Abstract: In accordance with one embodiment, a servicing watercraft that may be safely secured to a serviced watercraft. The servicing watercraft comprises at least one auxiliary section that may be positioned to either a) increase the effective width of the servicing watercraft thus reducing rolling motion while the servicing watercraft is stationary or in operation, OR b) decrease the width of the servicing watercraft thus reducing drag while the watercraft is moving through the water. Furthermore, the auxiliary section(s) help the servicing watercraft to be positioned in an optimum location adjacent to the serviced watercraft as to avoid impact from accidently dropped cargo or shipping containers from the serviced watercraft.

Abstract: An expandable waterproof flood protection container. The flood protection container consists of flexible and waterproof sidewalls attached to a buoyant rim. The flood protection container is sized to accommodate boxes and consumer goods, which can be placed inside the flood protection container. If the storage area where the items in the flood protection container floods, the buoyant rim will rise with the rising water, which will draw up the waterproof sidewalls to protect the contents from the water.

Abstract: A submersible device for lifting a boat over water has a couple of pneumatic containers and an air compressor for their inflation and deflation through valves arranged in the pneumatic containers. The pneumatic containers of the couple are interconnected by way of flexible cross members supporting the boat when the pneumatic containers are inflated.

Abstract: Various examples of transferring a watercraft between land and water are disclosed. When a vehicle receives a transfer signal, the vehicle locates a launch ramp, and the vehicle moves to the launch ramp. A trailer attached to the vehicle moved into the water using the launch ramp, such that a watercraft can be transferred between land and water via the trailer.

Abstract: A full face mask and snorkel can include a full face mask and a rigid snorkel attached to the side of the mask. The side location of the ridged snorkel avoids peripheral ducting of air around the full face mask. The full face mask includes a main peripheral full face seal coupled to the mask's rigid support structure. The full face mask includes a separation seal dividing the full face mask into at least an upper chamber. The snorkel is affixed to the side of the full face mask at a location proximate to where the separation seal meets the main seal. A full face mask and snorkel can also include an exhalation valve located within the snorkel and proximate to the mask so as to avoid a volume of respirated air within the snorkel from being reinhaled into the lower chamber of the full face mask.

Abstract: A regulator first stage for two-stage underwater breathing apparatuses includes a reduction chamber communicating with a high-pressure gas supply through a balance valve, which is influenced by the pressure of the external environment by a balance diaphragm that, by way of a suitable actuator, acts on the valve. The reduction chamber includes one or more medium pressure outlets, having axes parallel to the operating axis of the balance valve. In one configuration, one or more medium pressure outlets are also provided having axes orthogonal to the operating axis of the valve.

Abstract: An underwater docking system for an autonomous underwater vehicle, the underwater docking system including: an underwater station including a base mount fixed to a seabed and a circular frame member supported by the base mount and parallel to a horizontal plane; and an autonomous underwater vehicle configured to dock with the underwater station while sailing through an upper side of the frame member, wherein: the autonomous underwater vehicle includes an underwater vehicle main body.

Abstract: The apparatus includes a pin, a pair of plates and a brace. The pin, in use, is received by one of the pairs of trim holes of an outboard engine mounting bracket. The pair of plates, in use, is secured to the main assembly of the outboard motor using the other of the pairs of holes. The brace is adapted, when the brace and the main assembly are operatively positioned and when the lower unit of the outboard motor is locked against movement away from the transom, to be gripped between the plates and the pin, to restrain the main assembly against said pivotal movement.

Abstract: One embodiment of the invention comprises a method for controlling a marine vessel having a first steerable propulsor, a corresponding first reversing device, a second steerable propulsor and a corresponding second reversing device. The method comprises receiving a first vessel control signal corresponding to a rotational movement and no translational movement command, generating at least a first actuator control signal and a second actuator control signal in response to the first vessel control signal, coupling the first actuator control signal to and controlling the first steerable propulsor and the second steerable propulsor, and coupling the second actuator control signal to and controlling the first reversing device and to the second reversing device. The method creates rotational forces on the marine vessel with substantially no translational forces on the marine vessel.

Abstract: Unmanned and remotely controlled airship constituted from system of multirotor combined with inflatable envelope. The airship may be lifted/powered by a power system comprising three or more rotors. In some embodiments, the airship may be constructed using rods, connectors, the main system/control box and the rotors. The airship system may have a systemic symmetry for weight distribution and flight control and may be, for example, a symmetric ellipsoid envelope/blimp.

Abstract: The zero carbon emission vehicle as disclosed herein may include a condenser for extracting fluid water from the atmosphere, an electrolyzer for generating hydrogen from the fluid water, and one or more deformable fluid-retaining chambers that couple thereto for selectively adjusting the buoyancy and altitude of the zero carbon emission vehicle in real-time, to maintain the air vehicle in flight substantially without needing to land and refuel the air vehicle. Solar panels provide the energy for the described systems, and the energy from the solar panels can be stored in the form of hydrogen gas which gives buoyancy to the air vehicle.

Abstract: A method of installing interior modules to support structures in an aircraft fuselage comprises attaching fixed ends of a plurality of tie rods to the support structures; and determining installation length of the tie rods, installation spacing between free ends of the tie rods, and installation orientation of the tie rods prior to positioning the interior module for installation. The method further comprises securing tie rod holding fixtures to the tie rods to hold the spacing and orientation at or near final configuration to facilitate installation of the interior modules.

Abstract: An aircraft emergency exit door (10) with opening mechanisms integrated by a grouping of the mechanisms into a door beam (3) located on a given side of a window (16) of standard dimensions. In the beam, an inner handle (1) is mounted on a main shaft (102) connected with a locking shaft (8A) on which there is mounted, against return springs (83), a door blocking/locking mechanism (8) comprising a lock (81). A mechanism for conditionally opening the door (100) includes a vent flap (110), a pivot connection (12) for coupling the flap (110) to the inner handle (1), and a blocking shaft (120) that has, at each end, a pressure lever (121) equipped with supports for blocking (122) and unblocking (123) the flap (110). Return springs (32) mounted against the conditional opening mechanism (100) are calibrated to allow the opening of the flap (110) by exerting reduced pressure in residual pressure variation conditions, and to prevent it from opening in overpressure conditions.

Abstract: An aerodynamic sealing includes: an elastic first sealing wall extending between a first bottom edge and a first tip edge; an elastic second sealing wall extending between a second bottom edge and a second tip edge, and extending convergent with respect to the first sealing wall, so that the first and second sealing walls are joined together at their first and second tip edges to form a tip line; a bottom element connecting the first bottom edge to the second bottom edge, wherein the bottom element is joined to both the first sealing wall and the second sealing wall; and a plurality of stiffening elements connecting the first sealing wall to the second sealing wall between the tip line and the bottom element, wherein the stiffening elements are spaced apart from one another and joined to both the first sealing wall and the second sealing wall.

Abstract: An aileron counterbalance or aircraft spade apparatus disposed to afford optimal drag force, which particularly enhances the capability of an aircraft to spin, turn and dive more quickly and efficiently in aircraft races. The aircraft spade apparatus includes a rectangular shape and which exhibits a greater surface area and higher drag force characteristics.

Abstract: A lever outputs a first signal level where the first signal level is based at least in part on the position of the lever and the first signal level is used to control a first set of rotors associated with a vertical propulsion system. A thumb controller (coupled to the vertical thrust lever) outputs a second signal level where the second signal level is based at least in part on the position of the thumb controller, the second signal level is used to control a second set of rotors associated with a horizontal propulsion system, and the thumb controller includes a detent associated with a recommended sustained maximum.

Abstract: A braking test for a high lift system. The system including a plurality of high lift surfaces movably arranged at a wing, a plurality of drive stations coupled with the high lift surfaces via a transmission shaft, a power drive unit coupled with the transmission shaft including an electric motor operably coupled with a brake, and a control unit operably coupled to the power drive unit. The control unit executing a method for testing the brake, including actuating an electric motor, acquiring a sensor output of a sensor coupled during the actuating of the motor and determining a motion of the motor, activating a selected brake under test, measuring an elapsed time until the brake has arrested the motion, and determining if the elapsed time is less than a threshold. Generating a brake failure signal for the selected brake if the elapsed time exceeds the threshold.

Abstract: A split winglet configured for attachment to a wing tip of a wing. The split winglet may include an upper winglet extending from the wing tip above a chord plane of the wing and a ventral fin projecting below the chord plane. The upper winglet and the ventral fin may include tip configurations. At least one of the upper winglet tip configuration and the ventral fin tip configuration may be provided by a curved blade cap attached thereto. The curved blade cap may include a leading edge having a first curve with a first radius, and a trailing edge having a second curve with a second radius different from the first radius. The curved blade cap may also include a distal segment oblique to the first curve and the second curve.

Abstract: A dual axis bifilar vibration absorber system including a first bifilar vibration absorber having a first support provided with a first cantilevered end including a first opening and a second cantilevered end including a second opening. The first opening is spaced from the second opening along a first axis. A first mass is operatively connected to the first support. A second bifilar vibration absorber is collocated with the first bifilar vibration absorber. The second bifilar vibration absorber includes a support member having a first opening element and a second opening element. The second opening element is spaced from the first opening element along a second axis that is substantially perpendicular to the first axis. A second mass is operatively connected to the support member. The first mass is selectively pivotable about the second axis, and the second mass is selectively pivotable about the first axis.

Abstract: There is provided, in accordance some embodiment, a method for enhancing autorotation performance of a rotary-wing aircraft in emergency events. The method comprises an action of receiving a request for emergency thrust from a user interface. The method comprises an action of sending a start command to an emergency engine coupled to a rotary-wing aircraft following the request. The method comprises an action of thrusting the rotary-wing aircraft coupled to the emergency engine in a direction substantially of a longitudinal axis of the rotary-wing aircraft, thereby enhancing autorotation performance of the rotary-wing air-craft in an emergency event.

Abstract: This invention is about a rotorcraft that possesses a configuration made up of the join of three technologies Know separately as “Jet Tip”, “Circulation Control” and “Advancing Blade Concept”. These three technologies synergizes of unusual form allowing the embodiment of a rotorcraft with advantages qualitative and quantitative in fields as flight characteristics, manufacturing, maintenance, security in flight and operational costs.

Abstract: The Multi-Rotor Safety Shield (MRSS) provides a complete and substantial encasement system which can be secured about a Drone, protecting a multitude of aircraft components from contact with any outside disturbance and which can protect the sensitive components from dust, water, wind, rain, snow, fingers, toes, appendages of any kind, and atmospheric changes as example, from disabling the Drone and can protect people, places or things from high velocity spinning exposed rotor/propellers. The MRSS provides rigid non-permeable platform for attaching or incorporating additional safety devices as found in the Drone industry (or other industries) resulting in a safety device that completely prevents the loss a Drone due to the catastrophic failure of any Drone system or combination of systems which would typically result in rapid decent, and/or uncontrolled flight.

Abstract: A helicopter rotor hub assembly for coupling a pair of helicopter blades to a helicopter mast. It includes a yoke assembly and a pitch assembly. The yoke assembly includes a central section and first and second sections extending respectively on opposite sides of the central section. Each one of the first and second sections has a pair of elongated arms defining inbetween a bearing-receiving interspace. The pitch assembly includes first and second attachment plates extending respectively along the first and second sections of the yoke assembly and first and second pitch bearing assemblies. Each attachment plate is connected to a respective one of the helicopter blades. Each pitch bearing assembly extends in the bearing-receiving interspace of a respective one of the first and second sections of the yoke assembly. Each pitch bearing assembly contacts a respective one of attachment plates to allow a pitch movement of the helicopter blades.

Abstract: An unmanned aerial vehicle according to various embodiments includes: a housing; a communication circuit, wherein the communication circuit establishes wireless communication with an external controller; and a plurality of propulsion systems connected to the housing, wherein the propulsion systems include: a motor; a rotation shaft having an axis extending in a first direction, wherein a first end is connected to the motor, and wherein the rotation shaft is rotates in a first direction by the motor; a cap structure fixed to the second end of the rotation shaft, a propeller including: a hub including a through-hole formed in the first direction, such that the rotation shaft rotatably passes through the through-hole, wherein the propeller is detachably connected to the cap structure, such that, when an external force is exerted on the blade, the propeller is released from the cap structure to be freely movable along the axis toward the motor.

Abstract: Disclosed is a system for controlling acoustic radiation from an aircraft. The system comprising a plurality of rotor systems (one or more) and a noise controller configured to regulate acoustic radiation from the plurality of rotor systems. The noise controller can be configured to regulate a commanded flight setting from the flight control system and to output a regulated flight setting to the plurality of rotor systems. Based on the regulated flight setting, the plurality of rotor systems are configured to generate, individually and in aggregate, acoustic radiation having a target acoustic behavior. The target acoustic behavior may be achieved using beamforming techniques to, for example, change the directionality of acoustic radiation from the plurality of rotor systems, or otherwise tune the acoustic radiation to reduce detectability and/or annoyance.

Abstract: A closeout structure for a rotor blade includes a first fluid channel for supplying a first pressure to a first port of a trailing edge (TE) device, a second fluid channel for supplying a second pressure to a second port of the TE de vice, and a trough disposed between the first fluid channel and the second fluid channel. The closeout structure forms a double-W shape.

Abstract: A novel electromagnetic actuator designed to operate at system resonance, used in the construction of a unique vehicle system, is presented herein. An exemplary embodiment of the vehicle system is based on an electromagnetic actuator coupled to a plurality of actuating members of a micro aerial vehicle. Attributes of this type of actuation offer several enhancements over traditional approaches. The unique use of an electromagnetic actuator lends itself to a near unlimited number of coil cross-sectional designs that can be optimized to meet performance requirements while maintaining minimal costs of fabrication.

Abstract: A roadside assistance system for motorists, comprising a plurality of unmanned aerial vehicles (UAVs) each having an emergency battery power supply connected to an inductive charger, an emergency detachable fuel supply, an imaging system and a visual landing software module configured to land the UAV on a predetermined target. In addition, each has an inductive charging pad electrically connected to a vehicle electrical system, the inductive charging pad bearing the predetermined to by which the UAV may deliver a charge necessary to jump a vehicle or provide an emergency recharge.

Abstract: Systems and methods are provided for a network of relay drones utilized as a set of relays or linkages between a base station and a working drone controlled by the base station. The relay drones in the network may augment a communication link or communication signal between the base station and working drone. Relay drones may augment the communication link by acting as nodes that relay communication between the base station and the working drone by boosting the communication signal at each node to compensate for loss of signal power over a traveled distance and/or providing a path with a direct line of sight between the base station and working drone. Directional antennas may be utilized when a direct line of sight is established, which may improve communication signal efficacy when compared with omnidirectional antennas.

Abstract: An aerial vehicle, preferably including: a rotary wing and a protection housing enclosing the rotary wing. An aerial vehicle, preferably including: a first rotary wing module including a first rotary wing and a second rotary wing module including a second rotary wing, wherein the first rotary wing module and the second rotary wing module are preferably operable between a folded configuration and an unfolded configuration. A method of aerial vehicle operation.

Abstract: Systems and methods using an Unmanned Aerial Vehicle (UAV) to supply one or more batteries include loading the UAV with the one or more batteries as cargo; causing the UAV to fly to a remote location; and at the remote location, inserting the one or more batteries in a battery system for powering thereof. The method can further include, at the remote location, retrieving a second set of one or more batteries from the battery system; and causing the UAV to fly back with the retrieved second set.

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

Abstract: A disbursement system for a UAV is provided. The disbursement system may include a plurality of disbursement nozzles operable to dispense an agricultural product at variable flowrates, a flow controller responsive to instructions and operable to regulate a volume of the agricultural product dispensed by the disbursement nozzles, and a control system. The control system may include a plurality of sensors operable to monitor a plurality of flight parameters and a processing unit configured to model an effect of the plurality of flight parameters on first flow control instructions corresponding to a prescription coverage of the agricultural product and calculate and output modulated flow control instructions to the flow controller. The control system may modulate the first control instructions to change a flowrate of one or more of the plurality of disbursement nozzles to achieve an actual coverage of the agricultural product that is closer to the prescription coverage.

Abstract: Fluid dispersal systems and methods of controlling such systems are provided. A method for emitting a fluid from an aerial fluid dispersal system includes receiving data corresponding to an initial aerial distribution profile of fluid emitted by the aerial fluid dispersal system across a distribution width. The fluid is emitted through a plurality of individually controlled nozzle assemblies, and an emission rate of the fluid emitted from a respective nozzle assembly of the plurality of nozzle assemblies is based on an operating parameter of a valve assembly of the respective nozzle assembly. The method also includes determining an effect of the emission rate of each respective nozzle assembly on the initial aerial distribution profile of the fluid across the distribution width. The method also includes controlling the operating parameter of each respective valve assembly to adjust the emission rate of each respective nozzle assembly to generate a compensated distribution profile.

Abstract: The invention relates to an overhead luggage compartment for an aircraft, comprising an upper luggage compartment element, a lower luggage compartment element movable between a locked and an open position, a holding device for holding the lower luggage compartment element in the closed position, a lifting spring for supporting the movement of the lower luggage compartment element from the open position to the closed position, and a retaining device for fixing the lifting spring in the tensioned state in the open position of the lower luggage compartment element. An operating handle for releasing the retaining device in the open position of the lower luggage compartment element is provided, wherein the lower luggage compartment element is movable, optionally with support by the lifting spring or with the lifting spring fixed in a tensioned state, from the open position to the closed position.

Abstract: Apparatus and methods to attach an object to an overhead section of a cabin of an aircraft. An example apparatus includes a bracket to be positioned between rails in a cabin of an aircraft. The bracket includes edges having first attachment points to align with second attachment points of each of the rails. The bracket is positionable along a length of the rails by aligning the first attachment points of the bracket with a portion of the second attachment points of the rails. The bracket also includes flanges disposed between the edges. The flanges have respective third attachment points and fourth attachment points aligned to receive fasteners for hanging a device used in the cabin of the aircraft.

Abstract: An aircraft cabin management system includes a control unit and at least one sensor intended to be incorporated into a seat and suitable for establishing a communication with the control unit in order to transmit, to the control unit, at least one signal relating to at least one measurement performed by the sensor.

Abstract: A securement mechanism for a storage compartment in a seat headrest may comprise a housing tray and a first latch disposed in the housing tray. A release button may be disposed in the housing tray and may contact the first latch. The release button may be configured to be substantially coplanar with the housing tray when the securement mechanism is in a secured position.

Abstract: The invention relates to a pump unit for inflating and deflating a pneumatic cushion, comprising a pump with two conveying directions, a first fluid line to connect the pump to the pneumatic cushion, and a second fluid line with which the pump can be connected to a supply line or the atmosphere, as well as a first pressure sensor that is connected to the first fluid line or to the second fluid line in order to measure a fluid pressure present in the fluid line. The pump unit also has a control unit that is connected to the pump and to the first pressure sensor. The pump, at least one part of the first fluid line, the second fluid line, the first pressure sensor and the control unit are arranged in a common housing.

Abstract: Apparatus and associated methods relate to projecting a light beam onto an interior surface of an aircraft window so as to indicate a testing location to test for ice accretion. The testing location is determined, by a boundary locator, based on aircraft flight conditions, aircraft exterior shape, and a predetermined size of super-cooled droplets, which could present a hazard to the aircraft. The determined test location corresponds to a calculated boundary that separates locations where super-cooled water droplets of the predetermined size cause ice-accretion from locations where such particles do not cause ice accretion, for such aircraft flight conditions. The light beam is then projected onto the interior surface of the aircraft window at the determined test location. The projected beam of light can indicate, to an observer and/or a detector, a location to monitor for ice accretion caused by super-cooled water droplets of the predetermined size.

Abstract: An evacuation slide that includes a first portion and a second portion and a connector that includes a first subunit mounted to the first portion and a second subunit mounted to the second portion. The first subunit and the second subunit may be configured to be detachably coupled together, and the connector may include two different types of fasteners. The first subunit may include a first patch of hook-and-loop material and a first snap-fastener element and the second subunit of the connector may include a second patch of hook-and-loop material and a second snap-fastener element.

Abstract: A system is provided for interfacing a Full Authority Digital Engine Control (FADEC) system with engine sensors and actuators using miniaturized Low Temperature Co-fired Ceramic (LTCC) substrates operating as smart notes that communicate digitally over a data bus to a miniaturized LTCC operating as a data concentrator. The use of smart nodes and/or data concentrators assembled on LTCC substrates provides enhanced thermal and vibration performance along with resistance to hydration, improved reliability and reduced overall size of the circuitry unit.

Abstract: A method and apparatus of displaying data in an aircraft, the method including receiving data, from at least one sensor operably coupled to the aircraft, averaging, by a control module, at least two data points of the received data to define a delta and averaged data, comparing, by the control module, the delta to a reference threshold value, and providing an indication, on a display of the aircraft, of the averaged data based on the comparing.

Abstract: A method of and a system for presenting an operating status of an aircraft engine. The method comprises accessing a first indication indicative of a position of an aircraft engine start switch and accessing a second indication indicative of an aircraft engine start operating mode, the second indication having been generated based on an analysis of a parameter associated with an operating condition of the aircraft engine. The method, upon determining that the position of the aircraft engine start switch is an “on” position and the aircraft engine start operating mode is a healthy start causes the display of a visual indication indicative of the healthy start. The method upon determining that the position of the aircraft engine start switch is an “on” position and the aircraft engine start operating mode is an abnormal start causes the display of a visual indication indicative of the abnormal start.

Abstract: The present disclosure provides a computer implemented method of providing an indicator useful for piloting an aircraft. The aircraft comprises an antenna configured to communicate with a transceiver. The method comprises: obtaining an antenna envelope characterizing directions relative to the aircraft for which a directive gain of the antenna exceeds a predetermined threshold; determining a direction of the transceiver relative to the aircraft; calculating a maneuvering range of the aircraft by comparing the antenna envelope and the transceiver direction, wherein the maneuvering range is indicative of eligible orientations of the aircraft for maintaining the transceiver within the antenna envelope; and outputting data indicative of the maneuvering range.

Abstract: A 3-axis camera gimbal is disclosed in the present disclosure. The disclosure gimbal may include: a first supporting body; a lens barrel including a lens group and coupled to the first supporting body in a rotatable manner about a first axis; a rolling driving unit mounted at a first position of the lens barrel to provide force for rotating the lens group about a second axis perpendicular to the first axis; a pitching driving unit mounted to the first supporting body to provide force for rotating the lens barrel about the first axis; a second supporting body coupled to the first supporting body in a rotatable manner about a third axis perpendicular each of to the first and second axes; and a yawing driving unit mounted to the second supporting body to allow the first supporting body to rotate about the third axis. Various embodiments are also possible.

Abstract: Liquid dispensing assemblies including adhesive anchoring assemblies configured to adhere to a support surface external to a device such as a vehicle. An air vehicle includes (a) a fluid adhesive container assembly detachably attached to the air vehicle, wherein the fluid adhesive container assembly comprises: (i) an adhesive container comprising fluid adhesive; and (ii) one or more fibers, wherein the one or more fibers are configured, or a brush of fibers, or a fabric of fibers, is configured to conduct the fluid adhesive and to structurally support an adhesive bond between the one or more fibers and a surface; and (b) means for dispensing the fluid adhesive from the fluid adhesive container, to the one or more fibers.

Abstract: A fluid coupler includes a housing with an inlet port and an outlet port, a piston disposed in the housing and configured to control fluid flow between the inlet port and the outlet port, and a piston retainer disposed in the housing. A piston may include at least one radially-extending support member, and the radially-extending support member may include an aperture. The at least one radially-extending support member may be substantially planar.

Abstract: An aircraft boarding apparatus has a passenger bridge that has a confinement structure coupled to the second passenger bridge. The confinement structure exerts a ground-anchoring effect on the second passenger bridge to offset the ultralight configuration of the passenger bridge.

Abstract: This disclosure provides a joint assembly that thermally isolates a warm structure, such as a payload, from a cold structure, such as a cryogenic fuel tank, in a space vehicle while maintaining structural interconnection within the joint assembly. The joint assembly includes a primary joint that is capable of separating, and a secondary joint connected to and adjacent to the primary joint. The secondary joint includes an inflatable annulus structure and one or more restraining members, where separation of the primary joint causes the inflatable annulus structure to be in compression and the one or more restraining members to be in tension.