Abstract: An underwater body having a movable component which can be moved into a retracted position and, as a result, increases the volume of the underwater body. In addition, a method is disclosed for operating such an underwater body. An expansion means conducts a fluid into a hollow space. The hollow space is operatively connected to the movable component. When the fluid is conducted into the hollow space, the movable component is moved into the extended position relative to the shell of the underwater body. The fluid in the hollow space hardens. The hardened fluid in the hollow space holds the movable component in the extended position.

Abstract: A submarine optical positioning beacon system with self-generating capability, which has an array of underwater beacons. When the underwater rover moves to the vicinity of an certain underwater beacon, the underwater beacon's COMS sensor detects the underwater rover's light and then turns on the LED lamp group. The COMS sensor of the underwater rover analyzes the light species of the LED light group and converts it into digital information. The underwater rover analyzes the digital signal to obtain its location. Each underwater beacon has an independent power generation component, which generates power by utilizing ocean current, greatly increasing the working time of the beacon. The LED lamp group gives positional information feedback through the light, which can reduce the system power consumption and increase the system working duration.

Abstract: An adjustable frame device for a profiled sail device includes a fixed luff-sided first frame portion and a leech-sided second frame portion. The second frame portion includes a first flexible sail batten and a second flexible sail batten that are movable with respect to one another in a sail-batten longitudinal direction to adjust the frame device, with one of the sail battens serving as a compression batten and the other of the sail battens serving as a tension batten. An adjustable profiled sail device includes a first profiled surface against which air can flow, a second profiled surface against which air can flow, with the first profiled surface and the second profiled surface being spaced apart from one another, and an adjustable skeleton device disposed between the profiled surfaces. The skeleton device includes at least one adjustable frame device.

Abstract: There is provided a steering device of an outboard motor to be attached to a boat hull. A swivel bracket to be attached to a side of the boat hull supports a steering shaft to which an outboard motor main body is connected. A steering actuator is disposed above the swivel bracket and the steering actuator generates power in accordance with input from outside. A power transmission mechanism is disposed above the swivel bracket to connect the steering actuator to the steering shaft. The power transmission mechanism transmits the power of the steering actuator to the steering shaft. A cover member is attached to an upper portion of the swivel bracket to cover the steering actuator, the power transmission mechanism, a connection part between the steering actuator and the power transmission mechanism, and a connection part between the power transmission mechanism and the steering shaft.

Abstract: A method of operating a thruster apparatus involves causing a first propeller to rotate in response to pressure of a first flow of pressurized hydraulic fluid, and causing a second propeller to rotate in response to pressure of a second flow of pressurized hydraulic fluid separate from the first flow of pressurized hydraulic fluid. Thruster apparatuses are also disclosed.

Abstract: The present invention is realized by apparatus and methods for harvesting, storing, and generating energy by permanently placing a large rigid buoyant platform high in the earth's atmosphere, above clouds, moisture, dust, and wind. Long, strong and light tethers can connect the buoyant structure to the ground which can hold it in position against wind forces. Weights suspended from the buoyant platform with cables are raised and lowered by electric winches to store and release gravitational potential energy. High voltage transmission lines electrically connect the platform to the earth's surface. Electrical energy from the high voltage transmission lines or from photovoltaic arrays on the platform can be stored as gravitational potential energy and subsequently released as electricity from generators driven from the stored gravitational potential energy and used on the platform or transmitted via the high voltage transmission lines.

Abstract: A structure for an aircraft fuselage, the structure comprising a skin having an outer face and an inner face machined as a grid-stiffened panel, a plurality of frames, each frame shaped as the cross section of the fuselage and the frames being arranged one after the other along a longitudinal direction of the fuselage. The outer perimeter of each frame is secured to the inner face, a plurality of stringers extend parallel to the longitudinal direction, each stringer extending across multiple frames, passing through these at an opening provided to that end in each frame, and each stringer is pressed against the inner face and secured thereto. In the upper part and in the lower part of the fuselage, a torsion box is provided extending parallel to the longitudinal direction, each torsion box comprising a horizontal plate and tabs which secure the plate to the inner face.

Abstract: Unmanned aerial vehicle (UAV) including a flight propulsion system and a support system coupled to the flight propulsion system, the support system comprising a protective outer cage configured to surround the flight propulsion system, wherein the outer cage comprises a plurality of cage frame modules that are manufactured as separate components and assembled together to form at least a portion of the outer cage configured to surround the flight propulsion system.

Abstract: Assemblies and methods for facilitating the assembly of aircraft wings to a fuselage are disclosed. In some embodiments, a wing unit includes features that are configured to define one of more parts of a pressure vessel that is partially defined by the fuselage portion. In some embodiments, the aircraft assemblies disclosed herein comprise one or more first structural interfaces that permit positional adjustment between the wing unit and the fuselage portion so that one or more second structural interfaces may be finished only after such positional adjustment. In some embodiments, the aircraft assemblies disclosed herein comprise one or more structural interfaces that are disposed outside of the wing unit in order to eliminate or reduce the need for assembly personnel to access the interior of the wing unit to carry out the structural assembly of the wing unit to the fuselage portion.

Abstract: Assemblies and methods for facilitating the assembly of aircraft wings to a fuselage are disclosed. In some embodiments, a wing unit includes features that are configured to define one of more parts of a pressure vessel that is partially defined by the fuselage portion. In some embodiments, the aircraft assemblies disclosed herein comprise one or more first structural interfaces that permit positional adjustment between the wing unit and the fuselage portion so that one or more second structural interfaces may be finished only after such positional adjustment. In some embodiments, the aircraft assemblies disclosed herein comprise one or more structural interfaces that are disposed outside of the wing unit in order to eliminate or reduce the need for assembly personnel to access the interior of the wing unit to carry out the structural assembly of the wing unit to the fuselage portion.

Abstract: A fuel tank dam comprises a first section, a second section, a third section, and a flange section. The first section can be fixed to a first structural component, and the second section can be fixed to a second structural component. The third section has a bellows comprising a plurality of folded sections and is disposed between the first section and the second section. The flange section extends along an outer plate at least from an edge section of the third section and can be fixed to the outer plate.

Abstract: A strake for a turbine engine nacelle may comprise a forward portion coupled to a turbine engine nacelle inlet, and an aft portion coupled to a turbine engine nacelle fan cowl, wherein the aft portion is configured to move between a first position and a second position, and the aft portion engages the forward portion in response to the aft portion moving to the second position to secure the fan cowl with respect to the inlet.

Abstract: The present disclosure relates to a cell structure for an acoustic attenuation device for a nacelle of an aircraft propulsion assembly. This cell structure includes lateral partitions forming channels that each extend between a first end and a second end and skin elements arranged so that each channel is at least partly closed at the first end thereof by at least one skin element. Each skin element is connected to a respective lateral partition and can move relative to the other lateral partitions. A continuous skin can be assembled on this cell structure so as to at least partly close the channels at the second end thereof and to thus form an acoustic attenuation device.

Abstract: An aerodynamic surface for an aircraft, comprising a torsion box, a movable control surface, and a central element, the torsion box comprising a rear spar, upper and lower covers, and the movable control surface comprising a leading edge, a front spar, a hinge line, a beam having a first end and a second end, and a counterweight attached to the second end of the beam. The first end of the beam is attached to the front spar, and the second end is projected beyond at least the hinge line so that the counterweight is arranged between the upper and lower covers extending from the rear spar of the torsion box towards the movable control surface.

Abstract: Braking systems for aircraft are disclosed. An example braking system includes a parachute launching system configured to deploy a parachute from a stowed position within a launch tube of the parachute launching system to a deployed position in an airstream of the aircraft. The system also includes a parachute retrieval system including a first cable configured to recover the parachute from the deployed position to the stowed position for subsequent use.

Abstract: A propeller system includes a rotatable housing having at least one propeller blade mounted thereon and an electric pitch control motor within the rotatable housing. A pitch control member is coupled to the propeller blade and extends through a wall of the rotatable housing. The pitch control motor is configured to move the pitch control member and to thereby vary the pitch of the propeller blade.

Abstract: A system for controlling a propeller having a plurality of blades having a primary control system and a backup control system. The primary control system including a sensor responsive to a propeller state, and a controller connected to the sensor and to an electrohydraulic control actuator. The electrohydraulic control actuator connected via a bypass valve to a hydraulic actuator that controls at least a blade angle of a blade of the propeller. The controller generating commands to the electrohydraulic control actuator based on at least the propeller state. The backup control system including a second controller, an electrohydraulic solenoid operably connected to the bypass valve. The backup control system operable to hydraulically disable the primary control system via the bypass valve upon the occurrence of a selected condition, the second controller modulates the operation of the electrohydraulic solenoid to control the bypass actuator based on the propeller state.

Abstract: Apparatus for controlling multi-rotor vehicle vibrations and related methods are disclosed herein. An example apparatus includes a vibration level detector to determine a vibration level of a frame of a vehicle based on data received from a sensor of the vehicle, the vehicle including a rotor. The apparatus includes a rotor operation analyzer to determine an operational parameter of the rotor based on the vibration level. The apparatus includes a communicator to transmit an instruction including the operational parameter to a controller of the rotor.

Abstract: Methods and systems according to one or more examples are provided for reducing chatter in a no-back brake during aiding load operations. In one example, an apparatus comprises a no-back brake, disposed within an actuator coupled to an aircraft, including a shaft, and a ball ramp plate, coupled to the shaft, to receive a force comprising an air loading force and is displaced responsive to the force. The apparatus further comprises a brake, coupled to the shaft and coupled to the ball ramp plate, and displaced by the ball ramp plate corresponding to a distance the ball ramp plate is displaced. The apparatus further comprises a modulating spring, coupled to the shaft and coupled to the brake, configured to compress in response to the brake being displaced, and the modulating spring is configured to apply a selective compressive force at the brake corresponding to a distance the brake is displaced.

Abstract: An aircraft is provided and includes fuselage having a nose, a main section aft of the nose and a tail aft of the main section, an engine nacelle partially embedded in the tail and including a boundary layer ingestion (BLI) propulsor with an inlet directly adjacent to the fuselage and a nozzle element disposed upstream from the inlet and configured to accelerate boundary flows flowing toward the interior side of the engine nacelle.

Abstract: Braking systems for aircraft are disclosed. An example braking system includes a fan cowl having a leading edge and a trailing edge. The braking system includes a hinge assembly coupled between the leading edge and a fan cage of an aircraft engine to enable the fan cowl to move between a stowed position and a deployed position. An actuator is coupled to the leading edge of the fan cowl, and the actuator is to move the fan cowl via the hinge from the stowed position to the deployed position in a direction away from the aircraft engine and toward a fore end of the aircraft to provide an air brake during a braking event.

Abstract: A method for protecting the landing gear of an aircraft against stroke-end shocks, the landing gear being manoeuvrable between a retracted position and a deployed position by means of a single electromechanical operating actuator (10) between these two positions. According to the invention, the method involves the step of equipping the electromechanical operating actuator with an internal damping device (17) arranged between an output shaft (18) of the electromechanical actuator coupled to the landing gear and a motor shaft (13) with a motor (12) of the electromechanical actuator.

Abstract: A heat shield assembly is disclosed. In various embodiments, the heat shield assembly includes a first heat shield segment having a first end and a second end spaced from the first end, the first end including a first hook member and the second end including a second hook member; and a first heat shield retainer including a first clip member configured to engage the first hook member and a second clip member.

Abstract: Braking systems for aircraft are disclosed. An example braking system includes a brake pad movably coupled to a lower section of a fuselage of the aircraft. The brake pad is movable between a stowed position and a deployed position. An actuator is configured to deploy the brake pad from the fuselage during an emergency braking event. The brake pad to engage a surface of a runway and increase frictional force to reduce a speed of the aircraft during the emergency braking event.

Abstract: A system and method are provided for continuous monitoring and controlling of aircraft braking that can reduce brake wear and aircraft operating costs through the retention of carbon brake powder from the brakes or addition of carbon powder in a device mounted with respect to the brake disc stack. The use of carbon powder reduces brake wear by providing small particles between the brake discs, acting as a buffer between the brake discs when the brake stack is clamped together. Moreover, when carbon powder or small particles are used at application, such use reduces the roughness of the carbon surface and reduces the number of large particles from braking off the carbon surface, thereby reducing brake wear. Adaptive or selective braking may be used in conjunction with carbon powder to further reduce carbon brake wear.

Abstract: A tiltrotor aircraft may be provided and may include a mast assembly, in which the mast assembly may include a mast; a bearing system; a housing; and a housing cap secured to the housing, wherein the bearing system is between the mast and the housing. The bearing system may further include a first bearing assembly including a first inner race, a first outer race, and a plurality of first tapered roller bearings; a second bearing assembly including a second inner race, a second outer race, and a plurality of second tapered roller bearings; an inner spacer and an outer spacer in which the inner and outer spacers are between the first and second bearing assemblies; and a retaining device in which the retaining device and the housing cap provide, at least in part, pre-loading for the first and second bearing assemblies.

Abstract: The present invention relates to systems and methods for powering and controlling flight of an unmanned aerial vehicle. The unmanned aerial vehicles can be used in a networked cellular communication system. A tether management system can be used to facilitate both mobile and static tethered operation to provide power and/or voice and data communication.

Abstract: In an aspect, in general, a spooling apparatus includes a filament feeding mechanism for deploying and retracting filament from the spooling apparatus to an aerial vehicle, an exit geometry sensor for sensing an exit geometry of the filament from the spooling apparatus, and a controller for controlling the feeding mechanism to feed and retract the filament based on the exit geometry.

Abstract: An unmanned aerial vehicle (UAV) launch system includes a launch container including a housing defining an internal chamber. A UAV includes a main body defining an inflatable envelope. The UAV is configured to be contained within the internal chamber. The main body is in a deflated state when the UAV is contained within the internal chamber. A reactant is configured to react with water to produce a lifting gas. The inflatable envelope is configured to be inflated by the lifting gas in response to the reactant reacting with the water to deploy the UAV from the launch container.

Abstract: A system composed of at least two unmanned aerial vehicles, each aerial vehicle comprising a drive unit, a flight control unit for controlling the trajectory of the aerial vehicle by means of the drive unit and a rechargeable power cell. Each aerial vehicle comprises an electrical first interface, and the system comprises at least one transport device with at least one chamber defined by boundary elements, in particular corner elements, for receiving the aerial vehicles stacked essentially vertically in the operating position and an electrical control and supply system for charging the power cells and/or for communicating with the flight control units via the first interfaces.

Abstract: Balancing a drone is difficult with engines, when drones are equipped with engines to increase the flight time. However, balancing the drone can be made easy by providing the drone with an electric motor or an electric motor that involves a generator feature.

Abstract: A method is provided for sending a drone to a user on request. The method includes providing software, an instance of which is installed on a plurality of mobile technology platforms, wherein each mobile technology platform is associated with a user and is equipped with a tangible, non-transient medium having an instance of the software installed therein. The software contains suitable programming instructions which, when executed by a processor, perform the steps of (a) displaying, on a display associated with the mobile technology platform, a graphical user interface (GUI) having a user selectable object displayed thereon, (b) determining when the user selectable object has been selected by a user, and (c) when the user selectable object has been selected by the user, (i) determining the current location of the user via the location awareness functionality, and (ii) transmitting a request for a drone, wherein the request includes the determined current location of the user.

Abstract: A propulsion device and a single-rotor unmanned aerial vehicle are provided. The propulsion device includes a duct, a main rotor, and at least two grid wings. The main rotor is located in the duct and is configured to drive fluid to flow in the duct to generate power. The at least two grid wings are located on a side of the main rotor, and a grid wing has a plurality of grid walls spaced apart and extended along an axial direction of the duct. Two side edges of a predetermined cross section of each grid wall have different shapes to generate a lift force under a pressure difference of the fluid flowing through the grid wing. The grid wing is configured to form a torque opposite to a torque of the main rotor under the lift force.

Abstract: An intermittent fluid delivery system includes a fill tank and a batch tank which is connected to the fill tank via a first pump and a first hose. The fill tank holds a first quantity of fluid. The batch tank holds a second quantity of fluid, which is lesser than the first quantity. The first pump delivers fluid from the fill tank to the batch tank. A second pump delivers fluid from the batch tank to a receiving tank.

Abstract: A transformable seat assembly includes a seat support structure and a back support structure connected to the seat support structure with a hinge defining an axis of rotation. An actuator assembly includes a cylinder and a piston positioned within the cylinder, wherein the cylinder is secured to one of the back support structure or the seat support structure and the piston is secured to other of the one of the back support structure or the seat support structure. Additionally a blocking member is positioned within and adjustable along the cylinder. With blocking member in a first position, piston is limited to travel to a first limit position and the back support structure to a first reclined position. With the blocking member in a second position, piston is limited to travel to a second limit position and back support structure is permitted to rotate to second reclined position.

Abstract: Transformable seat assembly includes a seat support structure and back support structure connected with an axis of rotation. Actuator assembly includes a cylinder and a piston positioned within the cylinder. The cylinder is secured to one of the back support structure or the seat support structure and the piston is secured to other of the one of the back support structure or the seat support structure. With blocking member in a first position, the piston is permitted to travel between the blocking member and an end of the cylinder spaced apart from the blocking member, such that with the piston traveling to the end of the cylinder, rotation of back support structure is limited from rotating beyond a first reclined position and with blocking member in a second position, back support structure is permitted to rotate into an overlying position relative to the seat support structure.

Abstract: A transformable seat assembly which includes a seat support structure and a seat connected to the seat support structure with a hinge. The hinge defines an axis of rotation. A back support structure connected to the seat support structure, which extends in an upward direction relative to the seat support structure. A back cushion is secured to the back support structure and a lumbar cushion extends along the back support structure positioned between the back cushion and the seat, wherein the lumbar cushion is releasably secured to one of the back cushion or the back support structure and an end portion of the seat positioned closer to the back support structure with the seat positioned in an occupant support position than the hinge, can rotate in a direction of rotation about the axis of rotation, which includes the upward direction and a direction away from the back support structure.

Abstract: Systems, methods, and computer-readable media storing instructions for utilizing space associated with unoccupied seats in organized seating arrangements are disclosed herein. The disclosed techniques identify unoccupied seats within an organized seating arrangement, such as seats on an aircraft. Upgradable seats within the organized seating arrangement are determined based upon the unoccupied seats and the transformation capabilities of the seats. Upgradable seats are directly in front of or behind unoccupied seats, such that either the upgradable seat or the associated unoccupied seat is transformable to enable an upgrade. An occupant of a seat is selected for an upgrade associated with an upgradable seat and assigned the upgrade to enable the occupant to utilize a portion of the space associated with the unoccupied seat while sitting in the upgradable seat.

Abstract: A console assembly and aircraft passenger seat arrangement including the same, the console assembly including a vertical back panel for affixing to a side wall of a static structure. The console assembly further including upper and lower tiers affixed to and extending horizontally from the vertical back panel, in which the upper tier is above and spaced apart from the lower tier. The lower tier may include a modular front panel for mounting electric devices, such as power ports and in-flight entertainment devices, for example. Thus, the vertical stacking of the upper and lower tiers may allow for condensed stowage space, while maintaining clear visual aesthetics without hiding useful features from view.

Abstract: The invention provides a kit of parts for assembling an aircraft seat unit, comprising a frame with a slot, a panel for forming a shell of the aircraft seat unit and defining a footprint of the aircraft seat unit, having a first end and a second opposite end, the first end configured to be slid in and out of the frame slot to provide a variable dimension from the frame to second opposite end of the panel, and a fixing mechanism for fixing the panel within the frame slot, in a configuration providing a desired value of aircraft seat unit variable dimension. The invention also provides a plurality of such kits of parts, an aircraft seat unit and an aircraft cabin comprising a plurality of such aircraft seat units or made from such kit of parts, and methods of installing an aircraft seat unit.

Abstract: A headrest frame for a seat is disclosed. In various embodiments, the headrest frame includes a main body portion having a stowed length; a top portion configured to assume a stowed position and a deployed position with respect to the main body portion, the deployed position defining a deployed length greater than the stowed length; and a deployment mechanism configured to urge the top portion into the deployed position from the stowed position.

Abstract: Transformable seat assembly includes a seat support structure and a seat connected to the seat support structure with a first hinge having a first axis of rotation. A back support structure is connected to the seat support structure with the back support structure positioned on a back side portion of the seat support structure and the first hinge is positioned on an opposing front side portion of the seat support structure. A wall member having a first end portion connected to the back support structure with a second hinge having a second axis of rotation, wherein the seat is rotatable about the first axis of rotation from an occupant support position to a deployed position and the wall member is rotatable about the second axis of rotation from an overlying position with respect to the back support structure to the wall member extending away from the back support structure.

Abstract: An aircraft seating unit includes a base, a seat coupled to the base, a housing coupled to the base and enclosing frame elements of at least one of the base or the seat, and an ottoman. The housing defines a recess at a location below and to a rear of the seat. The ottoman is disposed within the recess. The ottoman includes a guide coupled to at least one of the frame elements, a slide translatable along the guide, a foot platform coupled to the slide, and an actuator positioned to facilitate selectively translating the slide along the guide to reposition the foot platform between a stowed position and a deployed position. The guide defines a translation axis that is angled relative to a vertical axis such that the foot platform moves both vertically and horizontally as the slide translates along the guide.

Abstract: Systems and methods provide airflow to a first area from a second area within a vehicle. The system includes a fan mounted within a door separating the first area from the second area. The fan is configured to direct airflow from the second area into the first area. The fan having a shield positioned adjacent to the second area that is configured to conceal the fan.

Abstract: An environmental control system of an aircraft including a compression device including a compressor having a compressor inlet and a compressor outlet, a primary inlet for supplying a first medium to the compressor inlet, and a secondary inlet for supplying a second medium to the compressor inlet.

Abstract: An anti-icing system is disclosed. In various embodiments, the anti-icing system includes an inner duct having a first end configured to deliver heated gas to a plenum and a second end spaced from the first end; an outer duct circumferentially encompassing at least a portion of the inner duct; and a seal system disposed proximate the second end, the seal system including a first annular seal having a radially inner end positioned proximate a flange disposed on the inner duct.

Abstract: Disclosed is a multilayer structure, comprising: a first heater layer comprising a CNT heater, wherein the CNT heater comprises a composite of carbon nanotubes and silicone; and a second heater layer comprising a PTC heater, wherein the PTC heater comprises a composite of carbon black and polymer; wherein the first heater layer and the second heater layer are first and second respectively in an electrical series; wherein the first heater layer has a negative temperature coefficient with respect to electrical resistivity; and wherein the second heater layer has a positive temperature coefficient with respect to electrical resistivity. Also disclosed is an aircraft component comprising the multilayer structure.

Abstract: A method of making an adhesive for an ice protection assembly includes transferring Z-CNTs from a substrate carrier into the adhesive. De-bonding of the adhesive for ice protection assembly inspection or repair or repositioning at initial installation includes heating the Z-CNTs in the adhesive to soften the adhesive and allow for easy removal.

Abstract: A method of making an adhesive for an ice protection assembly includes mixing ferrous nanoparticles into the adhesive. Removal of the adhesive for ice protection assembly inspection or repair includes heating the ferrous nanoparticles in the adhesive to soften the adhesive and allow for easy removal or repositioning of the ice protection assembly.

Abstract: An apparatus for the detection of either or both of water and ice within a system, more specifically, but not exclusively, the detection of either or both of water or ice crystal ingestion, or ice accretion on an aerofoil, within a gas turbine engine. The apparatus and method compares the measured temperature of the first region with a second temperature value, measured at a distinct second region of the aerofoil, wherein the second radial position of the second sensor is radially offset from the first radial position of the first sensor.