Abstract: A board-attachable accessory base lock has an accessory base lock-on that can removably attach to a paddleboard or similar craft. Once the base lock-on is attached, a storage repository can be removably attached to the base lock-on. The storage repository can comprise a cooler, waterproof box, a compartmented fishing box, a crate, a minnow bucket, a fishing live well, a seat, etc. The storage repository can have no top, a hingeably attached top, a removable top, a locking top, etc. The base lock-on can attach to the board via first and second lockdown bars. These bars are designed to fit universally into the hand slot that is commonly found on boards. Once the lockdown bars are situated in the hand slot, the user simply actuates the lockdown handle to secure the lockdown bars in place. Accessory bolts provide attachment of the various storage repositories to the accessory base lock-on.

Abstract: A personal flotation device may include a chest portion, an abdominal portion, and a connecting portion positioned between the chest portion and the abdominal portion. The width of the connecting portion may be smaller than the width of both the chest portion and the abdominal portion. The connecting portion may extend only from a center region of the chest portion. The chest portion, abdominal portion and connecting portion may be arranged to together form an approximately I-shaped portion. The personal flotation device may be secured to a garment.

Abstract: A propeller having a means for creating fluid flow in a non-axial direction and redirecting it in an axial direction.

Abstract: A substantially hollow wingsail is configured to enable electrical components to be situated within the wingsail. In particular, the wingsail may be configured to contain the solar panels used to power the other electrical components of the vessel, as well as other items that are conventionally situated on the exterior of the vessel, such as antennas, navigation lights, and so on. The surface of the wingsail may include transparent or translucent areas to provide light to the solar panels, as well as optical and electromagnetic reflective areas within the wingsail to enhance the performance of the solar panels and antennas. The wingsail may also include an internal light that illuminates the translucent areas of the wingsail for enhanced visibility to other vessels.

Abstract: A control unit, a circulation system, and a method for handling ballast water of one or more ballast tanks. The circulation system includes a control unit; a pipe structure having a first system inlet and a first system outlet; and a pump unit for pumping ballast water between the first system inlet and the first system outlet, the pump unit being connected to the control unit. The control unit is configured to: obtain a volume parameter indicative of pumped volume; determine if a pump criterion is fulfilled, the pump criterion being based on the volume parameter; and operate the pump unit based on whether the pump criterion is fulfilled or not.

Abstract: A lighter-than-air aircraft is provided including a deballasting system, the deballasting system including: at least one tank containing a liquid; a system for pressurizing the liquid of the at least one tank; and at least one sprayer arranged so as to eject the liquid from the pressurization system.

Abstract: A connecting mechanism between an aircraft door and a structure of the aircraft, a related aircraft and method are provided. The connecting mechanism includes an arm intended to be hinged on to the structure, a rotating connection between the door and the arm. The rotating connection may be disengaged from a connection configuration for connecting the door with the arm in an open position of the door, into an uncoupling configuration for uncoupling of the door from the arm, in a closed door position of the door.

Abstract: A yoke plate arrangement may comprise a yoke plate, a wear plate comprising a wear surface and a contact surface, wherein a post extends from the contact surface, and a yoke plate ear extending from the yoke plate in a radial direction, wherein a first aperture is disposed in the yoke plate ear, the post located at least partially within the first aperture, the contact surface being in contact with the yoke plate ear. The yoke plate arrangement may further comprise a retaining feature for coupling the wear plate to the yoke plate. The wear surface may be for engaging a trunnion bearing.

Abstract: A propeller hydraulic actuation system, includes a double-acting dual chamber hydraulic pitch change actuator. The pitch change actuator includes a first pressure circuit having first fluid supply lines and a first hydraulic chamber and a second pressure circuit having second fluid supply lines and a second hydraulic chamber. A piston separates the first and second chambers. At least one pressure sensor is provided for obtaining pressure measurements from which a load differential (F) applied to the piston by the circuits can be calculated. A closed loop controller is arranged to control the fluid supplied to the first and second pressure circuits, wherein the closed loop controller includes an actuator position loop arranged to utilise feedback on the actuator position to control the actuator position.

Abstract: Systems and methods are described for changing the performance of an aircraft by customizing aircraft control system parameters based on a subjective personal preference of a pilot. The system includes a user interface for receiving the customized aircraft control system parameters from the pilot. A first aircraft control module may receive the customized aircraft control system parameters from the user interface, and also receive flight control commands from the pilot. The received flight control commands and the received customized aircraft control system parameters may be processed by the first aircraft control module to cause the aircraft to perform according to customized characteristics as determined by the pilot.

Abstract: A system for augmented pilot operations is provided to perform checks and balances between navigable systems and a plurality of controlling parties of a Fly-By-Wire vehicle. A ground based control system having at least one of manual controls and an autonomous piloting system, an electronic communication system including at least one of an onboard communication system, a ground based communication system, and a programmable interface for inter party communication. An on board flight control system including at least one of a primary power unit, manual flight controls, and a programmable flight management system may be provided. An onboard auxiliary navigation system including at least one of an auxiliary power control unit, a ground operated control/navigation unit, a physical barrier may prevent manual override from within the plane or cockpit, and an assignment device. A disagreement detection system may be configured to detect unauthorized use of the Fly-By-Wire vehicle.

Abstract: A boundary-layer-influencing aerodynamic part comprises a carrier element provided with at least one air passage aperture for guiding an air flow through the carrier element, an air guiding layer disposed on the carrier element and a cover layer constituting at least a part of a flow surface and being configured to have air flow there through at least in sections. The air guiding layer is configured to have air flow there through with an air flow supplied to the part, at least in certain operating phases of the part, through the cover layer and flowing in the direction of the carrier element or through the air passage aperture of the carrier element and flowing in the direction of the cover layer. The cover layer is applied directly to the air guiding layer via an additive manufacturing method.

Abstract: An airplane wing assembly includes a wing, a winglet and a connection element. The wing has a wing box. The wing box is located at a wing tip of the wing and the winglet is connected with the wing by the wing box. The connection element includes a butt joint rib, which is assembled with the wing box, and a center connection, which is assembled with the winglet. The butt joint rib has a first shearing pin hole and a second shearing pin hole, into which are press fitted a corresponding first and a second shearing pin respectively to form interference fit. The center connector has a first sleeve hole and a second sleeve hole.

Abstract: An unmanned aerial vehicle (UAV) and a landing method thereof are provided. The landing method includes the following steps. Firstly, a depth image of a scene is obtained. Next, a landing position is determined in accordance with the depth image. Next, a height information of the landing position is obtained. Next, a plurality of relative distances of the landing gears relative to the landing position are adjusted in accordance with the height information to make the relative distances substantially the same. Then, the UAV lands on the landing position.

Abstract: A landing gear (0) for an aircraft comprising a wheel (R), a system (1) for rotationally driving the wheel that is mobile between a clutched position and a safety position by passing through a declutched position, and a manoeuvring system (3) to displace the driving system (1) between its declutched and clutched positions. The gear comprises an elastic return (4) for returning the driving system (1) to its safety position and first and second abutments (51a, 52a) that are separated as long as the driving system (1) is away from its safety position and in contact with one another when the driving system (1) is in safety position. The first and second abutments (51a, 52a) oppose the passing of the driving system (1) from its safety position to its declutched position when the abutments are in contact with one another.

Abstract: Aircraft landing gear comprising an axle (100), a wheel (102) borne by the axle, a stack of discs (104) arranged to impose a braking torque on the wheel in response to a pressure imposed on the stack of discs, at least one electromechanical actuator (106) extending facing the stack of discs in order in a controlled manner to apply the imposed pressure to the stack of discs, and an actuator bearer (107) designed to bear the electromechanical actuator, the electromechanical actuator being fixed to the actuator bearer while at the same time being demountable. The actuator bearer is incorporated into the axle in such a way that the axle and the actuator bearer form a single component. Method of demounting a stack of discs from such a landing gear.

Abstract: The present disclosure provides a skid control system that includes a brake control device configured to convert a current command value to create a braking pressure, wherein the braking pressure is applied to a hydraulically actuated brake and/or an electrically actuated brake. A deceleration control unit receives a filtered wheel speed value and/or a filtered wheel acceleration value from the wheel assembly. A brake control algorithm unit retrieves a noise threshold value corresponding with the at least one of the filtered wheel speed value or the filtered wheel acceleration value. A pressure control unit receives a feedback pressure from the hydraulically actuated brake and/or an electrically actuated brake, wherein the pressure control unit either increases or decreases the current command value in response to a difference between the pressure command value and a feedback pressure being either less than or greater than the noise threshold value.

Abstract: An aircraft is provided including an airframe, an extending tail, and a counter rotating coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system including a propeller is positioned at the extending tail. The translational thrust system provides translational thrust to the airframe. A drive system is configured to operate both the main rotor system and the translational thrust system. The drive system includes a clutch configured to selectively couple or decouple the propeller from the drive system.

Abstract: A fracture-resistant double shear joint including a clevis having a first end defining a first bore and a second end defining a second bore, and a reaction load member defining a third bore, wherein the first bore, the second bore, and the third bore are colinear. The fracture-resistant double shear joint can further include a first spacer positioned within the first bore, a second spacer positioned within the second bore, and a shear pin positioned within each of the first bore, the second bore, and the third bore. The shear pin may include an outer cylinder, an inner shear bolt threaded on both ends, and nuts at either end that engage the threads. The nuts may be tightened to place the outer cylinder in compression. The spacers in the first and second bore may include a low friction liner that interfaces with the outer cylinder of the shear pin. The ends of the spacers may be set back from the ends of the first and second bores (that are next to the third bore).

Abstract: A hinge assembly such as a lead-lag hinge can include a hinge pin assembly. The hinge pin assembly can include an outer cylinder, a shear pin that extends through the outer cylinder and having a first threaded end and a second threaded end, a first nut threaded on the first threaded end and a second nut threaded on the second end. An opposing force between the first nut and the second nut applies a compressive stress to the outer cylinder that may increase a resistance of the hinge pin assembly to wear and damage. In the case of complete failure of the outer cylinder, the shear pin can maintain structural integrity of the hinge pin assembly and of the hinge assembly.

Abstract: A directional control system for a rotorcraft having a tail boom including a no-tail-rotor apparatus configured to control rotorcraft yaw using forced air ejected from the tail boom and a duct configured to deliver the forced air to the no-tail-rotor apparatus. The directional control system comprises a heat exchanger having air passages and fluid passages, the air passages in fluid communication with the duct, the fluid passages in heat exchange relationship with the air passages and configured for receiving a cooling fluid, and a forced air driver in fluid communication with the duct for driving the forced air through the duct to the no-tail-rotor apparatus. Methods of providing directional control in a rotorcraft are also discussed.

Abstract: A cross flow fan to be incorporated into an aircraft comprises a cross flow fan rotor to be positioned in an aircraft, a drive arrangement for the cross flow fan rotor, and a plurality of vanes positioned downstream of the cross flow fan rotor. An aircraft is also disclosed.

Abstract: A method of deploying an unmanned aerial vehicle (UAV) operation system may be provided. A method may include estimating an amount of traffic for one or more routes based on a demand of the one or more routes. The method may also include determining a required number of docking stations for each route of the one or more routes based on the estimated amount of traffic for the route, a distance of the route, and a maximum travel distance for a UAV. Further, the method may include installing the required number of docking stations for each route of the one or more routes, wherein each docking station of the required number of docking stations including at least one of a power supply, a wireless charger, a communication module, a control module, and a camera.

Abstract: A method of distributing fragile insects in a distribution involving a wind shear, comprises, encapsulating the insects into a bubble and then releasing the bubble into the wind shear so that the bubble protects the insect from the wind shear. The insect may be inserted before or after formation of the bubble at any stage of the insect life cycle and the bubble may be uniform or made of a slow dissolving and a quick dissolving part. The bubbles are useful for aerial distribution of sterile male mosquitoes.

Abstract: A hovering aerial vehicle is provided, comprising an airborne unit and an auxiliary unit. The airborne unit is configured to carry the auxiliary unit during flight and comprises a flight system configured to facilitate providing aerodynamic lift to facilitate hovering of the vehicle. The auxiliary unit comprises an electrical power source in electrical communication with the flight system to provide electrical power for its operation. The hovering aerial vehicle further comprises a decoupling system configured to facilitate selectively switching the vehicle between a detached configuration thereof wherein the airborne and auxiliary units are remote from each other, and an attached configuration thereof wherein the airborne and auxiliary units are secured to one another, and to maintain the electrical communication when the vehicle is in its detached configuration.

Abstract: A diffuser for distributing insects such as mosquitoes from an aircraft, comprises a distribution tube connected to an insect source at a first end and open to the outside at a second end in a direction away from that of travel of the aircraft, for distribution of the insects; and a profile surrounding the second end, the profile being shaped to define a steadily changing airspeed. The pipe may be aligned with airflow at the point of exit of the pipe and protection may be provided around or just upstream of the exit to provide a point of minimal air velocity at the exit, the exit being the point of release of the insects.

Abstract: Disclosed is a package delivery mechanism (PDM) of an unmanned aerial vehicle (UAV). The PDM includes a gravity activated locking mechanism to lock and unlock a package attached to the UAV based on the weight of the package. When the package is attached to suspension means of the UAV that lowers the package to the ground from the UAV, the locking mechanism automatically engages with the package and keeps the package locked to the suspension means, due to the weight of the package. When the package is lowered and reaches on the ground, the weight of the package is offloaded from the suspension means, which enables the locking mechanism to be disengaged, thereby releasing the package. The PDM includes a severing module to sever the suspension means from the UAV.

Abstract: Certain aspects of the technology disclosed involve a container for delivery by drone (e.g., an unmanned aerial vehicle). The container can include a coupling mechanism to lock and unlock a package attached to the drone based on a tension applied to the coupling mechanism. The package can include sidewalls affixed to a top wall. The sidewalls can include securing mechanisms to be secured to a bottom wall of the container. A rigid extremity can be a contiguous extension of any of the sidewalls and extend below a lower surface of the sidewalls. The rigid extremity can include a malleable contour proximate to a corner of the container. The malleable contour can extend from a base of the rigid extremity through the sidewall. An aperture in the top wall can be configured for a inserting member of a coupling mechanism.

Abstract: Reconfigurable payload systems (RPS) and methods of configuring and using the same with operational load envelopes are disclosed that may be employed to enable external aircraft payloads to be rapidly interchanged or swapped out together with associated internal equipment within a given aircraft so as to modify or change payload capability of the aircraft, e.g., to meet a particular mission and/or to enable use of future payload types as they are developed. The RPS and associated methods may be implemented to allow multiple different payload systems to be swapped in and out on a given aircraft as required based on needs for a given mission.

Abstract: A wall module for a cabin of a vehicle for separation of different cabin regions comprises a lower wall section having at least one first fastening means for fastening the wall module to at least one near-floor structurally fixed component in the cabin, a surface-like rigid upper wall section converging with the lower wall section having at least one second fastening means in a region of the wall module facing away from the lower wall section for fastening the wall module to at least one near-ceiling structurally fixed component in the cabin. The upper wall section at least in a region comprises an arched curvature around a horizontal axis for adapting to the shape of a backrest of a seat. The wall module comprises at least one edge stiffening element, which extends between a near-floor region and a near-ceiling region of the wall module.

Abstract: A fastening system for fastening an object in a vehicle, in particular in an aircraft comprises at least one rail which is arranged on the vehicle side, and an object which is to be releasably fastened on the rail. The object can be positively fixed on the rail by way of at least one fastening device which is arranged on the object side. Spring means are provided on the fastening device, and these produce a non-positive fit between the fastening device and the rail, given a positive arrangement of the fastening device on the rail.

Abstract: Described herein is a seat which comprises a seat base, a seat back and a seat frame. The seat back comprises a first connector, a second connector and a securing means. The first and second connectors are for securing the seat back in pivotable engagement with the seat and the securing means is for controlling pivotal movement of the seat back relative to the seat and for preventing disengagement of the first and second connectors from the seat.

Abstract: A monument is configured to be positioned within an internal cabin of a vehicle. The monument includes a deployable portion. The deployable portion is configured to move from a non-deployed state into a deployed state when a force that meets or exceeds a predetermined threshold is exerted into the monument wall assembly.

Abstract: Described herein is a table leg comprising a first connector for connecting the table leg in pivotable engagement with a seat such that the table leg is pivotable between first and second leg positions, and a securing means for restricting movement of the table leg relative to the seat. The securing means is for allowing removal of the table leg from the seat when the table leg is in the first leg position and for preventing removal of the table leg from the seat when the table leg is in the second leg position.

Abstract: The present disclosure provides a swivel stop comprising a rotating member, a first boss coupled to the rotating member and a second boss coupled to the rotating member, and a second plate having a first interference surface and a second interference surface. An interference between the first boss and the first interference surface and the second boss and the second interference surface tends to limit the rotation of the rotating member with respect to the second plate. The swivel stop may further comprise a rail wherein the second plate is configured to translate along the rail.

Abstract: A flight attendant seat comprises a carrier device having a first surface, a seat element movably coupled to the carrier device, and a backrest element movably coupled to the carrier device and operatively coupled to the seat element. The seat is movable between an operative position, permitting the use of the seat by a flight attendant, and an inoperative position in which the seat element and the backrest element are positioned, relative to the carrier device, such that they do not protrude from the carrier device first surface. The seat may be positioned in such a way, relative to a passenger seat or a row of passenger seats, that the rear side of the backrest element faces towards the rear side of a backrest of the passenger seat or the rear side of a backrest of at least one passenger seat belonging to the row of passenger seats.

Abstract: An air gasper (air) for a vehicle includes an air inlet (26), a first housing (24) disposable through a panel in the vehicle (12), the first housing (24) being connected to the air inlet (26), a second housing (70) disposed within the first housing (24), an air outlet (72) disposed within the second housing (70), downstream of the air inlet (26), and a first mechanism (102, 70) connected between the first housing (24) and the second housing (70). The first mechanism (102, 70) permits the second housing (70) to be stowed within the first housing (24) in a stowed position and also permits the second housing (70) to extend outwardly from the first housing (24) in a deployed position.

Abstract: The present invention provides a dewatering device for an air-conditioning system of a plane, comprising: one or more filter plates disposed within a mixing cavity of an air-conditioning system of a plane, for filtering liquid-state water in mixed air in the mixing cavity, wherein the filter plates are configured to be inclinable relative to an axis of the mixing cavity, and an inclination angle thereof is adjustable so as to change a filtering amount of the mixed air.

Abstract: Tandem air cycle machine modules include a first air cycle machine having a first compressor and a first turbine, a second air cycle machine having a second compressor and a second turbine, and a structural manifold operably connected to both the first air cycle machine and the second air cycle machine.

Abstract: Assemblies are provided for an aircraft with a gas turbine engine. One assembly includes a body such as an inlet nose lip of a nacelle for the gas turbine engine. This assembly also includes a thermal management system that includes a duct, a regulator and a flow restrictor. The thermal management system is configured to direct a flow of bleed gas through the duct from the gas turbine engine to the body for substantially preventing ice buildup on the body. The regulator is configured to affect the flow of bleed gas downstream of the regulator. The flow restrictor is configured to selectively restrict the flow of bleed gas through the duct when a temperature of the flow of bleed gas is greater than a threshold temperature.

Abstract: A rotor ice protection system (RIPS) apparatus for an aircraft to heat aircraft rotor blades is provided. The RIPS apparatus includes circuitry disposed to transmit electrical loads associated with RIPS operations, an indicator unit disposed to alert a pilot of the aircraft to a RIPS condition indicating an operating status of the RIPS operations, a controller configured to actuate the RIPS operations in accordance with current conditions and to issue a command to the indicator unit to alert the pilot to the RIPS operations according to the actuation and a sensor system disposed to sense whether the circuitry is transmitting the electrical loads and to provide a sensing result to the indicator unit. The indicator unit additionally alerts the pilot to the RIPS operations according to the sensing result.

Abstract: An emergency vision apparatus comprises an inflatable enclosure to enable a user to see through the enclosure when expanded and observe a source of information at a distal end of the enclosure while smoke or other particulate matter is in the environment. The enclosure includes an opening configured for insertion of a user's hand into the interior of the enclosure to allow the user to operate a touch sensitive screen or hardware visible through the second clear member disposed toward a user and a sealable closure for closing the opening and sealing the opening around the user's hand. The sealable closure includes flexible first and second sheets covering the opening, the first and second sheets including respective first and second slits disposed transversely to each other, the first and second slits being configured to allow insertion of the user's hand into the interior of the enclosure.

Abstract: An upper bifi frame for preventing air leakage in a gas turbine engine including an engine casing and a fan case is provided. The upper bifi frame includes a forward fairing having a forward fairing midsection extending between the engine casing and the fan case. The forward fairing has a forward fairing first end including a flange configured to couple to the engine casing. The forward fairing has a forward fairing second end extending from the forward fairing midsection and configured to couple to the fan case. At least one aft seal is secured to the forward fairing and forms a seal therewith.

Abstract: A method of monitoring a first freewheel interposed between a first drive shaft of a first engine and a rotor. The state of operation of said first freewheel is correct if the first inlet speed of rotation of the first drive shaft lies in a second range of values corresponding to the current stage of operation while the outlet speed of rotation of the rotor lies in a first range of values corresponding to the current stage of operation.

Abstract: A system for protecting the structural integrity of an engine strut may include a first monitor, a second monitor, and a controller communicatively coupled to the first monitor and the second monitor. The first monitor may be mounted proximate an engine strut coupling a turbine engine to an airframe of an aircraft. The second monitor may be mounted proximate the first monitor. The first monitor and the second monitor may each be configured to fail upon reaching a triggering temperature indicative of a burn-through in an engine case during operation of the turbine engine. The controller may be configured to automatically reduce an operating parameter of the turbine engine upon a failure of both the first monitor and the second monitor.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a control unit to command the gas turbine engine to perform one of a rolling takeoff procedure and an unrestricted takeoff procedure. The control unit is configured command the gas turbine engine to perform the rolling takeoff procedure when information required to determine whether the unrestricted takeoff procedure can be performed is unavailable to the control unit.

Abstract: A vertical takeoff and landing aircraft (101) for transporting persons or loads, including a plurality of preferably equivalent and redundant electric motors (3) and propellers (2), substantially arranged in one surface, wherein each propeller is assigned an individual electric motor to drive the propeller, the aircraft being characterized in that at least one attitude sensor is provided for attitude control of the aircraft (101) in an active signal connection to at least one signal processing unit which is designed or set up to automatically perform the attitude control based on measurement data from the attitude sensor by regulating the speed of at least some of the electric motors (3), preferably with signal actions of the speed controller assigned to each electric motor such that the aircraft (101) is positioned in space with the surface defined by the propeller (2) substantially horizontal at all times, without control input by a pilot or a remote control.

Abstract: To provide a fuel pipe of an aircraft that makes it possible to maintain temperature of fuel in the fuel pipe at appropriate temperature while giving consideration to reliability that is constantly required for the aircraft. A fuel pipe provided in an airframe of the aircraft includes: an inner pipe defining a flow path through which fuel flows; and an outer pipe surrounding an outer periphery of the inner pipe. A gap is provided between the outer periphery of the inner pipe and an inner periphery of the outer pipe. The inner pipe is made of a rubber material, and the outer pipe is made of a metal material.

Abstract: A system for driving an environmental control system (ECS) of a vehicle with ground-based electrical power may include a turbine engine on board the vehicle, coupled to the ECS to pneumatically drive the ECS, and an electric machine, on board the aircraft, mechanically coupled to the turbine engine, to drive the turbine engine. A control system such that the electric machine provides motoring assistance to the turbine engine, and that the motoring assistance is limited to match the available current from the ground-based electrical power.

Abstract: An engine assembly for use as an aircraft auxiliary power unit, having internal combustion engine(s) in driving engagement with an engine shaft, a generator having a generator shaft directly engaged to the engine shaft such as to be rotatable at a same speed, a compressor having an outlet in communication with the internal combustion engine inlet, and a turbine having an inlet in communication with the internal combustion engine outlet. The turbine may be a first stage turbine, and the assembly may include a second stage turbine having an inlet in communication with the first stage turbine outlet. A method of providing electrical power to an aircraft is also discussed.