Abstract: A sub-frame and component configuration for mounting on a motorcycle include a body frame structure including a main frame portion; and a sub-frame portion, he sub-frame is fixedly secured to the main frame portion and is configured for receiving and securing thereon a drop seat providing a rider with a seating area that is relatively closer to the ground than the seating area of a conventional motorcycle seat. A method of mounting the sub-frame on a motorcycle includes: fixedly securing a drop seat sub-frame portion onto a main frame portion, wherein the drop seat sub-frame portion is configured for receiving and securing thereon a drop seat.

Abstract: According to some embodiments, an adjustable assembly for a bicycle comprises a first support and a second support slidably positioned within at least a portion of the first support, such that one of the first support and the second support is adapted to attach to a first bicycle portion and the other of the first support and the second support is adapted to attach to a second bicycle portion. In some embodiments, the second support comprises an expansion portion configured to be selectively moved between an expanded position and a retracted position. In one embodiment, the expansion portion is configured to contact and engage at least one portion of the first support when the expansion portion is in an expanded position, and the first support is configured to be selectively moved relative to the second support when the expansion portion is permitted to assume a retracted position.

Abstract: Provided is a rearview mirror with concealed and light-transmittable turn signal light, which is applicable to a vehicle to provide a function of a rearview with light reflection achieved with a reflector, and in addition, an outer cover of the rearview mirror is structured to allow for emission of light of turn signal therethrough so as to also provide a function of alarming for driving safety. The outer cover is made of a light-transmitting material and the outer cover has a surface that is subjected to sputtering to form a sputtering-coated film thereon. The outer cover receives therein a light casing, which is fixed to a minor base of the review mirror by fasteners. Electrical wires extend along a rearview mirror bracket to connect to the light base. The mirror base and the light casing are coupled to each other.

Abstract: To provide a LED headlight structure that visually conveys a modern or stylish appearance to an observer, the LED headlight structure is characterized in that: a headlight PCB(260) low beam and high beam headlight LED structures on at least one side of the motorcycle are mounted to one plate or in one plane such that high beam illumination is emitted at the inside of the motorcycle and low beam illumination is emitted at the outside of the motorcycle; an extension member (120) is positioned forward of the reflector assembly (140) and between a headlight case (104) and a headlight lens (102); and a window structure (122) configured for selectively passing portions of the low and the high beam illumination reflected by the reflector assembly is formed at the extension member (120).

Abstract: A number of variations may include a product comprising a bicycle with an integrated folding system comprising: a first latch system in a stem of the bicycle; a second latch system in a headset of the bicycle; a third latch system in a frame of the bicycle; and wherein the first latch system, the second latch system, and the third latch system work simultaneously to fold the bicycle to a compact size.

Abstract: A tube for use in a bicycle frame in which the tube has a first end and a second end, and a middle section extending between the ends. The first end, second end, and middle sections each have oval-shaped planar cross-sections. In the cross-sections of the first and second ends, the height is greater than the width. In the cross-section of the middle section, the width is greater than the height. This arrangement allows the middle section of the tube to flex vertically between it is narrower in the vertical direction. Likewise, this arrangement provides a strong connection point at the first and second ends which resists flex and movement vertically because the tube is thicker in the vertical direction.

Abstract: A steering system includes a front fork, a front wheel, a handlebar, two bar ends, and two steering members. The handlebar includes a support bar and two elbows disposed at two opposite ends of the support bar. The two bar ends each includes a grip and a linkage; the linkage fits through the corresponding elbow and connects with the grip. Each of the steering members connects the corresponding bar end to the front fork, so that the swing direction of the grips determines the turning direction of the front fork and thus the travel direction of the front wheel. A bicycle using the steering system is also provided. The steering system and the bicycle of the present invention utilize swinging of the grips of the bar ends connected to the two elbows extending from the handlebar to control the travel direction of the front wheel.

Abstract: An electrical propulsion system for bicycles (E-bike) is claimed. The system comprises an electric motor, at least three speed reduction stages and an output gear (driven gear). The motor has an output shaft oriented towards one side of the system, while the output gear is located on the opposite side of the system. The first and second reduction stage are located on the same side as the drive gear which is mounted on the output shaft of the motor. The sub-claims specify the first reduction stage to be a planetary gear set and specify the location of the third reduction stage. Further is the motor defined as high speed motor and is the system specified as module for mounting to a bicycle bottom bracket.

Abstract: An electric vehicle comprises a driving motor which generates heat during an operation of the driving motor; a driving power transmission mechanism which transmits driving power of the driving motor to a rear wheel (drive wheel); an oil pan (first reservoir section) which is placed below the driving motor and reserves oil (coolant) therein; an oil reservoir (second reservoir section) which is placed above the driving motor and reserves the oil (coolant) therein; a fluid passage which causes the oil pan and the oil reservoir to be in communication with each other; and a pump which supplies the oil (coolant) from the oil pan to the oil reservoir through the fluid passage, and the oil reservoir includes a first drop hole through which the oil (coolant) is dropped toward the driving motor by a gravitational force.

Abstract: A toothed sprocket hub with elastic centering element comprising an input shaft having a receiving portion and a cylindrical outer surface, a sprocket engagable with the input shaft, the sprocket comprising at least two first surfaces each disposed on a bending beam such that each first surface is elastically moveable in a radial direction, the two first surfaces bearing upon the outer surface, the two first surfaces each having a radius d that is less than a radius D of the outer surface, at least one second surface that is radially moveable to a lesser extent than a first surface, the second surface engaging the receiving portion to prevent a relative rotation of the sprocket with the input shaft, and a third surface in cooperative relation to the second surface, the third surface bearing upon the outer surface of the input shaft, the third surface having a clearance fit with the outer surface.

Abstract: A bicycle drive system includes a front sprocket assembly having a first front sprocket and a second front-sprocket. The first front-sprocket has a first front-tooth number that is the largest tooth number in the front sprocket assembly. The second front-sprocket has a second front-tooth number that is less than or equal to the first front-tooth number. The second front-sprocket is adjacent to the first front-sprocket without another sprocket intervening therebetween in an axial direction. The first front-tooth number is less than or equal to 40.

Abstract: The present disclosure relates to devices and methods of converting a bicycle frame from a mechanical gear-shifting configuration to an electronic gear-shifting configuration and vice versa. In a representative embodiment, a method of converting a bicycle frame from a mechanical gear-shifting configuration to an electronic gear-shifting configuration comprises removing a mechanical cable extending between a mechanical gear-shift actuator and a mechanical gear shifter via a cable stop of a removable bracket member secured to a down tube member of the bicycle frame, and removing the removable bracket member from the down tube member of the bicycle frame. The method further comprises mounting an electronically-actuated gear shifter to the bicycle frame in electrical communication with an electronic gear-shift actuator such that actuation of the electronic gear-shift actuator causes the electronically-actuated gear shifter to shift gears.

Abstract: A snowmobile ski tip is configured to be removably fitted over a snowmobile ski and has a bottom surface for contacting the snow and a top surface configured to contact a bottom surface of the ski, a side wall, and a top wall extending from the side wall. The ski tip forms a pocket configured to accept a front end of the snowmobile ski such that the ski tip widens at least the front end of the ski when installed.

Abstract: Mast systems are provided for use with an underwater vehicle. In one example the mast system includes a support base, a mast arm and a mast payload bay. The support base defines a base axis. The mast arm defines a longitudinal axis, and has a free longitudinal mast end and a mast mounting portion longitudinally spaced from the mast end. The mast payload bay is provided at the mast end, and is configured for supporting a payload. The mast arm is mounted to the support base via the mast mounting portion, and the mast arm is selectively deployable with respect to the support base at least between a retracted configuration, in which the mast end is at a first spacing with respect to the mast mounting portion, and an extended configuration, in which the mast end is at a second spacing with respect to the mast mounting portion, the second spacing being greater than the first spacing. The mast system is configured for operating in a marine environment.

Abstract: An anchor device and method for safely and reliably securing watercraft to the bed of a body of water is provided. The anchor device may include a handle member with detachable components and an auger. The auger may be bored into the ground upon rotation of the handle member and then detached from the handle member by lifting the handle member vertically. The auger may include a shaft with a square cross-section and a pointed bottom end. Two auger blades, separated by an axial gap, may be attached to the shaft. Each auger blade may extend circumferentially around the shaft in a helical configuration.

Abstract: A suction anchor for a remotely operated vehicle comprising a frame attachable to a remotely operated vehicle, anchor cans beneath the frame beneath and connectable to a pump. In particular the anchor can be deployed as part of a method for sampling or measuring the seabed comprising the steps of attaching a frame to the remotely operated vehicle, the frame having one or more downwardly mounted anchor cans and a mast to which sampling and/or measuring equipment is attached, placing the anchor cans on an underwater floor, and, at least in partially, evacuating the cans of water embedding them in part into the underwater floor, sampling and/or measuring the underwater floor using the sampling and/or measuring equipment. It can be used to mount other sensor equipment requiring a stable platform.

Abstract: A mooring system comprising: an offshore structure comprising one or more hawsers; a vessel; a first mooring line; and a second mooring line.

Abstract: The present invention relates generally to lighting systems employed in outboard motors used as marine propulsion systems, and to marine vessel assemblies employing outboard motors with such lighting systems, and related methods of operation and implementation. In one example embodiment of a lighting system, the lighting system includes a first cowling panel portion including a reflective strip portion, and a second cowling panel portion that, in combination with the first cowling panel portion, at least partly defines an interior region within the cowling. The lighting system also includes a lighting source that is positioned within the interior region and positioned so that, when operating, first light is emitted toward the reflective strip portion and, upon the first light reaching the reflective strip portion, at least some of the first light is directed outward away from the cowling.

Abstract: An acquisition unit acquires weather and marine data indicating a ship voyage schedule that serves as a reference, actual performance data, fuel consumption data, and weather and marine conditions the ship has encountered during a voyage. A time difference data generation unit calculates the difference between the time indicated by the reference data and the time indicated by the actual performance data for each of the journeys between ports. Projected fuel consumption calculation unit calculates projected fuel consumption for each of the journeys between ports based on the reference data, weather and marine data and fuel consumption data. Fuel consumption difference data generation unit calculates the difference between the projected fuel consumption and the actual fuel consumption amount indicated by the actual performance data for each of the journeys between ports.

Abstract: A supplemental bumper apparatus for covering the bumper of a personal water craft and providing enhanced shock absorption and blemish resistance. The supplemental bumper apparatus comprises a synthetic rubber body and a fastener system. The synthetic rubber body provides a barrier which can absorb shock and block blemishes from an impact. The synthetic rubber body is attached to the bumper fastener system defined by a plurality of snap fasteners on its upper section and a hook and loop fabric fastener is on its lower section. A plurality of snap fastener base members are permanently attached to the bumper and a corresponding hook and loop fastener material is permanently attached to the bumper, each providing a corresponding engaging member to enable the snap fasteners and the hook and loop fastener surface to attach the synthetic rubber body to the surface of the bumper.

Abstract: A system for monitoring a remote underwater location using an unmanned underwater vessel (5). The system includes an unmanned surface vessel (8), a communication unit (7) for submerged location and connected to the unmanned surface vessel (8) and in which the unmanned surface vessel has a position tracking control system for controlling the position of that vessel on a body of water and relative to the unmanned underwater vehicle (5). The communication unit (7) has a first wireless communication arrangement for communication with the unmanned underwater vehicle, a second wired communication arrangement (10) for communication with the unmanned surface vessel and the unmanned surface vessel has a third communication arrangement for communication with an operator or observer (1) remote from the unmanned surface vessel and the unmanned underwater vehicle.

Abstract: A selectively submersible vessel includes a combustor, a Stirling engine thermally coupled with the combustor, an electric generator mechanically coupled with the Stirling engine, a rechargeable battery electrically connected with the electric generator, a compressor electrically coupled with the rechargeable battery, a ballast tank fluidly coupled with the compressor, a snorkel fluidly coupled with the compressor, a controller electrically connected with the rechargeable battery, at least one sensor electrically connected with the controller, a data storage device electrically connected with the controller, and a data communications device electrically connected with the controller.

Abstract: A rigging for a wing propelled craft comprises a mast having a starboard side and a port side, wherein the mast is controllably rotatable in either direction about a longitudinal axis; a flexible sail comprising a star-board flexible sail portion and a substantially identical port flexible sail portion, each flexible sail portion having a luff and a leach, wherein the luff of each sail portion is connected to a respective side of the mast; and a plurality of elongated battens, each of which extends substantially between the luff and the leach of one of the respective sail portions, each of which is in contact with the respective flexible sail portion.

Abstract: An outboard motor includes a cooling water passage structure, in which a combustion chamber periphery water jacket through which the cooling water flows around the combustion chamber and an exhaust port periphery water jacket through which the cooling water flows around the exhaust port are formed in the cylinder head, a cylinder periphery water jacket through which the cooling water flows around the cylinder is formed in the cylinder block, and an exhaust passage periphery water jacket through which the cooling water flows around the exhaust passage is formed around the exhaust passage. The water jackets are connected such that the cooling water from the water passage will flow through the combustion chamber periphery water jacket, the exhaust port periphery water jacket, the cylinder periphery water jacket, and the exhaust passage periphery water jacket in order.

Abstract: A magnetic latching system is provided for removably latching a panel to an aircraft surface portion. The latching system includes a removable axis panel engageable to a latching land. The panel and land define opposing magnetically attractive surface portions, with a body of magnetic material disposed there between. An inflatable seal is also disposed intermediate the panel and the land. Upon inflation, the inflatable seal is operative to urge the panel away from the land far enough to reconnect magnetic engagement between the panel and the land, sufficient to permit disengagement of the panel from the land.

Abstract: An airplane flight deck which includes an escape opening closed off by an emergency door and an emergency hatch. The emergency hatch comprises a sheeting and a locking/unlocking mechanism configured to take up a locked state in which the sheeting closes off the escape opening and an unlocked state in which the sheeting frees the escape opening.

Abstract: The present invention provides a windshield of an aircraft, including a plurality of conductive members that are disposed along an in-plane direction of the windshield, and are wire-connected together, wherein the plurality of conductive members are heaters that generate heat when supplied with an alternating current, and the conductive members are wire-connected such that induced currents induced in the respective conductive members by a magnetic field in association with a lightning current are circulated between the conductive members.

Abstract: An aircraft with a fuselage that defines at least an interior region and a drive system accommodating region, the drive system accommodating region being arranged inside the fuselage and comprising at least one fire protection zone that is defined by at least one associated firewall arrangement, the at least one fire protection zone accommodating at least one engine within the at least one associated firewall arrangement such that the associated firewall arrangement defines a fire-resistant separation between the at least one engine and the interior region of the fuselage, wherein the at least one associated firewall arrangement comprises at least one air duct for ducting a hot air flow that is generated in operation of the aircraft independent from heat generation of the at least one engine.

Abstract: An object of the present invention is to prevent accumulation of moisture which has entered inside a honeycomb sandwich panel used for a stressed-skin structure of an aircraft. A reinforcing structure includes an outer panel constituting an outer shell of a tailplane and a honeycomb sandwich panel reinforcing the outer panel. The honeycomb sandwich panel includes a honeycomb core having a plurality of cells, an outer skin joined on the front side of the honeycomb core and disposed on the side of the outer panel, and an inner skin joined on the back side of the honeycomb core and disposed on the inner side of the tailplane. The inner skin has drainage channels formed therein through which each of the plurality of cells communicates with the outside of the honeycomb sandwich panel.

Abstract: There is provided a drainage system of an aircraft which discharges moisture having entered inside horizontal tails, which are structures of an airframe of an aircraft, toward the rear end of a fuselage, the drainage system including: a drainage channel which includes an introduction end and a discharge end, and by a capillary action delivers moisture introduced from the introduction end toward the discharge end; and a heater which heats and dries the moisture delivered through the drainage channel. The drainage channel of the present invention is preferably composed of a paper drainage material. It is also preferable that the introduction end of the drainage channel is provided in a lowermost region in the vertical direction within an area in which moisture can accumulate inside the horizontal tails while the aircraft is parked.

Abstract: A modular electronic control system is disclosed. The modular electronic control system may have a base control unit to which one or more internal subsystem module and/or external subsystem module may be mounted. Each subsystem module may perform a different function, or may connect with different sensors/effectors, however, each subsystem module has a standardized subsystem module mounting apparatus by which it can mechanically and electrically connect to the base control unit. As such, a standardized base control unit may receive any type of internal subsystem module and/or external subsystem module and intermediate communication and power provision between subsystem module and other aircraft systems, such as an aircraft data network.

Abstract: An aircraft undercarriage comprising a telescopic linear rod (0, 0?, 0?) comprising first and second sliding rod portions. The undercarriage further comprises: a first permanent magnet set (1a, 1a?, 1a?) fastened to the first rod portion (1, 1?, 1?); and a second permanent magnet set (2a, 2a?, 2a?) fastened to the second rod portion (2, 2?, 2?); the first and second permanent magnet sets (1a, 1a?, 1a?, 2a, 2a?, 2a?) generating a magnetic repulsion force between the first rod portion (1, 1?, 1?) and the second rod portion (2, 2?, 2?) and maintaining a first annular space (E1) between the first rod portion and the second rod portion.

Abstract: An aerial vehicle includes a body including a bottom portion, a plurality of rotors coupled to the body for driving the aerial vehicle to fly, and a landing gear coupled to the bottom portion of the body. The landing gear can include a first touchdown bar and a second touchdown bar. The first touchdown bar has a bottom face for contacting a horizontal plane. The second touchdown bar has a bottom face for contacting the horizontal plane. The bottom face of the first touchdown bar and the bottom face of the second touchdown bar cooperatively define a plane. When the aerial vehicle is in flight, the plane is at an angle relative to the horizontal plane. When the aerial vehicle is landing at the horizontal plane, the plane is parallel to the horizontal plane, the body is angled relative to the horizontal plane.

Abstract: Vibration control systems, devices, and methods are provided for a rotary wing aircraft having a rotor including a plurality of blades (20) each attached to a hub (10) at its root end and capable of pitching with respect to the hub (10). The systems, devices, and methods include a blade pitch adjuster (100) that is passively adjustable in response to aerodynamic loading on the plurality of blades (20) to adjust a pitch of one of the plurality of blades (20) with respect to the hub (10) based on a frequency of the aerodynamic loading. The blade pitch adjusters (100) can be configured to exhibit relatively high stiffness at the rotor rotating frequency and tailored dynamics at frequencies higher than the rotor rotating frequency such that hub loads at one or more higher harmonics are reduced.

Abstract: An aircraft has a bearing structure, the bearing structure having at least one central fuselage and two pylons each situated at a distance laterally from the fuselage. In addition, the aircraft has a wing structure, at least four hub rotors, and at least one thrust drive. Each hub rotor is fastened to the bearing structure, has a propeller having two propeller blades, and produces, through rotation of the propeller, an upward drive force acting in the vertical direction on the aircraft. The thrust drive is produces a thrust force acting in the horizontal direction on the bearing structure. The pylons each have two hub rotors, the hub rotors being configured to arrest respective propeller blades of a hub rotor in a position relative to the pylons. In the arrested position, the propeller blades of a hub rotor do not extend beyond the outer dimensions of the pylons.

Abstract: A vertical takeoff and landing aircraft includes an airframe with a wing having an airfoil, the airfoil having an airfoil chord line and the wing having a wingspan. The aircraft further includes at least one forward thrust rotor having a horizontal thrust offset angle defined between the airfoil chord line and an axis of rotation of the forward thrust rotor. The aircraft further includes a plurality of vertical thrust rotors, each of the plurality of vertical thrust rotors having a vertical thrust offset angle defined between the airfoil chord line and a plane of rotation of the vertical thrust rotor. The vertical thrust offset angle is between 3 degrees and 10 degrees. The axis of rotation of the forward thrust rotor and planes of rotation of the plurality of vertical thrust rotors define a plurality of relative thrust angles that are each less than the horizontal thrust offset angle.

Abstract: The system may include a ground station, a tether attached to a ground station on a first end and to two or more bridles on a second, and a kite. The kite may include a main wing. Each bridle of the two or more bridles may be attached to the main wing, and the two or more bridles may be adapted to provide a torque on the kite to control a roll of the kite.

Abstract: An aerial vehicle includes a body including a bottom portion, a plurality of rotors coupled to the body for driving the aerial vehicle to fly, and a landing gear coupled to the bottom portion of the body. The landing gear can include a first touchdown bar and a second touchdown bar. The first touchdown bar has a distal end for contacting a horizontal plane. The second touchdown bar has a distal end for contacting the horizontal plane. The distal end of the first touchdown bar and the distal end of the second touchdown bar cooperatively define a plane. When the aerial vehicle is in flight, the plane is at an angle relative to the horizontal plane. When the aerial vehicle is landing at the horizontal plane, the plane is parallel to the horizontal plane, the body is angled relative to the horizontal plane.

Abstract: An unmanned aerial vehicle (UAV) is disclosed that includes a retractable payload delivery system. The payload delivery system can lower a payload to the ground using an assembly that secures the payload during descent and releases the payload upon reaching the ground. The assembly can also include a bystander communication module for generating cues for bystander perception. While the assembly securing the payload is being lowered from the UAV, the bystander communication module can generate an avoidance cue indicating that bystanders should avoid interference with the assembly. The assembly also includes sensors that generate data used, at least in part, to determine when the descending assembly is at or near the ground, at which point the assembly releases the payload. The bystander communication module can then cease the avoidance cue and the UAV can retract the assembly.

Abstract: A load beam for an aerial vehicle comprises an elongate beam with a radial slot and a lug extending from the radial slot. A hook is pivotably connected to the lug. There is a first arm pivotably connected to the beam and a second arm pivotably connected to the beam. The first arm may be pivotably connected to a first mount and the second arm may be pivotably connected to a second mount. A pivot axis of the first arm relative to the elongate beam may be substantially parallel to a pivot axis of the first arm relative to the first mount. A pivot axis of the second arm relative to the elongate beam may substantially parallel to a pivot axis of the second arm relative to the second mount.

Abstract: In a method for manufacturing a sandwich component having a first and a second flat side, in a pre-assembly state all components of the sandwich component in relation to one another are placed in a nominal position: at least one shape-imparting structural layer and a conductor layer having an electrical conductor, and are connected in an assembly step with an adhesive, wherein in the pre-assembly state on both sides of the conductor layer two barrier layers which are vapour-tight are placed as further components and interconnected in such a manner that said two barrier layers enclose the conductor in a vapour-tight manner.

Abstract: An aircraft storage bin that includes an upper housing, a bucket that cooperates with the upper housing to define a bin interior and is pivotally connected to the upper housing, and at least a first assist spring having a spring force. The bucket is pivotable downwardly between a closed position and an open position and also can be positioned in an intermediate open position between the open and closed positions. The first assist spring is configured to maintain the bucket in the intermediate open position. When a downward force greater than the spring force is placed on the bucket, the bucket is configured to move from the intermediate open position to the open position.

Abstract: The invention concerns a system for managing the comfort equipment of an aircraft cabin, said management system comprising a calculation unit, computers (22) capable of communicating with said calculation unit to manage the comfort equipment, characterised in that it comprises near-field communication tags (32) comprising a memory (42) suitable for containing an identification of the location (ID) of the comfort equipment in the cabin, and in that the computers (22) each comprise an antenna (30) capable of reading said location identification (ID).

Abstract: A lavatory for an aircraft cabin includes a wall having a forward wall portion disposed immediately aft of and substantially conforming to an exterior aft surface of an aircraft cabin structure, such as a passenger seat, that is substantially not flat in a vertical plane. The forward wall portion includes a forward projection over an aft portion of the adjacent passenger seat. The forward wall portion can define a secondary space in the interior lavatory space, which can provide an amenity stowage space, and can include design elements providing visual space.

Abstract: A lavatory for an aircraft cabin includes a wall having a forward wall portion disposed immediately aft of and substantially conforming to an exterior aft surface of an aircraft cabin structure, such as a passenger seat, that is substantially not flat in a vertical plane. The forward wall portion includes a forward projection over an aft portion of the adjacent passenger seat. The forward wall portion can define a secondary space in the interior lavatory space, which can provide an amenity stowage space, and can include design elements providing visual space.

Abstract: An aft rest area assembly is positioned within an aft section of an internal cabin of an aircraft. The aft rest area assembly may include a lavatory section including at least one lavatory, a first galley station positioned on a first outboard side of the lavatory section, and a second galley station positioned on a second outboard side of the lavatory. The first outboard side is opposite from the second outboard side. The first galley station is separated from the second galley station by the lavatory section. The lavatory section may also include an egress flow director that forwardly extends into one or more egress paths of the internal cabin. The egress path(s) connect to at least one emergency exit door.

Abstract: Provided is a moving unit capable of easily mounting and dismounting a movable body to and from track rails. The moving unit includes the pair of track rails, which are laid on a fixed portion at an interval therebetween, and respectively have guiding surfaces on surfaces opposed to each other, a plurality of moving blocks, which are accommodated and arranged in an accommodating space sandwiched between the pair of track rails, and are configured to travel on the guiding surfaces of the respective track rails, and the movable body, which is arranged so as to be opposed to the fixed portion across the accommodating space, and is retained by the moving blocks. The movable body includes a mounting and dismounting mechanism, which is configured to change the interval between the moving block to be assembled to one of the track rails and the moving block to be assembled to another one of the track rails to cancel a contact state between the moving blocks and the respective track rails.

Abstract: A direct current (DC) deicing control system including a direct current (DC) power source, and a periodic deicing waveform generator electrically connected to the DC power source. The periodic deicing waveform generator outputs a switched DC voltage having a periodic electrical current waveform including periods of zero voltage and periods of non-zero voltage. The periods of zero voltage define arc extinguishing events reducing arc formation in the DC deicing control system.

Abstract: A method of an embodiment includes receiving data from a sensor that is configured to supply data related to an ice layer thickness on a skin surface, calculating the ice layer thickness, comparing the ice layer thickness to a threshold thickness, vibrating the skin surface using at least one mechanical element for a sufficient duration, sufficient frequency, and sufficient displacement to result in removal of a first portion of the ice layer thereby resulting in at least a partially deiced skin surface, and heating the partially deiced skin surface using at least one heating element. The method of an embodiment further includes heating from a leading edge of the skin surface to a trailing edge of the skin surface and heating the surface to result in a sufficient temperature increase in the skin surface for removal of a second portion of the ice layer.

Abstract: An aircraft which has a supporting structure which has at least one fuselage, a wing structure and at least one drive apparatus. The drive apparatus has at least one propeller and a drive motor. The aircraft has at least one energy store for providing energy for operation of the drive apparatus. The at least one drive apparatus and the at least one energy store are mechanically connected to the supporting structure and/or the wing structure of the aircraft by a securing device.