Abstract: Disclosed are a solar cell panel and a bicycle. The solar cell panel includes output busbars and a plurality of solar cell groups connected in parallel between the output busbars. Each of the solar cell groups includes a plurality of solar cell strings connected in series, and each of the solar cell strings includes a plurality of solar cells connected in series.

Abstract: The invention relates to a system for providing an air lubricating layer between the hull of a vessel and the water flowing under the hull as said vessel is moving through the water, comprising an air cavity and a wave deflector having a planar bottom surface which faces said interface plane and extends parallel thereto and is arranged in an air cavity of said air lubrication system at a distance of 2-15 cm from the interface plane, wherein said bottom surface has a peripheral edge that is spaced apart from said sidewalls by a gap having a width of 0.5-15 cm, wherein, when viewed in projection onto a plane wherein said planar bottom surface extends, at least 85% of the area of said opening is covered by said wave deflector and/or said planar bottom surface thereof, more preferably at least 90%, and most preferably at least 95%.

Abstract: A cover for a vehicle, such as a boat, including a ratchet and straps. The straps are connected to a plate for evenly distributing the load placed on the straps when the straps are tightened by the ratchet. The straps, when tightened, provide form to the cover such that water will run off the cover.

Abstract: A hydraulic mooring cable holding device provides a hydraulic cylinder-piston combination (20) for controlling the force on a mooring cable between one end of a ship and a mooring point. An overpressure protection part (26) with hydraulic liquid passing from the hydraulic cylinder (20) to a reservoir (260) when the pressure in the cylinder exceeds a threshold value, and returns the hydraulic liquid when the pressure has dropped. An auxiliary reservoir (24) with a steeper pressure response than the main reservoir (260) is connected in parallel with the main reservoir. The auxiliary reservoir may be connected to and/or disconnected from the cylinder under control of a sensor or a further mooring device at the other end of the ship, to reduce movement of the ship e.g. in swell. Furthermore, pressure from the auxiliary reservoir may be used to drive an electric generator.

Abstract: A natural gas liquefaction vessel including an increased deadweight tonnage, as compared to a liquefied natural gas carrier (LNGC) of a comparably-sized ship, is achieved by reducing the LNGC's cargo capacity. This difference creates room on the port and starboard sides of cargo tanks to increase the size of the adjacent wing tanks. The increased size of the wing tanks occupy the space created by the reduced cargo tank size of the vessel and may support a larger upper trunk deck. The ballast wing tanks and smaller cargo tanks increase the deadweight available. With this approach, the larger upper trunk deck of the vessel is able to support an efficient floating liquefaction plant that improves the LNG value chain because it is capable of producing 2.0-3.0 MTPA in the footprint of a standard vessel hull, such as for example a Q-Max hull.

Abstract: The present invention relates to a container transportation ship. More particularly, the present invention relates to a container transportation ship for transporting containers, characterized in that a loading space in which at least one container is loaded and a loading/unloading space configured such that an external transfer means can directly enter/exit in order to load and unload the container, are delimited on the deck of the container transportation ship; and a crane is provided to move the container in the longitudinal direction of the container transportation ship, in the transverse direction thereof, and in the upward/downward direction thereof for the purpose of loading the container on the external transfer means that has entered the loading/unloading space or unloading the container from the external transfer means.

Abstract: A surfboard having laterally opposed pairs of axial or lengthwise grooves with the pair forming opposed rails of greater stiffness and reduced mass. At least one of the grooves of each pair is at a board edge extremity and the other groove is nearby, preferably near or on the lower side of the surfboard. The grooves may be laid up with epoxy or fiberglass.

Abstract: Disclosed is a coupling system for coupling a piece of equipment rigidly connected to a user with at least one rigging strand, including a central body made of two parts configured to be assembled with one another via an attachment unit, a fastener including two ends, a shell configured to at least partially cover the side surface of the central body, and at least one lock configured to engage with the shell in order to releasably lock the second end of the fastener, the shell being movable in translation over the side surface of the central body and being connected to the central body via at least one elastic recall component.

Abstract: Disclosed is a control device for power kites. It consists of a tall Y-shaped structure, the base of which is connected to the center of a horizontal control bar arranged perpendicular to the structure. An articulation forms the connection between the base of the structure and the center of the horizontal control bar. The control lines for the leading edge and the control lines for the trailing edge of a power kite are attached to the front and rear pre-lines of the device. Compared to a standard kite bar, the disclosed control device makes it easier for the user to balance using very short lines.

Abstract: A measurement device for use with a traction pad. The measurement device may include a first container configured to hold a sensor, the first container including an opening connecting an inner side of the first container with an outer side, a second container configured to hold a processor, a watertight passage between the first and second containers which allows a signal communication between the sensor and the processor, a lid configured to seal the first and second containers, a power supply configured to supply power to the processor, and a switch disposed on an end of the measurement device which is accessible to a user.

Abstract: An apparatus (10) for lifting and moving an object that is underwater. The apparatus including a first (12) and a second (14) chamber, both chambers containing a first (16) and a second (18) fluid. There is a conduit (20, 21) in fluid communication with the first and second chambers, the first and second fluids moveable between the first and second chambers.

Abstract: A marine vessel has a hull with a bottom, a bow, a stern, and a propulsion arrangement including at least three propulsion units arranged at the stern of the marine vessel. The marine vessel has a base line and a centerline. The at least three propulsion units include a fixed centerline shaft propulsion unit with a shaft line and a propeller, and two turnable propulsion units with respective propellers and arranged at opposite sides of the fixed centerline shaft propulsion unit for steering of the marine vessel. For improving thrust efficiency, while maintaining optimal steering capability, the propeller of the fixed centerline shaft propulsion unit is arranged at a given distance aft of the stern of the marine vessel.

Abstract: The invention relates to a “wing” type rigid sail fragmented into independent segments, where general principle involves diving the rigid sail into different segments that can position themselves independently from neighboring segments, depending on the wind received, with the profile of the sail controlled following two independent but complementary methods, where the segments at the front of the sail are linked together by their front flap, through a process that allows adjusting their relative freedom, playing on the angle that each segment can take compared to neighboring segments, and on the back of the “sail sheet”, the rope allowing sail adjustment links each segment by its back flap, top to bottom, allowing for adjustment of the opening up of the sail while keeping the desired flexibility of the sail.

Abstract: A marine outboard motor mount fastener retainer, system, and method are presently disclosed. The fastener retainer has a first end portion configured to be held about a first motor mount fastener and a second end portion configured to be held about a second motor mount fastener. An extension extends from the first end portion of the motor mount fastener retainer to the second end portion of the motor mount fastener retainer. The extension is configured to hold the first and the second end portions of the retainer and to prevent rotation of the first and the second motor mount fasteners.

Abstract: A buoyant aerial vehicle includes: a balloon configured to store a gas; a payload coupled to the balloon; and a propulsion unit coupled to the payload by a tether. The propulsion unit includes: a fuselage having a substantially longitudinal shape, a first end, and a second end; a primary airfoil coupled to the fuselage; a secondary airfoil coupled to the fuselage at one of the first end or the second end; and a thrust generating device disposed at one of the first end or the second end and configured to move the propulsion unit relative to the payload along a propulsion flight path. The movement of the propulsion unit imparts movement of the buoyant aerial vehicle along a vehicle flight path.

Abstract: A system for controlling an aerial vehicle includes an aerial vehicle, a ballast coupled to the aerial vehicle, a server including a processor and a memory, and a wireless communication link that communicatively couples the aerial vehicle and the server. the memory stores instructions that, when executed by the processor, cause the server to receive weather data, determine, based on the weather data, that the aerial vehicle is experiencing, or is expected to experience, weather that satisfies a predetermined criterion, and cause the aerial vehicle to decouple at least a portion of the ballast based on a result of the determination.

Abstract: The present disclosure relates to an aircraft. The aircraft has a primary structural element, which extends along a main axis of the aircraft, and at least one monolithic structural component, which is produced by a three-dimensional printing method. The aircraft also has an aircraft system for carrying out an aircraft-specific function. The at least one monolithic structural component is fixed on the primary structural element by a fixing device, system, means, or mechanism. The monolithic structural component is embodied to accommodate the aircraft system. The disclosure also relates to a method for producing an aircraft.

Abstract: A stiffener for an aircraft assembly is disclosed. The stiffener provides structural stability to the aircraft assembly. The stiffener has a first stiffener part having a planar web portion and a second stiffener part arranged with the first stiffener part. The second stiffener part includes a corrugated web portion having a corrugation. The present application also relates to an aircraft assembly, a fuselage for an aircraft, an aircraft and a method of forming a stiffener for an aircraft assembly.

Abstract: A wide body aircraft is discussed having a fuselage with a first structural element, a second structural element, a wide-body fuselage section, and a plurality of tension members. Each of the first structural element and the second structural element may be arranged to traverse a longitudinal length of the wide-body fuselage section. The wide-body fuselage section may comprise a set of side-by-side fuselage subassemblies, where the set of side-by-side fuselage subassemblies can be coupled to one another via the first structural element and the second structural element. The plurality of tension members can be arranged to manage tension between the first structural element and the second structural element. The plurality of tension members can be configured to remain flexible under a compression load, while managing tension therebetween.

Abstract: A seal plate (201) for maintaining a continuous aerodynamic surface between a fixed part (302) of an aerostructure such as an aerofoil (103) and a movable surface such as a spoiler (304) is provided. The seal plate (201) includes a resilient material such as fiberglass and has an aerodynamic surface (203). It is configured to be mounted to the fixed part (302) of the aerofoil along one edge (205) and to slidably seal with the control surface (304) at a second edge (207). The seal plate (201) is stepped and has a rigid lever (217) to engage behind the control surface (304) to bend the seal plate precisely according to movement of the control surface (304) and maintain the continuous aerodynamic surface.

Abstract: A nacelle forward part of an aircraft propulsion assembly, includes an air inlet lip at the front end, an internal structure and an external panel extending the lip, and an annular stiffening frame formed around an axis of revolution and comprising an internal peripheral edge linked to the internal structure and an external peripheral edge linked to the external panel. The stiffening frame presents an inclination relative to the axis of revolution, its slope being oriented towards the front end of the nacelle forward part. The stiffening frame is configured to deviate, outside the nacelle of the propulsion assembly, an object striking the stiffening frame. The stiffening frame so configured is capable of withstanding the impacts of objects without breaking while enabling the object striking the stiffening frame to be deviated towards the exterior of the nacelle.

Abstract: An unmanned aerial vehicle includes a propulsion system including a driving device having a main body, a driving shaft rotatable relative to the main body, and a locking member disposed on the main body. The locking member includes at least one snap-fitting member. The propulsion system also includes a propeller coupled with the driving device, the propeller including a blade base and a blade mounted on the blade base. The at least one snap-fitting member is configured to snap-fit with the propeller. The propulsion system also includes an elastic abutting member sleeve coupled with the driving shaft, a first installation foolproof member disposed on the blade base, and a second installation foolproof member disposed on the locking member.

Abstract: The present invention relates to a rotor assembly where associated electric motors are configured to rotate the rotor, control the collective pitch of the rotor/assembly, and/or control the cyclic pitch of the rotor/assembly, by varying the relative rotational angle between two or more of the associated electric motors.

Abstract: A high stiffness hub assembly for a rotor system operable to rotate with a mast of a rotorcraft. The hub assembly includes a yoke and a constant velocity joint assembly. The yoke has a plurality of blade arms each configured to hold a rotor blade. The constant velocity joint assembly provides a torque path from the mast to the yoke that includes a trunnion assembly, a plurality of drive links and a plurality of pillow blocks. The trunnion assembly is coupled to the mast and has a plurality of outwardly extending trunnions. Each drive link has a leading bearing coupled to one of the trunnions and a trailing bearing coupled to one of the pillow blocks. Each pillow block is independently mounted between an upper surface of the yoke and a hub plate.

Abstract: A wing for an aircraft, including a main wing, a slat, and a connection assembly movably connecting the slat to the main wing, such that the slat is movable between a retracted position and at least one extended position. The connection assembly includes a first connection station and a second connection station spaced apart from the first connection station in a wing span direction. The object, to prevent the slat from skewing, is achieved in that the connection assembly includes a sync shaft coupling the first connection station to the second connection station for sync movement of the first and second connection stations.

Abstract: An aircraft, a control surface arrangement, and a method of assembling an aircraft are disclosed herein. In an exemplary embodiment, the aircraft includes, but is not limited to, an airframe, a control surface, and a rotary actuator. The rotary actuator rotatably mounts the control surface to the airframe. The rotary actuator supports the control surface on the airframe and is configured to rotate the control surface with respect to the airframe when the rotary actuator is actuated. The rotary actuator is further configured to deliver torque to the control surface from a longitudinally intermediate portion of the rotary actuator.

Abstract: The invention pertains to a remote-controlled miniature aircraft with at least one lift surface (17), with at least one pair of propeller drives (12, 13) and with a weight element (20), the position of which can be varied in the longitudinal direction of the miniature aircraft (10) in order to change the center of gravity of the miniature aircraft (10). In order to realize a more compact and more robust construction with improved flying characteristics, the lift surface (17) of the miniature aircraft (10) is arranged above a plane defined by the rotational axes of the propeller drives (12, 13) in order to generate a lifting force for taking off and/or landing from a standstill.

Abstract: A multi horizontal rotor drone having a propulsion unit coupled to a payload housing by a multi-axial gimbal assembly. The centers of mass of each of these three components resides at a common point that also coincides with the pitch and roll axes (and optionally the yaw axis) of the gimbal assembly's rotational orientations. The propulsion unit has the minimal operational mass necessary while the majority of the drone's mass is located onto the payload housing. With this arrangement, the payload housing can be stabilized on its center of gravity independent of the roll, pitch and yaw changes undergoing by the propulsion unit, during the drone's flight.

Abstract: A flow body for a vehicle having a flow surface, as well as a skin system attached to the flow surface is proposed. The skin system has a top layer and a foam arrangement positioned between the flow surface and the top layer, wherein the top layer includes an elastic, surface-like material, wherein the foam arrangement includes a first layer of an elastic, compressible open cell foam, wherein the foam arrangement is bonded to the top layer. The skin system has a static shape in an unloaded state, in which the shape defines an outer surface geometry that directly follows the geometry of the respective flow surface, and the skin system has a deflected shape when the flow body is subjected to turbulent air flow. The deflected shape at least temporarily compresses the foam arrangement.

Abstract: A rotor support device includes a plurality of first electrodes, a plurality of second electrodes, a dielectric material, and at least one alternating-current power supply. The dielectric material is disposed between the plurality of first electrodes and the plurality of second electrodes. The at least one AC power supply is configured to apply an alternating-current voltage across the plurality of first electrodes and the plurality of second electrodes and induce flows of gas by causing dielectric barrier discharge between the plurality of first electrodes and the plurality of second electrodes. At least one of the plurality of first electrodes or the plurality of second electrodes is disposed apart from each other in a static system that is stationary with respect to a rotor provided in an aircraft. The static system is adjacent to the rotor.

Abstract: A flow control apparatus includes a plasma actuator, a storage device, and a control circuit. The plasma actuator causes discharge in a discharge area by applying an alternating-current (AC) voltage between electrodes to form an induced flow of gas. The electrodes are shifted relatively to each other with a dielectric disposed between them. The storage device stores a changing condition of an AC voltage waveform for changing a gas flow state formed in a flow control area of gas from a first state to a second state by adding the induced flow of gas. The control circuit refers to the changing condition of the AC voltage waveform and control the AC voltage waveform based on the changing condition of the AC voltage waveform, in a case of changing the gas flow state formed in the gas flow control area from the first flow state to the second flow state.

Abstract: An aircraft support leg (2), the support leg (2) being movably connected to a main body of an aircraft. The support leg (2) can rotate to at least a first position and a second position. At the first position, an angle is provided between the support leg and the main body of the aircraft, and at the second position, the support leg (2) substantially abuts against the main body of the aircraft or is at least partly arranged in the main body of the aircraft. Such a support leg is convenient for the storage of the aircraft. Also disclosed are a control method for said support leg and an aircraft having said support leg and a control method for the aircraft.

Abstract: The invention provides methods and systems for controlling speed of an aircraft during an autonomous pushback manoeuvre, i.e. under the aircraft's own power without a pushback tractor. The method includes applying a torque to at least one landing gear wheel of the aircraft, the torque being in a direction opposite to the backwards rolling direction of rotation of the landing gear wheel. The torque applied does not exceed a limit for ensuring aircraft longitudinal stability. For longitudinal stability the torque applied should not cause the aircraft to risk a tip-over event.

Abstract: Systems and methods for enabling aircraft shock strut shrink are provided. The system may comprise a shock strut comprising a shrink piston, an accumulator comprising a gas piston and a hydraulic chamber, wherein the gas piston is configured to apply gas pressure to the hydraulic chamber, and a first valve in fluid communication with the accumulator. The system may further comprise a second valve, wherein the second valve is in fluid communication with a vent, the pneumatic cylinder, and the gas piston, wherein the first valve is in fluid communication with the hydraulic chamber and the shrink piston.

Abstract: A manned or unmanned aircraft has a main body with a circular shape and a circular outer periphery. One or more rotor blades extend substantially horizontally outward from the main body at or about the circular outer periphery. In addition, one or more counter-rotation blades extend substantially horizontally outward from said main body at or about the circular outer periphery, but vertically offset from the main rotor blades.

Abstract: A manned or unmanned aircraft has a main body with a circular shape and a circular outer periphery. One or more rotor blades extend substantially horizontally outward from the main body at or about the circular outer periphery. In addition, one or more counter-rotation blades extend substantially horizontally outward from said main body at or about the circular outer periphery, but vertically offset from the main rotor blades.

Abstract: The present invention provides a motor for a drone, comprising: a rotary shaft; a stator including a hole in which a rotary shaft is arranged; and a rotor arranged on the outer side of the stator, wherein the rotor comprises: a cover part coupled with the rotary shaft and covering the upper part of the stator; a body part covering a side portion of the stator; and a plurality of magnets arranged on an inner circumferential surface of the body part so as to be spaced from each other, wherein the body part includes a plurality of groove portions arranged so as to be spaced from each other, thereby providing an advantageous effect of reducing the weight of a drone by reducing the weight of the rotor.

Abstract: A rotor for a hover-capable aircraft is described that comprises: a hub rotatable about a first axis and at least two blades hinged to the hub; each blade comprises a main portion hinged to the hub and a tip portion, which is arranged radially outermost with respect to first axis with respect to the corresponding main portion; the tip portion of each blade is movable with respect to the corresponding main portion of that blade; the tip portion of each blade is selectively movable with respect to the corresponding main portion of that blade between a first position, in which it defines a dihedral or anhedral angle with respect to the corresponding main portion; and a second position, in which it defines a positive or negative sweep angle with respect to the corresponding main portion.

Abstract: A thick airfoil shape that is to form a blade neck for blades, the blade neck connecting a blade root to a streamlined portion of the blade, and/or a blade cuff connecting a blade to the hub of an aircraft rotor. The thick airfoil shape has a leading edge and a trailing edge together with thick airfoil profiles for which the particular positions of points defining the maximum thickness of each airfoil profile make it possible to improve the aerodynamic behavior of the thick airfoil shapes and of the rotor during rotation of the rotor while the aircraft is advancing, for the blade both when it is advancing and when it is retreating. The thick airfoil shape also serves to reduce the vibration as generated by a wake from the rotor on a tail boom or a horizontal and/or vertical stabilizer of the aircraft.

Abstract: Embodiments of the present disclosure disclose a water surface detection method, an unmanned aerial vehicle landing method and an unmanned aerial vehicle. The detection method includes: controlling the unmanned aerial vehicle to generate an airflow, where the airflow is used to generate a water surface ripple; obtaining an image of a landing area of the unmanned aerial vehicle and a flight parameter of the unmanned aerial vehicle; and processing the image, and determining, with reference to the flight parameter, whether the landing area has the water surface ripple. Damage caused by erroneous landing of the unmanned aerial vehicle on a water surface can be alleviated by determining whether the landing area has the water surface.

Abstract: In some embodiments, unmanned aerial task systems are provided that include a plurality of unmanned aerial vehicles (UAV) each comprising: a UAV control circuit; a motor; propulsion system; and a universal coupler configured to interchangeably couple with and decouple from one of multiple different tool systems each having different functions to be put into use while carried by a UAV, wherein a coupling system of the universal coupler is configured to secure a tool system with the UAV and enable a communication connection between a communication bus and the tool system, and wherein the multiple different tool systems comprise at least a package securing tool system configured to retain and enable transport of a package while being delivered, and a sensor tool system configured to sense a condition and communicate sensor data of the sensed condition to the UAV control circuit over the communication bus.

Abstract: The present invention discloses an unmanned aerial vehicle, including: a fuselage; a battery accommodation cavity, disposed on the fuselage; a battery pack, including at least two battery blocks and mounted inside the battery accommodation cavity; a battery circuit board, electrically connected to the battery blocks in the battery pack; and a functional module, electrically connected to the battery circuit board, the battery blocks in the battery pack supplying power to the functional module via the battery circuit board at the same time. By using the solution of the present invention, endurance of the unmanned aerial vehicle is increased.

Abstract: Example implementations may relate to door-enabled loading and release of payloads in an unmanned aerial vehicle (UAV), which could be a type of UAV in a group of UAVs that is assigned to carry out certain transport tasks. In particular, the UAV may include a fuselage having a first side and a second side, as well as a chamber formed within the fuselage and arranged to house a payload. A first door may be arranged on the first side of the fuselage, such that an opening of the first door enables loading of the payload into the chamber. And a second door may be arranged on the second side of the fuselage, such that an opening of the second door enables release of the payload from the chamber. Moreover, the UAV may include a control system configured to control flight of the UAV, and possibly opening and/or closing of door(s).

Abstract: An example system includes an aerial vehicle, a sensor, and a winch system. The winch system includes a tether disposed on a spool, a motor operable to apply a torque to the tether, and a payload coupling apparatus coupled to the tether and configured to mechanically couple to a payload. The system also includes a repositioning apparatus configured to reposition the payload coupling apparatus in at least a horizontal direction. A control system is configured to control the aerial vehicle to deploy the payload coupling apparatus by unwinding the tether from the spool; receive, while the aerial vehicle hovers above the payload and from the sensor, data indicative of a position of the payload coupling apparatus in relation to the payload; and reposition, using the repositioning apparatus and based on the data, the payload coupling apparatus in the horizontal direction to mechanically couple to the payload.

Abstract: A magazine for storing and launching countermeasures arranged in cartridges, comprising a plurality of longitudinal cartridge cases forming the magazine, where each cartridge case comprises side walls and a front opening and a centre axis, where the magazine is adapted to be mounted on an aircraft, where the side walls of two adjacent cartridge cases are arranged to each other in a slidable manner in a longitudinal direction, and where the magazine comprises a tilting means adapted to tilt the cartridge cases, such that the openings of the cartridge cases can be directed in a selected direction. The advantage of the invention is that a countermeasure can be directed in a desired angle before it is launched.

Abstract: A system for monitoring a passenger cabin, in particular a passenger cabin of an aircraft, has a power supply channel (PSC) having a recess and extending longitudinally in a passenger cabin, wherein the recess points in the direction of the passenger cabin, a multiplicity of power supply unit modules (PSU) for arrangement in the recess, a multiplicity of cover modules for partially covering the recess, wherein the multiplicity of power supply unit modules and the multiplicity of cover modules can be arranged in the power supply channel such that the recess is partially covered by the multiplicity of power supply unit modules and the multiplicity of cover modules in the longitudinal orientation of the power supply channel in the direction of the passenger cabin, and at least one camera for capturing images of at least one part of the passenger cabin.

Abstract: In one embodiment, a dual configuration aircraft lavatory includes a plurality of walls enclosing and defining a lavatory interior space, wherein one of the walls is coextensive with a portion of the cabin. Within the lavatory interior space are a toilet, a washing station and a waste receptacle movable between a first position and a second position. In the first position, the waste receptacle is attached to a wall of the lavatory between the washing station and a door wall. In the second position, the waste receptacle occupies a second predetermined volume of space in the aircraft cabin separated from a first predetermined volume of space occupied by the waste receptacle in the first position. Moving the waste receptacle from the first position to the second position reveals additional space within the lavatory sufficient so that two adult humans simultaneously fit within the lavatory interior space.

Abstract: A group of seats for a passenger aircraft, which is configured as a rotating group of seats and by rotating the group of seats about the rotation axis a relocation of the position of the group of seats in relation to the initial position in the aircraft cabin is simultaneously achieved. The group of seats has a seat frame and at least one seat element. A support plate for fastening the group of seats to the aircraft structure is furthermore provided, the support plate having a rotating element which rotatably connects the support plate and the aircraft structure, the rotation axis of the rotating element being positioned in the region of the front half of the seat element, wherein the support plate is capable of being fastened to the aircraft structure by way of quick-release locks.

Abstract: A table apparatus includes a table device and a table support structure that is connected to the table device. The table support structure includes a carrier structure and a table support linkage. The carrier structure is connected to the table support linkage via a single pivot connection. The table device is pivotable about only the single pivot connection.

Abstract: An example method includes: forming a conductive layer on at least a portion of a surface of a substrate, where the substrate comprises a composite material of an aerodynamic structure, and where the conductive layer is configured to provide a conductive path to conduct an electric current generated by a lightning strike to an electrically-grounded location; depositing an insulating layer on the conductive layer; removing one or more portions of the insulating layer to form respective gaps in the insulating layer and expose corresponding one or more portions of the conductive layer; and forming a resistive-heater layer on the insulating layer such that the resistive-heater layer fills the respective gaps in the insulating layer and contacts the corresponding one or more portions of the conductive layer, such that when electric power is provided to the conductive layer, the electric power is communicated to the resistive-heater layer thereby generating heat therefrom.