through at least one of the openings of each cavity in the set of cavities. Each piston has a hollow tube portion projecting lengthwise from the at least one opening, a flange attached to the hollow tube portion and a grabber portion in communication with the flange. The grabber portion includes a plurality of bearings for grabbing a stud attached to an apex of the balloon envelope. A handle portion is coupled to the plate. The handle is arranged to lift the balloon envelope when the bearings have grabbed a given stud.

Abstract: A control system for terminating flight of a balloon having a balloon envelope is provided. The control system includes a shuttle that has one or more cutting blades. The cutting blades are configured to cut open the balloon envelope. A tubular track is attached to a section of the balloon envelope. This tubular track has a guiding portion arranged to receive and guide the shuttle along the track. The control system includes a type of releasable ballast attached to the shuttle. When the ballast is released, the ballast is configured to move the shuttle along the tubular track in order to cause at least one of the cutting blades to cut open a portion of the balloon envelope. This allows lift gas to escape from the balloon envelope.

Abstract: A system for filling balloons with lift gas is provided. The system includes apparatus for use with a balloon envelope of a balloon. This apparatus includes a main body having first and second portions. The first portion has a fill port and a hollow tube portion in communication with the fill port. The second portion has a surface and is insertable into a predefined opening in the balloon envelope. The surface of the second portion is configured to attach to an inner portion of the balloon envelope when the second portion is inserted in the predefined opening.

Abstract: An aircraft wing includes a rib attached by a joint to a tubular spar that varies in cross sectional shape during flight. The joint includes a ring attached to the tubular spar, and pivot pins connecting the ring with the rib. The pivot pins allow relative movement between the rib and the tubular spar as the tubular spar varies in cross sectional shape.

Abstract: An assembly to support a wing leading or trailing edge device during deployment and retraction of the device includes a fixed support member attachable to the support structure of an aircraft wing, an intermediate link arm having one end pivotally mounted for rotation relative to the support member about a first axis and, a primary link arm having a first end pivotally mounted to the opposite end of the intermediate link arm for rotation relative to the intermediate link arm about a second axis. A second end of the primary link arm is for attachment to the device via a bearing element so that the device can move relative to the primary link arm in any direction when the intermediate and primary link arms rotate about the first and second axes, respectively, during deployment or retraction of the device from the aircraft wing.

Abstract: A new ring cam and ring cam assembly, developed for providing more diverse dynamic pitching schedules for cyclorotor blades, particularly for providing both cyclic and collective pitch control, can be used for any apparatus where dynamic variation of cam controlled movement is needed. The new ring cam has its cam surface on the inside of a ring, the cam surface defining a plurality of different cam profiles which can be dynamically chosen and applied according to need. The different cam profiles are provided by different configurations and by combinations of those configurations. One configuration uses a plurality of adjacent different cam profiles across the inside width of the ring, so that a cam follower follows different cam profiles as it moves across or relative to the cam surface. Another configuration moves a center axis of the ring in relation to the axis of rotation of the cyclorotor, or other rotating device, to dynamically change the effective cam profile.

Abstract: A method and apparatus for managing a flow of a fluid. The fluid is received at an input port of a structure. The fluid is sent through a chamber in communication with the input port. The fluid is caused to flow from the chamber and out of an output port in a direction that changes with a frequency based on an application of pressure pulses in the chamber.

Abstract: A winglet system for an aircraft wing may include an upper winglet and a lower winglet mounted to a wing tip. The upper winglet root chord and the lower winglet root chord may each have a length of no greater than 100 percent of the wing tip chord. The lower winglet may have a static position when the wing is subject to an on-ground static loading. The lower winglet may be configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading.

Abstract: An aircraft landing gear including wheels and a fairing arranged to be moveable between a first and a second configuration, wherein in the first configuration the fairing is arranged to shield an element of the landing gear from incident airflow and wherein in the second configuration the fairing is arranged to deflect debris or spray propelled from one or more of the wheels.

Abstract: An aircraft landing gear self-orients so to align itself within a plane parallel to the plane defined by the aircraft's roll and yaw axis. A nose gear of a tricycle landing gear configuration includes the ability to not only caster 360 degrees but also self-orient itself to be aligned parallel with the plane defined by the aircraft's roll and yaw axis once removed from any interaction with the ground. A simple and efficient mechanical design provides the landing gear with a substantially constant centering torque that neither impedes nor impairs ground movement yet returns the nose gear to a proper alignment for retraction and stowage.

Abstract: An elastic device for coupling between an aircraft landing gear wheel and a coaxial motorization member for motorization of the wheel. The elastic device comprises a plurality of arms to be rotationally coupled to the motorization member adjacent a first radially inner end and which are to be linked to the wheel adjacent their radially outer opposite end, the arms being substantially rigid in a plane perpendicular to the rotational axis of the wheel and flexible in directions substantially transverse to the plane.

Abstract: A power plant (10) having a main gearbox (20), a turbine engine (40), and a heat exchanger (60), the main gearbox (20) including a substantially vertical rotor mast (21). The main gearbox (20) comprises at least a rotary speed reduction stage arranged in a flat casing (22), and a pylon (23). The turbine engine (40) has an engine casing (42) with an outlet shaft projecting from said engine casing (42) and penetrating into said flat casing (22), said outlet shaft (41) being substantially parallel to the rotor mast (21), said engine casing (42) being offset longitudinally from the pylon (23) and not being in contact with the pylon (23). The heat exchanger (60) extends longitudinally behind said turbine engine (40), while, on the contrary, said rotor mast (21) is situated longitudinally in front of said turbine engine (40).

Abstract: An aerial vehicle includes at least one wing, a plurality of thrust producing elements on the at least one wing, a plurality of electric motors equal to the number of thrust producing elements for individually driving each of the thrust producing elements, at least one battery for providing power to the motors, and a flight control system to control the operation of the vehicle. The aerial vehicle may include a fuselage configuration to facilitate takeoffs and landings in horizontal, vertical and transient orientations, redundant control and thrust elements to improve reliability and means of controlling the orientation stability of the vehicle in low power and multiple loss of propulsion system situations. Method of flying an aerial vehicle includes the variation of the rotational speed of the thrust producing elements to achieve active vehicle control.

Abstract: One variation of a method for imaging an area of interest includes: within a user interface, receiving a selection for a set of interest points on a digital map of a physical area and receiving a selection for a resolution of a geospatial map; identifying a ground area corresponding to the set of interest points for imaging during a mission; generating a flight path over the ground area for execution by an unmanned aerial vehicle during the mission; setting an altitude for the unmanned aerial vehicle along the flight path based on the selection for the resolution of the geospatial map and an optical system arranged within the unmanned aerial vehicle; setting a geospatial accuracy requirement for the mission based on the selection for the mission type; and assembling a set of images captured by the unmanned aerial vehicle during the mission into the geospatial map.

Abstract: One variation of a method for imaging an area of interest includes: within a user interface, receiving a selection for a set of interest points on a digital map of a physical area and receiving a selection for a resolution of a geospatial map; identifying a ground area corresponding to the set of interest points for imaging during a mission; generating a flight path over the ground area for execution by an unmanned aerial vehicle during the mission; setting an altitude for the unmanned aerial vehicle along the flight path based on the selection for the resolution of the geospatial map and an optical system arranged within the unmanned aerial vehicle; setting a geospatial accuracy requirement for the mission based on the selection for the mission type; and assembling a set of images captured by the unmanned aerial vehicle during the mission into the geospatial map.

Abstract: A device for distributing granular material to a target area from an aircraft is provided. The device includes one or more electric sifters, and each of the one or more electric sifters includes a motor to distribute the granular material on the target area and a screen on the bottom surface of the electric sifter. The granular material is stored in the one or more electric sifters. The screen includes a first portion and a second portion. The first portion allows the granular material to pass through the screen to the target area. The second portion prevents the granular material from passing through the screen. The device also includes a circuit to control the motors, one or more power sources to power the motor and the circuit, and an interface for a human operator to control the circuit.

Abstract: A remotely-piloted aircraft for distributing beneficial insects on a target area is provided. The aircraft includes an enclosure, including a top lid, one or more internal compartments, a door for each of the one or more internal compartments, and an actuator to open and close each of the doors. The aircraft also includes a circuit to control the actuators, a wireless receiver, coupled to the circuit, to receive commands to open and close the doors, and one or more power sources to power the actuators and the wireless receiver. An operator controls the aircraft and the circuit with at least one of a wireless transmitter and an uploaded program in the circuit. When the wireless receiver receives a command to open a door, the circuit controls an actuator corresponding to the door. The actuator opens the door, and the beneficial insects are distributed from internal compartments.

Abstract: Embodiments described herein may help to provide medical support via a fleet of unmanned aerial vehicles (UAVs). An illustrative UAV may include a housing, a payload, a line-deployment mechanism coupled to the housing and a line, and a payload-release mechanism that couples the line to the payload, wherein the payload-release mechanism is configured to release the payload from the line. The UAV may further include a control system configured to determine that the UAV is located at or near a delivery location and responsively: operate the line-deployment mechanism according to a variable deployment-rate profile to lower the payload to or near to the ground, determine that the payload is touching or is within a threshold distance from the ground, and responsively operate the payload-release mechanism to release the payload from the line.

Abstract: A toilet arrangement for a vehicle includes a first toilet compartment, an adjacent second toilet compartment and a partition wall situated between the first toilet compartment and the second toilet compartment, wherein the partition wall is movably supported and designed for being transferred into an open position, in which the partition between the first toilet compartment and the second toilet compartment is removed. This makes it possible to convert two relatively small toilet compartments into a larger toilet compartment that is suitable for use by persons with limited mobility.

Abstract: A method of regulating the de-icing of a leading edge of an aircraft includes regulating the flow of air used for de-icing by at least a first regulator valve in accordance with two regulation levels, a first regulation level corresponding to the regulated position of the first regulator valve and a second regulation level corresponding to the fully open position of the first regulator valve. A de-icing device enables implementation of the regulation method.

Abstract: A method for deicing an aerostructure includes driving a sensing current through a heater element coated to an aerostructure, the heater element having a resistance that is temperature dependent. A resistance of the heater element is monitored. It is determined whether there is icing at the heater element using the monitored resistance of the heater element. A melting current is driven through the heater element when it is determined that there is icing at the heater element.

Abstract: A fuselage mounted gas turbine engine installation the installation includes at least one propeller stage and a gas turbine core arranged in use to drive the propeller stage. The core is external to the fuselage and the rotational axes of the core and propeller stage are offset with respect to each other.

Abstract: An autothrottle retard initiation method includes receiving an aircraft's ground speed, receiving the aircraft's vertical speed, determining autothrottle retard initiation height based on the aircraft's ground speed, the aircraft's vertical speed, and an aircraft vertical landing speed factor, receiving the aircraft's height above ground, and initiating autothrottle retard when the aircraft's height above ground and the autothrottle retard initiation height are equal.

Abstract: The present invention relates to a method and to an associated fuel metering system for balancing the power delivered by two aircraft turboshaft engines by determining first and second limiting margins of the engines (M1, M2) which are transformed into first and second power margins. Thereafter, the values of the first and second power margins are compared in order to determine a primary difference between said first and second power margins. Finally, the engine having the greater power margin is accelerated in order to balance the first and second engines in power by minimizing the primary difference to as great as extent as possible.

Abstract: An aircraft fuel tank vent opening having a liquid separation nozzle, the liquid separation nozzle and the opening dimensioned such that migration across the liquid separation nozzle to the underside of a wing, of fuel escaping from the vent opening, is inhibited during normal operating conditions.

Abstract: An on board inert gas generation system receives cabin air, or air from another relatively low pressure source, passing a portion thereof through an energy recovery turbine to ambient to extract power which is used to provide all, or part of, the energy required to drive a positive displacement compressor to compress another portion of cabin air to increase the pressure thereof to be suitable for supply to an air separation module.

Abstract: A method for providing one or more aircraft with weather data during flight includes generating a weather model using a source of weather data. The weather model incorporates flight operations information and performance requirements. The method includes generating a weather message from the weather model. The weather message is generated in a format that is compatible with the aircraft. The method also includes transmitting the weather message to the aircraft during flight of the aircraft.

Abstract: A computer-implemented flight data monitoring method is provided for monitoring flight data, for example flight data obtained by a flight data recorder or quick access recorder on an aircraft. The method comprises receiving input flight data, performing flight data validation on the input flight data to generate validated flight data, and performing flight data analysis on the validated flight data to detect at least one predetermined type of flight event. The events may be useful for generating an aircraft safety report, for example. By validating the data before performing the analysis, the number of events which are falsely detected based on invalid or unreliable data can be reduced.

Abstract: A method for monitoring degradation of an on-board device of an aircraft includes comparing an abnormality score obtained for a given aircraft flight to a decision threshold and emitting an alarm when the decision threshold is exceeded.

Abstract: A static discharge device includes a body an an electrical path carried in the body for discharging static electricity. Carried on the body is visual indicia indicating a present operational status of the electrical path to discharge static electricity effectively. The visual indicia is observable to an airplane operator or technician to quickly determine the operational or non-operational status of the static discharge device.

Abstract: Systems and methods are provided for swapping the battery on an unmanned aerial vehicle (UAV). The UAV may be able to identify and land on an energy provision station autonomously. The UAV may take off and/or land on the energy provision station. The UAV may communicate with the energy provision station. The energy provision station may store and charge batteries for use on a UAV.

Abstract: According to one embodiment, a system for measuring coupling misalignment of a rotorcraft drive shaft includes a reference device and a sensor. The sensor is configured to receive a signal from the reference device indicative of a distance between the reference device and the sensor. The reference device and the sensor are configured to be disposed on opposite sides of a flexible coupling coupled to the drive shaft and disposed between the engine and the pylon. The flexible coupling is configured to rotate with the drive shaft and comprises a flexure portion configured to flex in response to a difference in alignment between the engine and the pylon. A misalignment measurement system may be configured to generate a misalignment value in response to the signal.

Abstract: A global network is described for accessing aircraft remotely via a wide area network. Aircraft flight and operational data stored on the aircraft may be directly accessed via remote workstation or downloaded by centralized automatic processes for later analysis and diagnosis.

Abstract: A plurality of orbiting solar generators stay in constant touch. They can be congregated rapidly in space at any desired secret location. Once congregated they all discharge their energy to a death star. This death star could be a newly launched ICBM. A laser generator uses this newly acquired energy on the death star to project a non-nuclear laser ray to a target. The target could be a city, a ship or a satellite. In the event of an asteroid approaching earth, this system could destroy an asteroid. In peacetime the orbiting solar generators could supply electric power to an earth based power grid.

Abstract: A system and method for controlling de-orbit of a spacecraft is presented. Embedded command modules are commanded directly from a central command and telemetry module. Latch valves, thruster valves, and solar wing drive of the spacecraft are operated in response to inputs to the embedded command modules. The spacecraft is maneuvered to a safe disposal orbit in response to commands from the central command and telemetry unit.

Abstract: A nuclear thermal propulsion rocket engine. A reactor is provided to receive a fissionable fuel and a propellant fluid. Fuel may be transported and injected using a carrier fluid. Carrier fluid for fuel may be hydrogen or an isotope thereof. Fuel may be plutonium or selected actinide. A neutron generator is provided, and utilizes an ion generator and a target container which extends into the reactor to hold a target material therein. Neutrons may be emitted almost omni-directionally by impact of ions from the ion generator on target material. Cooling of the target container may be provided by a cooling sleeve that receives and circulates a cooling fluid, and discharges the cooling fluid after it has been heated. Fuel injectors provide fuel through fuel injector valves regulated to cycle on and off to pulse output power of the rocket engine, by timing frequency and duration of fuel feed, and regulating injected fuel amounts, to regulate the energy released over discrete time periods.

Abstract: A directionally-controlled roll-out elastically deployable solar array structure is disclosed. The structure includes one or more longitudinal elastic roll out booms that may be closed section or open section to allow for efficient rolled packaging onto a lateral mandrel. A flexible photovoltaic blanket is attached to a tip structure and to a lateral base support structure, but remains uncoupled from the longitudinal booms. The solar array system may be stowed simultaneously into a rolled package comprised of the roll out booms and the flexible planar blanket together, or onto independent rolls. Alternatively, the system may be stowed by rolling the booms, and accordion Z-folding the hinged flexible photovoltaic blanket into a flat stack. Structural deployment is motivated by the elastic strain energy of the roll out booms, and several methods of deployment direction control are provided to ensure a known, controlled, and unidirectional deployment path of the elastically unrolling booms.

Abstract: A vial holder is provided to protect a user's hand from needle sticks. The holder includes a handle and a shield attached to a distal end of the handle. An opening is formed in the distal end of the handle to receive a vial. The vial is placed through the opening and into a passageway of the handle with the upper end of the vial exposed. A user grasps the handle which holds the vial in a stabilized manner. A needle may then safely approach the vial in which inadvertent slippage or movement of the needle results in contact with the needle against the shield and not contact with the user's hand.