Abstract: Systems, methods and apparatus are provided through which in some implementations a motorized tricycle includes a lean mechanism and an active system that is operably coupled to the lean mechanism that receives an signal indicative of an interaction with human, that is operable to detect a lean of the body of the human and that is operable to receive a sensed movement on the seat via multisensory devices, and to generate and send a signal to the lean mechanism from the signal, the lean and the sensed movement.

Abstract: In a saddle-type vehicle, an engine is supported by a pivot shaft through insertion of the pivot shaft into a bracket part provided at a rear part of the engine. A center lower cross frame is so provided as to span a space between parts in left and right pivot plates on the lower side relative to the pivot shaft. The pivot shaft and the center lower cross frame are connected by a hanger member.

Abstract: A scooter having a riding platform rotationally engaged to a front steering assembly is provided which significantly increases the ability of riders to perform tricks. The riding platform is rotationally engaged to the steering column which itself may be employed as a riding platform. An optional mechanism may be employed whereby the riding platform is rotated by a spin of the steering column with the handlebars. The scooter may also be equipped with skids to allow employment in the snow or on ice.

Abstract: The present invention relates to a bicycle having a front wheel driving means. The bicycle having the front wheel driving means according to the present invention includes a frame, a front wheel, a rear wheel, a steering part, and a chain part, wherein opposite sides of the front wheel are provided with respective recoilers having respective one-way clutches therein, and the steering part is provided with a driving means for pulling a wire connected to each of the recoilers.

Abstract: A propulsion system for human powered vehicles includes an outer lever having an input end and an output end. An orbiting sprocket is coupled to the output end of the outer lever. A fixed sprocket is also provided, with the orbiting sprocket orbiting around the fixed sprocket. A closed tension-bearing member engages an outer circumference of both the orbiting sprocket and the fixed sprocket. A driveshaft is co-axial with the fixed sprocket, the driveshaft being free to rotate with respect to the fixed sprocket and the crank lever being fixedly connected to the driveshaft and rotationally connected to the orbiting sprocket. A chassis is propelled by the driveshaft. Wherein application of a force on the input end of the outer lever causes the orbiting sprocket to orbit around the fixed sprocket and thereby rotate the crank lever to impart rotation to the driveshaft and propel the chassis.

Abstract: A vehicle is provided which is operable to motor power and/or pedal power, in particular an electric bicycle, which includes a crankshaft drive having a bottom bracket spindle, a chain ring, which outputs a drive torque for the vehicle to a chain, an electric drive, and a cone ring transmission for the continuous variation of a gear step ratio, the cone ring transmission and the electric drive being situated at the crankshaft drive, and the cone ring transmission being connected to the crankshaft drive and set up in such a way that a torque generated by the rider is transmitted to the chain ring.

Abstract: A bicycle sprocket includes a sprocket body and a plurality of sprocket teeth. The sprocket teeth extend radially outwardly from an outer periphery of the sprocket body. The sprocket body includes a first layered member, a second layered member and a third layered member. The first layered member has a first axial surface and a second axial surface. The second layered member is attached to the first axial surface such that the first and second layered members overlap each other in an axial direction as viewed parallel to a rotational axis. The third layered member is attached to the second axial surface such that the first and third layered members overlap each other in the axial direction as viewed parallel to the rotational axis. At least one of the second and third layered members has at least one concavo-convex portion.

Abstract: An electric front derailleur is provided with a base member, a movable member, a driving unit and a controller. The base member includes a bicycle mounting portion. The movable member moves with respect to the base member. The controller selectively operates the driving unit with one of a first mode which moves the movable member between a first end position and a second end position, and a second mode which moves the movable member between a third end position and a fourth end position. The controller operates the driving unit to selectively position the movable member at first, second and third stop positions while in the first mode. At least one of the third and fourth end positions differs from the first and second end positions. A first distance between the first and second stop positions differs from a second distance between the second and third stop positions.

Abstract: A bicycle front derailleur is basically provided with a base member, a movable member, an electric driving unit and a biasing member. The base member includes a bicycle mounting portion. The movable member is movably supported with respect to the base member between a first position and a second position that is farther than the first position from the base member. The electric driving unit is operatively coupled to the movable member to move the movable member between the first position and the second position. The biasing member is operatively disposed between the base member and the movable member to bias the movable member towards the second position.

Abstract: A power unit includes: a rotation plate 62 that is fixed to an end of a shift drum 50, includes a plurality of recessed portions 63, and rotates together with the shift drum 50; a shift lever 66 that engages with the rotation plate 62; a shift shaft 74 fixed to the shift lever 66; a support shaft 76 disposed substantially in parallel with the shift drum 50; a stopper lever 78 rotatably supported by the support shaft 76; and a stopper roller 88 that is provided in the stopper lever 78 and engages with the recessed portion 63 of the rotation plate 62. When viewed in an axial direction of the shift shaft 74, the stopper lever 78 is disposed to intersect a first line segment A that connects a center 74C of the shift shaft 74 and a center 62C of the rotation plate 62 to each other.

Abstract: A marine vessel comprising a command module, first and second buoyant tubular foils, and first and second struts for connecting the first and second buoyant tubular foils to the command module, respectively, wherein the first and second buoyant tubular foils provide substantially all buoyancy required for the marine vessel, and wherein the marine vessel further comprises first and second engines enclosed within the first and second buoyant tubular foils, respectively, and first and second propulsion units connected to the first and second engines, respectively, for moving the marine vessel through water, and means for reducing drag on the vessel as the vessel moves through water.

Abstract: A kit is provided to attach two or more boats together either at shore or while in deep water without exiting either boat so the two watercraft function as one, separated by a constant stable distance. A hammock may be stretched between the two boats with hooks and straps. When the hammock is allowed to extend below the surface of the water, ease of entry into and exit from the water is assured. When the hammock is stretched tightly between the boats, a stable, dry platform is provided for items such as fishing supplies, hunting equipment, coolers, camera equipment, etc. An adjustable or fixed distance may be provided between boats for different uses of the hammock.

Abstract: Provided herein is a Mooring Line Restrainer capable of withstanding the whiplash from the impact of a snapped mooring line, and including a contoured Restraining Member shaped to engage and restrain snapped mooring lines and incorporating a single or multi-turn spring, mounted on a framework attached to one or more support bases. At least one of the support bases is a magnetic holding device adequate for different sizes of mooring lines, for securely and strongly fixing the Mooring Line Restrainers on the deck of a ship at appropriate positions along and on either sides of the mooring lines as per a mooring layout plan. The support bases have provisions for interlinking the plurality of adjacent or alternate Mooring Line Restrainers for forming a strong structure around the mooring lines for confining and restraining any snapped mooring lines within a narrow zone around their pre-snapped positions on the ship's deck.

Abstract: A rotatable boat rail and method of making and using same, the rail including a cylinder defining a passageway and a generally L-shaped member having a horizontal section and a vertical section coupled to the cylinder member such that a proximal end of the L-shaped member extends radially outward from a lower end of the cylinder. The horizontal section of the L-shaped member is arranged essentially perpendicular to the cylinder and the vertical section is arranged essentially parallel to the cylinder. In use, a seat on a boat seat stand is removed from the stand and the stand is inserted through the cylinder passageway so that the cylinder is rotatably supported on the stand and the vertical section of the L-shaped section extends upwardly. The seat is then re-attached to the top of the stand. In use, a person requiring support when exiting or entering the boat, can grasp the L-shaped member and apply pressure against the boat rail for steadying the person.

Abstract: A water propelled flying board has a left and a right thrust nozzle. Each thrust nozzle has a knuckle joint attachment to a pressure water manifold. The thrust nozzles can be independently swiveled forward, backward, sideways or other directions relative to the rider. A left foot and a right foot platform are independently secured to the respective nozzle inlet to allow the rider to go toe up of toe down, they can rotate 360 degrees independently with each foot. This enables trick flying maneuvers including spinning like a top. The knuckle joint can be either a hose segment or a bearing. The left and right foot platforms or center blocks can be locked together and can have a spring return to neutral assembly.

Abstract: The present invention relates to a vessel comprising:-a hull,-a support structure connected to said hull, the support structure configured for supporting the mass, the support structure being constructed to allow the mass to make a back and forth movement relative to said hull along a trajectory between opposite ends of said trajectory,-a damping device configured to dampen the movement of the mass relative to said hull. The present invention also relates to a method for damping the movements of a vessel or of a mass.

Abstract: A watercraft with outboard stabilizing members on a hull with a bow wrap and port and starboard side sheets with one or more longitudinal channels. The port and starboard stabilizing members comprise buoyant members in a sheath having one or more longitudinal keepers that are configured to be received into the side sheet channels. Tension members extend through the keepers, and are attachable near the aft end of the watercraft, and releasably engage tensioning mechanisms in the bow wrap, for releasably attaching the stabilizing members to the side sheet. Deck access plates through the side walls provide access to the tensioning mechanisms, which may be, for example, crank or electric winch mechanism.

Abstract: The present invention utilizes the resilient force (i.e. the force to deform when pressure is added and to return to the original shape when the pressure is removed) of an elastic member or bias member. A large pressure if added in advance to the elastic member or bias member disposed in a preserver body to set the preserver body in a thin and flat state. In an emergency, the resilient force of the elastic member or bias member causes water or air to be sucked into the preserver body. The volume of the preserver body is expanded by the air sucked in due to the resilient force of the elastic member or bias member or by gas generated by a chemical reaction between the sucked-in water and a foaming agent. The increased volume causes the preserver body to float, thereby enabling a wearer to breathe.

Abstract: A jet propelled watercraft includes a prime mover, a jet pump driven by the prime mover and jetting water from a jet port, a reverse gate changing a direction of the jet flow jetted from the jet pump, a shift actuator capable of moving a position of the reverse gate to a plurality of shift positions including a forward drive position, at which the direction of the jet flow is toward the rear of the body, a reverse drive position, at which the direction of the jet flow is toward the front of the body, and an intermediate position in between these positions, and a controller configured or programmed to execute a stoppage shift control of controlling the shift actuator to move the reverse gate to the forward drive position when stoppage of the prime mover is detected.

Abstract: In a boat propulsion device, a head portion of an engine includes plug holes, first attachment portions, and a second attachment portion. The plug holes are aligned vertically and parallel or substantially parallel to a crankshaft. The first attachment portions are arranged on the periphery of the plurality of plug holes. The first attachment portions are configured to attach a plurality of ignition coils which are respectively integrated with spark plugs in a coil-on-plug configuration. A second attachment portion is provided separately from the first attachment portions. The second attachment portion is configured to attach an ignition coil connected to the spark plugs in a double ended ignition coil configuration via cables.

Abstract: A method for setting an engine speed of an internal combustion engine in a marine propulsion device of a marine propulsion system to an engine speed setpoint includes determining the engine speed setpoint based on an operator demand and predicting a position of a throttle valve that is needed to achieve the engine speed setpoint. The method also includes determining a feed forward signal that will move the throttle valve to the predicted position, and after moving the throttle valve to the predicted position, adjusting the engine speed with a feedback controller so as to obtain the engine speed setpoint. An operating state of the marine propulsion system is also determined. Depending on the operating state, the method may include determining limits on an authority of the feedback controller to adjust the engine speed and/or determining whether the operator demand should be modified prior to determining the engine speed setpoint.

Abstract: A method for heating a cargo on a watergoing vessel using an energy source (such as a heat source) on another watergoing vessel. The vessels may be underway. The energy may be transferred to the cargo via energy umbilicals configured to carry energy in a transfer fluid. The transfer fluid may be circulated in a cargo heat exchanger configured to move energy into the hot cargo. The energy source on the another watergoing vessel may be a propulsion motor, exhaust heat, or non-propulsion heat source. The method may include heating the hot cargo. The method may also include switching between heat sources when both vessels are configured to heat the hot cargo.

Abstract: A sandwich structure includes a first skin, a second skin, a first hinge member, and a second hinge member. The first hinge member may be movably coupled to the first skin and a first skin joint. The second hinge member may be movably coupled to the second skin and second skin joint. The first hinge member and the second member may be movably coupled to one another and a member joint located between the first and second skin joint.

Abstract: An aeroplane includes an escape opening passing through an external skin and an internal bulkhead. The escape opening is closed off by an external escape hatch having an external opening controller. The aeroplane further includes an internal escape hatch that closes off said escape opening flush with the internal bulkhead, and kept closed by at least one catch movable between a locked state and unlocked state, a first opening controller that controls the passage from the locked state to the unlocked state of the catch being accessible from inside the aeroplane, and a second opening controller that controls the passage from the locked state to the unlocked state of the catch being positioned such that the actuation of the external opening controller of the external escape hatch or the passage of the external escape hatch from the closed position to the open position causes the second opening controller to be actuated.

Abstract: An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

Abstract: A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box including spars extending along the spanwise direction of the main wing, ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box includes a wing box base section (K10) and a wing box adapter section, that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device. In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib of the wing box base section (K10) up to the outermost rib of the wing box adapter section.

Abstract: The present disclosure pertains to an actuation mechanism for a flap with aileron functionality, including a crank having a crank axle, a crank arm and a crank pivot; a displacement shaft articulated to the crank pivot at an actuating end portion; and a rotatable linear-motion bearing in which the displacement shaft is slidably supported, wherein the displacement shaft is fixedly connectable to a flap body of the aircraft flap at a flap end portion of the displacement shaft opposite to the actuating end portion, and wherein the linear-motion bearing is rotatably attachable at a pivot point to an aircraft wing comprising the aircraft flap, so that the displacement shaft is able to rotate around an axis running spanwise of the aircraft wing around the pivot point. The present disclosure further pertains to an aircraft flap with such an actuation mechanism and an aircraft having an aircraft flap.

Abstract: A system for modifying a shock wave formed in a fluid by a body to modify effects of the shock wave on information transferred to or from the body. The system includes an element for heating fluid along a path to form a volume of heated fluid expanding outwardly from the path, the path extending from the body and through the shock wave; an element for transferring the information to or from the body; and an element for timing the transferring of the information relative to the heating of the fluid along the path to modify certain effects of the shock wave on the information.

Abstract: A landing gear for an aircraft having a main fitting arranged to be coupled to the aircraft and arranged to move between a stowed condition and a deployed condition and a trailing arm movably coupled to the main fitting. A torsion spring is coupled to the trailing arm such that the movement of the trailing arm causes torsion loading of the torsion spring. A stay assembly is provided which comprises the torsion spring, the stay assembly having a first condition in which it is arranged to react axial loading thereof so as to maintain the main fitting in the deployed condition and a second condition in which it is arranged to permit the main fitting to move between the stowed condition and the deployed condition.

Abstract: The present disclosure provides a rotor blade control device for a helicopter. The rotor blade control device may include a swash plate disk with a non-rotating component coupled to the helicopter. At least three actuators may be arranged around a rotor shaft axis of the helicopter, and a coupling element may be located between each actuator and the non-rotating component. The coupling element can be adjusted to change the position of a crosspoint at the non-rotating component of the swash plate disk alongside the rotor shaft axis in order to adjust the rotor blades. The actuators may be arranged onto the non-rotating component and may be able to pivot around a respective swivel axis. A radial distance of the first crosspoint to the rotor shaft axis may change with the swivel movement of an actuator around the swivel axis.

Abstract: An 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. The main rotor blades are connected to a first annular gear that rotates in a first direction and the counter-rotation blades rotate are connected to a second annular gear that rotates in a second direction that is opposite the first direction for anti-torque. Planetary gears simultaneously drive the first and second annular gear at about the same speed.

Abstract: A rotor hub assembly for a helicopter includes a rotor hub operably connectable to a shaft of a helicopter. One or more flex beams extend through the rotor hub, with each end of each flex beam operably connectable to a rotor blade. One or more inner bearings are located at the rotor hub to spherically support the one or more flex beams in the rotor hub. A rotor assembly for a helicopter includes a rotor hub operably connectable to a shaft of a helicopter. One or more flex beams extending through the rotor hub and one or more inner bearings are located at the rotor hub to spherically support the one or more flex beams in the rotor hub. A plurality of rotor blades are operably connected to the ends of the one or more flex beams.

Abstract: An apparatus for controlling a rotor of a rotary wing aircraft, including a stationary frame, a rotary propulsion shaft extending through the frame, the propulsion shaft having a first shaft portion and a second shaft portion coupled to the first shaft portion at a joint, the first shaft portion being configured to be coupled to a drive unit and the second shaft portion being pivotable relative to a centerline of the first shaft portion in two degrees of freedom about the joint, and at least one actuator coupled to the stationary frame at one end and connected to the second shaft portion at the other end so that the second shaft portion rotates relative to the at least one actuator, the at least one actuator being configured to pivot the second shaft portion in the two degrees of freedom.

Abstract: An air filter bank may include a housing configured to be coupled to an exterior of an air vehicle. The housing may have an air intake at a forward end and an air exit at an aft end and defining an air path therebetween. The air filter bank may further include at least one air filter positioned within the housing along the air path. The air filter may be configured to remove pollutants entrained in a volume of air entering the air intake and impinging on the filter surfaces prior to exiting the air exit.

Abstract: Described are methods and apparatuses for synchronizing two or more sensors of an UAV. In the implementations described, a synchronization event is performed such that identifiable signals of the synchronization event can be collected by each sensor of the UAV. The synchronization event may be generated by a synchronization event component that generates multiple output signals (e.g., audio, visual, and physical) at approximately the same time so that different sensors can each collect and store at least one of the output signals. The collected signals are then compared and the sensors are adjusted to align the signals.

Abstract: A method for improving ground movement capability and enhancing stealth in unmanned aerial vehicles is provided. The present method comprises providing, in an unmanned aerial vehicle equipped with wheels, one or more onboard drive means capable of translating torque through the vehicle wheels and controllable to move the unmanned aerial vehicle on the ground without reliance on the unmanned aerial vehicle main motive power source. The onboard drive means is controllably powered by a power source with substantially no acoustic signature to move the unmanned aerial vehicle quietly on the ground with only a minimal audible or visible footprint. This method provides a significant expansion of ground movement capability and expands the potential ground uses of unmanned aerial vehicles, particularly in military applications. The present method can also be applied to move any manned aerial vehicle or aircraft on the ground with only minimal audible or visible footprints.

Abstract: This disclosure generally relates to an automotive drone deployment system that includes at least a vehicle and a deployable drone that is configured to attach and detach from the vehicle. More specifically, the disclosure describes the vehicle and drone remaining in communication with each other to exchange information while the vehicle is being operated in an autonomous driving mode so that the vehicle's performance under the autonomous driving mode is enhanced.

Abstract: A multi-modular aerial firefighting control method and apparatus for use by firefighters to control fire. The multi-modular aerial firefighting control method and apparatus generally includes multi-modular units that are held together to form an aerial firefighting system. The modular units may work together or independently. The multi-modular system comprises more than one modular unit, fluid, fluid conduit, reservoir, air flow generator, multi-modular unit support structure, aerial suspension system and aerial lift system.

Abstract: A method to load stores on an aircraft, the method may be controlled by one or more controller and may include one or more acts of loading stores onto corresponding lift portions; determining a relative position of the aircraft; positioning the stores relative to the determined position of the aircraft; and securing the stores to corresponding hardpoints (HPs) of the aircraft.

Abstract: The present disclosure includes cargo loading systems and components including cargo systems utilizing one or more air cushions to elevate one or more cargo shuttles. The air cushions are formed by one or more air curtains, which include pressure compensating seals. The seals allow the air curtains to contact and seal against a floor panel, reducing leakage from the air cushion.

Abstract: An area on board of a vehicle, in particular of an airplane. The area has a compartment and an opening providing access to the compartment. The area includes a curtain arranged to be drawn in a closed position in which the curtain covers the opening. The curtain includes at least one magnetic curtain element provided along a lower edge of the curtain, and the area includes at least one magnetic opening element positioned along a lower edge of the opening, which at least one magnetic opening element and at least one magnetic curtain element are arranged to attract each other when the curtain is in the closed position.

Abstract: A seat integrating a loudspeaker system includes a seat having a seat body having a horizontally oriented seat bottom and a seat back secured thereto. The loudspeaker system includes a sound assembly mounted within the seat back for selective movement between a storage orientation and a use orientation. The sound assembly includes a first support arm and a second support arm. A retraction control mechanism that moves the first support arm and the second support arm between the storage orientation and the extended use orientation. The system also includes a positioning system in communication with the retraction control mechanism, the positioning system including a user interface in the form of a graphical user interface allowing a user to input his or her position within the seat.

Abstract: An aircraft passenger seat assembly as described herein is formed from two primary and modular components: a structural frame that provides passenger support and dynamic load paths for the seat assembly; and a comfort frame that provides the passenger seating surface and the external upholstery layer for the seat assembly. If the seat assembly is designed for multiple passengers, then a separate comfort frame is used for each passenger seat location. The structural frame can be formed as a molded composite construction, and the comfort frame can also utilize a molded composite support frame. The support frame is used as a mounting shell for a fabric carrier that includes the external upholstery layer. The modular design and use of composite materials results in a significant weight and parts count savings relative to conventional seat designs.

Abstract: An exhaust system for an aircraft galley chiller is provided. The exhaust system includes a galley having a chiller that includes an inlet, a condenser fan inlet, a condenser fan outlet proximate to chiller inlet, and a first flow of air through the condenser, an air ventilation outlet conduit that includes a second flow of air therethrough, and an ejector pump. The ejector pump includes a first airflow inlet, a second airflow inlet and an airflow outlet, wherein the first airflow inlet is coupled in flow communication with the condenser fan outlet, the second inlet is coupled in flow communication with the air ventilation outlet conduit. As the second airflow increases, the first velocity increases in a direction away from the galley chiller facilitating a decrease in temperature at the condenser fan inlet.

Abstract: An aircraft air provision system includes a power turbine that receives bleed air at a first pressure and provides rotational energy to a shaft and outputs output air at an intermediate pressure. The system also includes a compressor coupled to the shaft that receives input air at a second pressure that is lower than the first pressure and outputs compressed air having a pressure equal to the intermediate pressure and a mix chamber coupled to outputs of both the power turbine and the compressor where the output air and the compressed air are mixed. The system also includes a cooling turbine coupled to the shaft and that is in fluid communication with an output of the mix chamber.

Abstract: An aircraft ice protection system (10) comprises an ice protection device (21), an onboard power source (30), a supply line (31) from the power source (30) to the device (21), a controller (41) which controls the line (31), and an optimizer (50) which conveys operation-optimizing instructions (51) to the controller (41). An ice detector (60) provides an input (70) to the optimizer (50) and this ice-condition input (70) is used to generate the operation-optimizing instructions (51).

Abstract: A motor pylon system adapted for use with an airborne power generations system is disclosed. The pylons may support turbine driven generators for wind based electrical power generation which also function as electric motors in some aspects. The pylons may be designed to provide side force useful for turning a tethered flying wing flying in a circular cross wind flight path. The pylons may be designed to minimize air flow disruptions over the main wing.

Abstract: The invention described herein provides a flight crew with an easier and more intuitive way to control and monitor flight-control surfaces. Specifically, the invention displays all flight-control surfaces on a touch-screen display device located in an aircraft cockpit. The invention includes graphical and numerical position indicators to continuously display actual position information for flight-control surfaces. Additionally, the invention allows a flight crew to make flight-control surface adjustments through the touch-screen device. The invention further includes an engine performance indicator and a mode controller configured to display autopilot modes and to receive autopilot mode selections. A method is presented for controlling an aircraft flight-control surface via a touch screen device. The method includes receiving an indication of a flight-control surface and enabling selection of a position change.

Abstract: The drone (10) comprises a camera with a hemispherical-field lens of the fisheye type pointing to a fixed direction (?) with respect to the drone body. A capture area (36) of reduced size is extracted from the image formed by this lens (42), the position of this area being function of the signals delivered by an inertial unit measuring the Euler angles characterizing the attitude of the drone with respect to an absolute terrestrial reference system. The position of this area is dynamically modified in a direction (44) opposite to that of the changes of attitude (38) of the drone detected by the inertial unit. The raw pixel data are then processed to compensate for the geometric distortions introduced by the fisheye lens in the image acquired in the region of the capture area.

Abstract: A helicopter dolly includes a platform defining a helicopter landing area, a plurality of rollers connected to the platform such that a vertical clearance is defined between the platform and the ground and a plurality of safety panels movably connected to edges of the platform so as to be movable relative thereto between raised and lowered positions. The safety panels cover the vertical clearance in the lowered position. A method of using a helicopter dolly includes arranging a helicopter dolly for a helicopter landing, moving a plurality of safety panels and a plurality of corner members to cover a vertical clearance defined between a platform and the ground and moving the plurality of safety panels and the plurality of corner members to uncover the vertical clearance after the helicopter landing.