Abstract: A cooling system for an outboard motor of a marine vessel is provided. The cooling system includes an oil sump housing having an inner housing wall and an outer housing wall. The inner housing wall defines a transmission mounting cavity, and the inner housing wall and the outer housing wall defines an oil containment cavity that at least partially surrounds the transmission mounting cavity. The cooling system further includes a first sprayer nozzle and a second sprayer nozzle. Both the first sprayer nozzle and the second sprayer nozzle are coupled to the oil sump housing and configured to spray cooling fluid within the transmission mounting cavity onto an inner surface of the inner housing wall.

Abstract: A marine vessel maneuvering system includes a propulsion device, a steering device, a forward/reverse drive switch, a steering wheel, a forward drive operator, a reverse drive operator, and a controller. The forward drive operator and the reverse drive operator are respectively located on one and the other sides of a pivot axis of the steering wheel, and are pivotable together with the steering wheel. The controller performs a forward drive propulsion control and a reverse drive propulsion control to set the propulsive force direction and control a magnitude of the propulsive force according to the operation of the forward drive operator and the reverse drive operator. The controller enables the forward drive propulsion control in a forward drive operation valid range. The controller enables the reverse drive propulsion control in a reverse drive operation valid range.

Abstract: An arched gutter that can be used to channel moisture within an aircraft can include an arched web including a plurality of laterally spaced arches. The plurality of arches impart a flexibility to the arched gutter such that the arched gutter has an increased resistance to fatigue cracking and other wear and damage resulting from, for example, parasitic loads due to high bending strains that are transferred to the arched gutter by a wing to which the arched gutter is attached during operation of the aircraft. An aircraft section and an aircraft including the arched gutter are also described.

Abstract: In one embodiment, an apparatus includes a collapsible workstation assembly to be used in a temporarily-mounted control system of an aircraft. The collapsible workstation assembly is mounted to a floor of the aircraft via one or more mounting plates and one or more adaptive floor plates. The collapsible workstation assembly includes a number of modules for display and user controls. Each of the modules are connected via hinges and hinge locks to be moved between a deployed position for use and a stowed position when not in use. The collapsible workstation assembly is further connected to an observer chair assembly and a temporary door plug.

Abstract: A bi-directional egress hatch for a passenger aircraft may allow passengers to rapidly and safely exit an overhead cabin of the aircraft onto the main deck, while allowing cabin crew to safely ascend into the overhead cabin if need be. Hatch panels may blend in with overhead bin doors and ceiling panels of the main cabin; the inner portions of the hatch panels (facing the overhead cabin) may include anti-skid portions and graspable handles for descending passengers. The hatch may be easily activated by a passenger with a single motion (or remotely activated, or autodeployed). Once activated, the hatch panels may swing open and a telescoping ladder may deploy from the inner portion to the main deck, remaining rigid once reaching the floor. Similarly, any barriers protecting the ladder from passengers in the overhead cabin may be released, granting access to the telescoping ladder.

Abstract: A windowed structure includes a body having a frame with an outer wall extending between a first end and a second end. An inner wall extends from the outer wall. The inner wall is connected to the outer wall at the first end to define a proximal joint of the body delimiting a window opening extending through the body. A window element covers the window opening and defines an outer window surface and an inner window surface. The window element has an overlap segment overlaying the outer wall and attached thereto. An unobstructed portion of the window element is defined between the overlap segment and is unobstructed by the frame between the proximal joint.

Abstract: An aircraft wing is provided with a shutter mechanism to close a cut-out opening in the leading edge of the wing when a leading edge wing slat associated with the wing leading edge is moved to a deployed condition.

Abstract: An aerodynamic structure comprising an aerodynamic surface. The aerodynamic surface is formed by a first part of the aerodynamic structure; a second part of the aerodynamic structure; and a sealed gap between the first part and the second part. The sealed gap contains a sealant material and a support material.

Abstract: An aircraft includes a wing and a rotor pod mounted to the wing. The rotor pod includes a body having a forward end and an aft end. A propeller is mounted to the body of the rotor pod at the forward end. A control surface is mounted to the body of the rotor pod between the forward and aft ends and extends outwardly from the body. The control surface is displaceable relative to the body between a first control configuration and a second control configuration to control an attitude of the aircraft. The control surface in the first control configuration is closer to the propeller than the control surface in the second control configuration.

Abstract: Aircraft nacelles having adjustable chines are described. An example apparatus includes a multi-segment chine coupled to a nacelle. The multi-segment chine includes a first segment and a second segment. The first segment is oriented along a fore-aft direction. The first segment is rotatable relative to the nacelle about an axis of rotation. The axis of rotation is substantially perpendicular to a plane of the first segment defined by an outer mold line of the first segment. The second segment is fixedly coupled to the nacelle. The second segment is oriented along the fore-aft direction. The second segment is substantially coplanar with the first segment.

Abstract: A mechanism for folding a rotor blade that is rotatably coupled to a blade cuff about a blade-fold axis between an extended position and a folded position. The mechanism includes a swash plate configured to translate relative to a mast, a pitch link rotatably coupled to the swash plate, a pitch horn rotatably coupled to the pitch link, a crank coupled to the pitch horn, and a link rotatably coupled to the crank and rotatably coupled to the rotor blade. The pitch horn and the crank being configured to commonly rotate relative to the blade cuff about a crank axis in response to translation of the swash plate, wherein the crank axis passes through the blade cuff.

Abstract: Methods and apparatus for enhancing aircraft flight control surface effectiveness via forced oscillation are described. An example control system of an aircraft includes a flight control surface, an actuator, and one or more processors. The actuator is configured to move the flight control surface. The one or more processors are configured to determine a current position of the flight control surface. The one or more processors are further configured to determine whether the current position exceeds a position threshold. The one or more processors are further configured to generate a forced oscillation signal in response to determining that the current position exceeds the position threshold. The one or more processors are further configured to command the actuator to move the flight control surface based on the forced oscillation signal.

Abstract: In some embodiments, a control manager is disposed between the rotor system and the flight control inceptor. The control manager is configured to receive control commands wirelessly from a ground control station, translate the control commands into one or more axes associated with the flight control inceptor, and transmit the translated control commands to the rotor system in place of the instructions received from the pilot via the flight control inceptor.

Abstract: A vehicle control surface, such as an aircraft horizontal stabilizer, is hydraulically controlled using solenoid operated valves (SOVs) controlling directional control valves and/or rate control valves with small numbers of ports, e.g. a four port three position directional control value and/or a four port two position rate control valve.

Abstract: An aircraft flight control system includes a first actuator attached to a wing main body, a horn arm configured to transmit an output of the first actuator to a control surface, and a second actuator that is a rotary actuator and attached to the control surface. At least one of the first actuator and the second actuator is an electromechanical actuator (EMA). A first end of the horn arm is coupled to an output terminal of the first actuator, and a second end of the horn arm is fixed to an output terminal of the second actuator. The second actuator is attached to the control surface such that a turning axis of the output terminal is parallel to or coincides with a fulcrum axis (hinge line) of the control surface.

Abstract: A system for shrinking landing gear includes a shock strut having a cylinder and a piston to be received by the cylinder. The system further includes a collar coupled to a brace linkage and the piston, a torque arm configured to resist rotation between the collar and the piston, and a shrink linkage coupled between the torque arm and the cylinder. The collar rotates relative to the cylinder in response to retraction of the landing gear. Rotation of the collar rotates the piston and the torque arm relative to the cylinder. The rotation of the collar relative to the cylinder forces, via the shrink linkage, the piston towards the aircraft attachment within the cylinder.

Abstract: A retractable landing gear assembly for an aircraft includes a leg mounted to airframe structure for rotation about a pivot axis. A stay assembly is provided for maintaining the landing gear assembly in a deployed, for example down and unlocked, configuration. The stay assembly has a linkage mechanism including a first stay and a second stay movable between a folded state and an unfolded state. Room that would otherwise be occupied within a landing gear bay may be freed up above the landing gear leg when in a stowed configuration by the stay assembly being unfolded but generally aligned with the length of the landing gear leg, with the stay assembly being mostly positioned beneath the leg.

Abstract: A method for designing and operating an aircraft nose landing gear wheel-mounted electric taxi system to move aircraft with optimal torque during a broad range of ground travel conditions. Electric taxi system components may be sized to produce optimal ground travel torque to move aircraft during the majority of aircraft ground travel conditions and operated to produce a maximum or breakaway torque to move the aircraft with the electric taxi system when a higher level of torque is required. Turning the nose landing gear wheels to a selected angle or through a range of angles simultaneously as the electric taxi system is operated produces the breakaway torque required to get the aircraft moving. When lower torque is needed, the aircraft may be driven with the nose landing gear wheels parallel to the longitudinal axis to produce optimal torque for electric taxi system-powered aircraft ground travel.

Abstract: A method of making an axle sleeve includes forming a main body comprising a cylinder and forming an expansion member whereby a diameter of the main body may be varied. The method includes cutting an inner helical cutout comprising a first slit defined through the main body and extending helically from an inner edge of the main body, cutting an outer helical cutout comprising a second slit defined through the main body and extending helically from an outer edge of the main body, forming an inner edge remaining portion comprising an annular section of the main body unbroken by the inner helical cutout, and forming an outer edge remaining portion comprising an annular section of the main body unbroken by the outer helical cutout.

Abstract: An aircraft landing gear assembly comprising: an axle having an axis, a wheel rotatably mounted on the axle to rotate about the axis, a brake arranged to selectively exert a braking torque on the wheel about the axis, a brake anchor structure having a substantially fixed position relative to the axle, a brake reaction linkage that mechanically couples the brake to the brake anchor structure, and a sensor comprising a sensor element arranged to detect a change in one or more physical properties of a component of the brake reaction linkage in order to determine a stress in the component due to the braking torque, wherein the sensor element does not contact the component.

Abstract: A vibration control assembly for an aircraft including a housing operatively coupled to the aircraft. Also included is a cage disposed within an interior region of the housing, the cage rotatable within the housing about a first axis. Further included is a gyroscope wheel disposed within the cage and rotatable about a second axis other than the first axis, wherein a controllable moment is imposed on the aircraft upon rotation of the gyroscope wheel to counter vibratory moments produced by the vehicle.

Abstract: An aircraft includes an airframe, an extending tail, a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly, and a translational thrust system positioned at the extending tail. The translational thrust system provides translational thrust to the airframe. An upper hub fairing is positioned at the upper rotor assembly. A lower hub fairing is positioned at the lower rotor assembly. A shaft fairing is disposed between the upper hub fairing and the lower hub fairing. The upper hub fairing is substantially sealed to the shaft fairing and the lower hub fairing is substantially sealed to the shaft fairing.

Abstract: A rotorcraft having a rotor system including a yoke, a plurality of grip assemblies, each of which is hingedly attach a rotor blade to the yoke, a plurality of flap stops, each flap stop attached to a respective grip assembly, a channel bounded by an upper and lower retaining surfaces, and a droop ring slideably disposed in the channel of the droop limiting system. The droop ring has a body with an inner surface, an outer surface, and a first end surface between the inner surface and the outer surface. The droop ring further has a first wear element removably disposed at the first end surface and extending above the first end surface and spaces the first end surface apart from the channel. Each flap stop is arranged to contact the outer surface of the droop ring and limit a downward droop of the respective rotor blade.

Abstract: A system for controlling an unmanned aerial vehicle (UAV) includes smart glasses and a remote controller. The smart glasses are configured to establish a first channel directly with the UAV, receive first person view (FPV) image data directly from the UAV through the first channel, and display the FPV image data. The remote controller is configured to establish a second channel directly with the UAV, and send a flight control instruction directly to the UAV through the second channel.

Abstract: An apparatus, method and system utilize an unmanned air vehicle (UAV) in order to support the definition and use of routes by bicyclists, pedestrians or scooters. With respect to defining a bicycle route a map database is accessed that represents roads segments in a geographic area. The map database contains map data that indicates attributes of the road segments. The bicycle route is then defined from an origin to a destination based upon the map data indicative of attributes of the road segments. In this regard, the bicycle route is defined to include one or more road segments that allow bicycle traffic unaccompanied by a UAV and one or more road segments for which bicycle traffic is unauthorized unless accompanied by a UAV. The bicycle route is subsequently caused to be provided to the bicyclist or a device accessible to the bicyclist.

Abstract: A grasp and release mechanism for carrying a load. The grasp and release mechanism includes a frame; a grasp mechanism attached to the frame and including plural permanent magnets configured to magnetically attach to a ferrous load; a release mechanism attached to the frame, wherein the release mechanism includes a drop plate; and an actuator mechanism attached to the frame and configured to apply a force F to the drop plate. The drop plate is configured to suddenly move relative to the frame to apply the force F to the load.

Abstract: Systems and methods for the automated aerial application of chemicals onto agricultural areas. Unmanned aerial vehicles (UAVs) are configured to selectively attach to modular sprayer payloads, each payload having a payload reservoir, a spray nozzle, a pump, and a battery. A ground station having landing pads for the UAVs is configured to coordinate and automatically fill at least one payload reservoir from a material tank and provide the payload to a given UAV. A control subsystem can determine a mission plan and command the UAV to selectively deliver the contents of the payload reservoir to at least a portion of one or more agricultural areas.

Abstract: Zone-based unmanned aerial vehicle landing systems and methods are provided herein. An example method includes establishing a plurality of operational zones, each of the plurality of operational zones being associated with a range of altitudes, guiding an unmanned aerial vehicle (UAV) through each of a plurality of operational zones to land the UAV on a target location using sensors, wherein the sensors are configured to sense a distance between the UAV to the target location, further wherein portions of the sensors are configured for use at different altitudes, and determining an error for the UAV during landing, wherein the UAV retreats to a higher altitude operational zone when the error is determined.

Abstract: A computer is programmed to deploy an aerial drone to fly within a specified distance of a first vehicle. The computer is programmed to detect a second vehicle and then activate an aerial drone light.

Abstract: A payload mechanism for a vehicle is provided.

Abstract: A latch assembly (1) is presented which comprises a safety latch (2) and a trigger latch (4). The safety latch (2) is releasable to raise from a lowered end position into a raised end position for, in use with an object, locking the object. The trigger latch (4) is adapted for fixing the safety latch (2) in its lowered end position and operable for releasing the safety latch (2). The safety latch (2) is adapted to be reset from its raised end position into its lowered end position for unlocking the object. Moreover, a storage compartment having at least one latch assembly (1) is presented.

Abstract: A retaining assembly secures an equipment item within an aircraft galley compartment. The retaining assembly may include a turn button assembly including a turn button connected to a front edge of the galley compartment to secure the equipment item within the galley compartment. The turn button rotates between a first position for allowing insertion or release of the equipment item from the galley compartment and a second position for securing the equipment item within the galley compartment. A turn button recess on an inner surface of a panel door that is coupled to an edge of an opening for the galley compartment receives the turn button of the turn button assembly when the turn button is in the second position to allow the panel door to fully close over the opening for the galley compartment.

Abstract: The invention provides a rear side shell structure in the form of a back covering that can be attached to a lower structure of a seat without support legs. One representative rear side shell structure and seat unit according to the invention relates to a rear side shell structure for covering a back of a seat, the rear side shell structure including a front surface member and a rear surface member, wherein a reinforcing region in which a space reinforcing member is provided between the front surface member and the rear surface member is provided in a portion of the rear side shell structure, and the front surface member and the rear surface member are directly joined to each other except for in the reinforcement region. Further, the front surface member and the rear surface member are formed of composite members. Also, the space reinforcing member has a honeycomb structure.

Abstract: A hybrid heater system for aircraft wing ice protection is provided. The hybrid heater system includes a voltage source, a carbon nano-tube (CNT) heater, a first positive temperature coefficient (PTC) heater disposed in parallel with the CNT heater to form a parallel formation and a second PTC heater disposed in series between the voltage source and the parallel formation.

Abstract: A seat pan adjustment system for an ejection seat may comprise a guide bracket defining a channel and a seat pan mount configured to translate relative to the guide bracket. A support bracket may extend from a surface of the seat pan mount. A rod may be located through a rod opening defined by the support bracket. The rod may be located in the channel. A biasing member may be coupled to the rod and configured to force the rod away from the surface of the seat pan mount.

Abstract: A restraint may include a longitudinal body having a first end and a second end. The restraint may also include a plurality of engagement features distributed between the first end and the second end. A dimension of at least one of the longitudinal body and the plurality of engagement features may vary along at least a portion of a length of the longitudinal body. The restraint may further include a head disposed at the first end of the longitudinal body. The head may define an aperture and may include a pawl that configured to individually engage the plurality of engagement features. The dimension may vary incrementally or continuously along at least the portion of the length of the longitudinal body from the first end to the second end.

Abstract: The invention relates to an electric drive for an aircraft hybrid system. This electric drive comprises a rotor and a stator, wherein the stator may be connected to a structure of the aircraft and the rotor has an annular flange with a shaft through opening for mounting on a propeller flange, wherein the flange is formed of at least two parts, wherein each of these parts of the flange delimits a section of the shaft through opening.

Abstract: Systems and methods for determining a throttle position of an aircraft are described herein. A first throttle position is obtained from a first sensor, a second throttle position is obtained from a second sensor, and a third throttle position is obtained from a third sensor. The first, second, and third sensors are separately coupled to a throttle of the aircraft for obtaining independent throttle position measurements therefrom. A difference between the first throttle position and the second throttle position is determined. A mismatch is detected when the difference between the first throttle position and the second throttle position exceeds a threshold. A valid one of the first throttle position and the second throttle position is selected based on the third throttle position, in response to detecting the mismatch. A signal indicative of the throttle position is outputted based on the valid one of the first throttle position and the second throttle position.

Abstract: A monitoring system is disclosed for identifying an operating state of a motor, the system comprising: a speed sensor for determining a speed of a motor and providing a speed signal as a function of time in response thereto, and a processor configured to identify a symmetric and/or an asymmetric oscillation of the speed signal as a function of time.

Abstract: An aircraft landing gear assembly (112) including a shock absorber strut (114), a bogie (120), a link assembly (124), and a movement detector (132). The shock absorber strut includes an upper and a lower telescoping parts (118, 116), the upper part being connectable to the airframe of an aircraft and the lower part being connected to the bogie such that the bogie may adopt different pitch angles. The link assembly extends between the upper and lower telescoping parts, such that relative movement between the upper and lower telescoping parts causes relative movement between parts of the link assembly. The movement detector is arranged to detect movement of the link assembly relative to the bogie. The movement detector detects movement by sensing a change in linear displacement of, or angle between, one or more members.

Abstract: A power distribution system can include a power source, a power distribution unit, and at least one electrical load supplied by the power distribution unit. A detection circuit can be utilized in the power distribution system to sense or detect the occurrence of an electrical failure within the power or electrical unit.

Abstract: A system for warning an open state of a two-part fan cowl of an aeronautical structure, wherein the system includes at least one device arranged between these two parts of the fan cowl and adapted to exert force spacing them apart from each other, thus leaving a predefined gap between them at their lower ends when that two-part fan cowl is in the open state.

Abstract: A system including an unmanned aerial vehicle (UAV) or aerial robotic system (ARS) to perform at least one task to an object during flight of the UAV in a movement mode configured for maneuvering near a surface of the object. A task sensor configured to sense at least one parameter of the surface. An adjustable sensor arm attachable to the UAV and supporting the task sensor to facilitate the task performed to the surface of the object by the UAV during flight of the UAV. The sensor arm being resilient to impact forces caused by direct contact of the sensor or sensor arm with the surface to bend, spring or swivel relative to a contour of the surface.

Abstract: A transportable launch and landing pad for drones includes a round surface member for supporting a drone on a ground surface. The surface member includes an endless flexible weighted ground surface contacting, engaging and conforming perimeter disposable on the flat or undulating topography of the ground surface. The endless flexible weighted ground surface contacting, engaging and conforming perimeter is formed of a stranded carbon steel wire rope. The surface member has a diameter establishing an area of the pad that is greater than any linear distance across an area of downwardly moving air of the drone when operated. The pad maintains a position on the ground surface without any separate securing member inserted into the ground, and the pad is not lifted from the ground surface by air from the thrust of the drone during approach and departure of the drone relative to the pad.

Abstract: The present disclosure describes various systems, devices, and methods configured to retrieve a fixed-wing aircraft from free flight using a flexible capture member and a monopole assembly.

Abstract: A method and apparatus for cleaning surfaces of an object. A platform may be moved along a path relative to the object using a robotic device. A liquid may be applied onto the plurality of surfaces of the object using an applicator associated with the platform. The liquid may be worked into the plurality of surfaces using a plurality of cleaning elements associated with the platform to dislodge undesired material from the plurality of surfaces. A plurality of flexible members may be moved along the plurality of surfaces to dry the plurality of surfaces and remove the undesired material from the plurality of surfaces. An airflow may be generated that moves the undesired material into a vacuum duct in a vacuum system.

Abstract: A method for building an aerodynamic structure, an aerodynamic structure, and a vehicle that includes the aerodynamic structure are provided. The method includes providing a structure with at least one substantially-flat exterior surface. The method also includes attaching blocks of rigid fibrous insulation to the at least one substantially-flat outer surface of the structure. Outward-facing surfaces of the blocks of rigid fibrous insulation extend past a target outer mold line of a final aerodynamic shape. The method also includes machining the outward-facing surfaces of the attached blocks to the outer mold line.

Abstract: A packaging unit for packaging pharmaceuticals into a pouch includes packaging equipment operable to form the pouch, a track configured to direct the pharmaceuticals toward the packaging equipment, and a receptacle coupled to the track upstream of the packaging equipment to receive the pharmaceuticals from the track. The receptacle includes a plunger. The pouch is formed around the plunger.

Abstract: There is described a packaging apparatus for forming a plurality of sealed packages comprising a conveyor for advancing a web of packaging material along an advancement path, an isolation chamber, a tube forming device adapted to form a tube from the, in use, advancing web of packaging material, a sealing device adapted to longitudinally seal the tube, a filling device for continuously filling the tube formed by the tube forming device, a package forming unit adapted to form and seal the packages from the, in use, advancing tube formed by the tube forming device and filled by the filling device and a support platform supporting the isolation chamber from a first side of the support platform and carrying the package forming unit from a second side of the support platform opposite to the first side.

Abstract: A standing tree baling apparatus includes a main frame and a boom pivotably connected to the main frame. The boom has a first end and a second end. A boom lifter is connected between the main frame and the boom for raising and lowering the boom about a pivot joint at the first end of the boom. A rotation arm has a first arm end and a second arm end. The rotation arm is pivotably connected to the second end of the boom at the first arm end. A driver pivots the arm relative to the boom. A compression ring is sized for loosely encircling a trunk of a standing tree and adapted for forcibly moving a succession of branches of the tree non-destructively inward toward the trunk of the tree as the ring is raised about the tree to facilitate baling of the tree with rope line. The ring is connected to the second arm end.