Abstract: The invention relates to a movable fin assembly, which includes a housing attachable to an underside of a watercraft and a rotation and pivoting mechanism. The mechanism positioned inside the housing and movable about two axes of rotation. The mechanism further has a fin locating position, thereby a fin provided at the fin locating position is capable of moving about the two axes of rotation via the mechanism, such that the fin's toe angle and camber angle changes when moving through the water. The invention further extends to an interchangeable self-aligning fin and static fin kit which includes a rotation and pivoting mechanism and a static member shaped and dimensioned to correspond with an interior of the housing. The static member and the rotation and pivoting mechanism interchangeably receivable by the housing in order to selectively provide a dynamic or static fin on the underside of the watercraft.

Abstract: A system for towing watercraft embodying a towable carrier is provided. The towable carrier is adapted to attach to tow components of a towing vehicle, while sandwiching the towable object between netting an arrangement of strapping and padding. The towable carrier provides netting that spans a framework, wherein the framework attaches to the tow components by way of adjustable strapping, sleeves and clamps pivotably connected to the framework.

Abstract: A buoyant structure having a hull, a main deck, an upper cylindrical side section extending downwardly from the main deck, an upper frustoconical side section, a cylindrical neck, a lower ellipsoidal section that extends from the cylindrical neck, an ellipsoidal keel and a fin-shaped appendage secured to a lower and an outer portion of the exterior of the ellipsoid keel. The upper frustoconical side section located below the upper cylindrical side section and maintained to be above a water line for a transport depth and partially below the water line for an operational depth of the buoyant structure.

Abstract: A safety release mechanism for kite surfing with a safety release member by which a kite surfer is attached to the body. A locking element detachably secures an attachment end of the safety release member to the body. A resilient element urges the locking element into the unlocked position, such that upon release for the locking element, the resilient element moves the locking element to the unlocked position thereby resulting in a release of the attachment end of the safety release member, regardless of the orientation of the device, the orientation of the kite, or the available strength of the kite surfer.

Abstract: A rudder device for a hydrojet vessel. The rudder device includes a mounting plate, a primary rudder and a secondary rudder coupled to a hydrojet. The primary rudder and the secondary rudder providing steerage as the hydrojet vessel is displaced through the water.

Abstract: A paddle assembly includes a paddle with a handle having a fixed blade attached at one end and a grip member attached at the opposite end, a removable blade and attachment unit configured to removably attach the removable blade to the paddle, such that the paddle assembly is able to take on a first, double-paddle configuration when the removable blade is attached to the end of the handle on the grip member side, or a second, single-paddle configuration when the removable blade is attached to the end of the handle on the fixed blade side and against the fixed blade.

Abstract: A device and technique for reducing noise experienced by boat passengers from an outboard boat motor is discussed. The device may be implemented in the form of a cover that is adjacent to at least a portion of the boat motor. The cover includes one or more walls or surfaces that reflect or attenuate soundwaves. The cover may be attached to the boat motor and/or the boat. The cover may be integral with the boat motor and/or the boat. The cover may be attached to the boat via a hinge to permit the cover to be pivoted away from the boat motor. The materials used to construct the cover may be provided in layers that help to attenuate, absorb or reflect soundwaves.

Abstract: A user input assembly for controlling operation of a trolling motor assembly including a propulsion motor, the user input assembly having an input device housing defining a top surface that is configured to receive a user's foot thereon, wherein the top surface defines a left edge and right edge, a support plate, wherein the input device housing is pivotably mounted to the support plate, and a switch that is selectively secured to the input device housing in one of a first position and a second position, wherein the first position is proximate the left edge of the input device housing, the second position is proximate the right edge of the input device housing, and the switch is movable between an open position and closed position so that the power is supplied to the propulsion motor.

Abstract: A ship including a plurality of engines and a plurality of exhaust gas purifiers provided on respective exhaust paths for exhaust gas from the engines. Each exhaust gas purifier includes a casing and an opening. The casing accommodates a purification catalyst for purifying the exhaust gas. The opening serves to place the purification catalyst into or displace the purification catalyst from the casing. The exhaust gas purifiers are arranged so that the respective openings of the exhaust gas purifiers face an identical space, and operation directions of an operation performed through the openings in at least two of the exhaust gas purifiers cross.

Abstract: A vacuum lighter than air vehicle (VLTAV) includes a rigid frame of rods connected together to form a hexakis icosahedron. A membrane skin covers the rigid frame and defines therewith a vessel configured to hold an internal vacuum that allows the vessel to float in the air. The plurality of rods and membrane skin have weights and dimensions that result in a neutral and/or positive buoyancy for the vessel while preventing geometric instability.

Abstract: The present invention relates to a hydrogen recycling flight system and flight method, the hydrogen recycling flight system including: a flight fuselage which has at least one pair of wings at each of both sides of a body; a hydrogen gas balloon which is air-tightly connected to the flight fuselage; a hydrogen fuel cell which is connected with the hydrogen gas balloon and is installed outside or inside the flight fuselage; and a secondary battery which is charged with electricity generated from the hydrogen fuel cell, electricity generated from a solar cell provided at an outer peripheral portion of the flight fuselage, or electricity of an external power network, in which by using a switch, the hydrogen fuel cell is switched to a water electrolysis device or the water electrolysis device is switched to the hydrogen fuel cell, the hydrogen recycling flight system includes: a water tank which stores water generated from the hydrogen fuel cell; the water electrolysis device which electrolyzes the stored water;

Abstract: A pressure bulkhead for an aircraft comprising a pressurized zone, the pressure bulkhead made of a composite material and comprising a front panel intended to be faced towards the pressurized zone; and a rear panel, substantially parallel to the front panel and intended to be located farther from the pressurized zone than the front panel. The pressure bulkhead further comprises a plurality of longerons located between the front panel and the rear panel, each one of them being attached to the front panel and to the rear panel; and a plurality of stiffeners, some of them being attached to the front panel and a remainder of them being attached to the rear panel.

Abstract: A reinforcing arrangement for an opening in an aircraft fuselage structure has a fuselage skin having an inner side, an outer side and a first opening with a first opening contour, and a one-piece reinforcing structure having a thickening section and at least one projecting profile. The first opening contour is surrounded on the inner side of the fuselage skin by an opening edge surface having a thickness corresponding to a thickness of the fuselage skin surrounding the opening edge surface. The thickening section has a bearing surface matched to the opening edge surface and has a receiving section facing away from the bearing surface and surrounding a second opening. The bearing surface is in surface contact with the opening edge surface, and the reinforcing structure is connected to the fuselage skin, with the result that the first opening and the second opening lie one above the other.

Abstract: Various techniques provide a heat shield assembly and mounting thereof on an aircraft. In one example, a heat shield assembly may include flexible member. The heat shield assembly may further include a plurality of frame members disposed on the flexible member. The heat shield assembly may further include a plurality of mounting structures configured to directly mount the heat shield assembly to a strut of an airplane. Each of the plurality of mounting structures may be disposed on one of the plurality of frame members. Related methods are also provided.

Abstract: A wing airframe for a wing of a tiltrotor aircraft includes a wing airframe core assembly and a wing skin assembly disposed on the wing airframe core assembly. The wing skin assembly includes an outer skin and a damping sublayer, the damping sublayer interposed between the outer skin and the wing airframe core assembly. The tiltrotor aircraft includes a pylon assembly subject to aeroelastic movement during forward flight. The wing is subject to deflection in response to the aeroelastic movement of the pylon assembly. The damping sublayer reduces the deflection of the wing, thereby stabilizing the wing during forward flight.

Abstract: Systems and methods include providing an aircraft with a fuselage and a wing assembly rotatable relative to the fuselage about a stow axis between a flight position and a stowed position. The aircraft includes an engine reduction gearbox (“ERGB”) having a retractable driveshaft assembly with an actuation shaft and a first friction plate. Actuation of the retractable driveshaft assembly by the actuation shaft causes the first friction plate to selectively engage and disengage a second friction plate associated with a mid-wing gearbox (“MWGB”) via axially translatable motion of the retractable driveshaft assembly along its rotation axis. When the friction plates are engaged, rotation of the retractable driveshaft assembly imparts rotation to at least one rotor assembly. When the friction plates are disengaged, the wing assembly is capable of selectively rotation with respect to the fuselage about the stow axis between the flight position and the stowed position.

Abstract: A propeller includes a blade free to rotate. A first stop is positioned to mechanically engage one or both of a first portion of the blade and a first structure coupled to the blade when the blade is in a first position at a first end of the rotational range of motion. A second stop is positioned to mechanically engage one or both of a second portion of the blade and a second structure coupled to the blade when the blade is in a second position at a second end of the defined rotational range. The blade rotates to the first position against the first stop when the propeller is rotated in a first direction and to the second position against the second stop when the propeller is rotated in a second direction.

Abstract: In an embodiment, a rotorcraft includes: a rotor system; a sensor; a flight control device; and a flight control computer (FCC) coupled to the rotor system, the sensor, and the flight control device, the FCC configured to: determine a rotation speed of the rotor system; select a first aeroservoelasticity filter configuration from a plurality of aeroservoelasticity filter configurations according to the rotation speed of the rotor system, the aeroservoelasticity filter configurations being predetermined configurations corresponding to different rotation speeds of the rotor system; receive a signal from the sensor; filter the signal according to the first aeroservoelasticity filter configuration; and adjust the flight control device according to the filtered signal.

Abstract: A fly-by-wire system includes an electromechanical actuator which includes a plurality of electromechanical motors. Each of the plurality of electromechanical motors is configured and operable to exchange operating status information with the other redundant electromechanical motors within the actuator. Also, each one of the plurality of electromechanical actuators is configured and operable to automatically configure itself for optimal mode of operation based on the received operating status information of at least one of the other electromechanical motors. The fly-by-wire system further includes a flight control computer operatively connected to the plurality of electromechanical motors within the actuator.

Abstract: An electronic braking arrangement includes a brake stack assembly, a driver circuit, a current limiter circuit, and a voltage limiter circuit. The driver circuit is operably connected to the brake stack assembly. The current limiter circuit and the voltage limiter circuit are connected in series between the driver circuit and the brake stack assembly to drive friction brake loads in the brake stack assembly with a voltage limited constant drive current.

Abstract: An electric compound aircraft is disclosed with a capability of making vertical takeoff and landing and forward flight. In a specific embodiment, the compound aircraft includes an electric motor-powered tip-jet-driven rotary wing, an electric motor-powered tip-jet-driven propeller. The rotary wing provides lift for vertical takeoff and landing, hovering capability and during flight. The propeller provides thrust for forward flight. A fixed wing can be used, in addition to the rotary wing to provide lift for forward flight. Various electric control devices are used to provide control and stability for the compound aircraft and automation.

Abstract: A propulsion unit includes a motor rotor, propeller blades, and a pivot stop. The motor rotor spins about a central rotational axis. The propeller blades, including first and second propeller blades, each having a proximal base mounted to the motor rotor such that the propeller blades are rotatable about the central rotational axis. The second propeller blade is pivotally attached to the motor rotor to pivot about the central rotational axis independent of the motor rotor by a limited angle. The pivot stop mechanically limits an amount of pivoting of the second propeller blade relative to the first propeller blade.

Abstract: An autopilot system includes an actuator arrangement that receives control signals to influence the flight of the helicopter in a selected one of a plurality of different flight modes. A control stick input arrangement allows flight mode selection and control with no more than a particular one of the pilot's hands in the engaged position on the stick and without moving the hand away from the engaged position. A slaved gyro output signal is based on no more than the set of sensor outputs used by the autopilot such that an autopilot display presents autopilot flight mode information while displaying a slaved gyro output. The autopilot provides for pilot selection of one of a subset of the plurality of flight modes which is customized based on a current flight status of the helicopter. An automatic autorotation mode is provided.

Abstract: A tiltrotor aircraft having a VTOL flight mode, a forward flight mode and a storage mode includes a fuselage having a wing rotatably mounted thereto. The wing has an orientation generally perpendicular to the fuselage, in the flight modes, and an orientation generally parallel to the fuselage, in the storage mode. First and second pylon assemblies are positioned proximate outboard ends of the wing. First and second mast assemblies are respectively rotatable relative to the first and second pylon assemblies and have generally vertical orientations, in the VTOL flight mode, and generally horizontal orientations, in the forward flight mode and the storage mode. First and second proprotor assemblies are respectively rotatable relative to the first and second mast assemblies. Each proprotor assembly includes a plurality of rotor blades and has a radially extended orientation, in the flight modes, and a stowed orientation, in the storage mode.

Abstract: A mast lockout system for a tiltrotor aircraft having a proprotor assembly. The system includes a mast coupled to and rotatable with the proprotor assembly. A proprotor gearbox having a proprotor gearbox housing is configured to transmit torque and rotation energy to the mast. A lock assembly has first and second lock members. The first lock member is coupled to the mast between first and second mast bearings and configured to rotate with the mast. The second lock member is coupled to the proprotor gearbox housing. The lock assembly has a first position in which the first and second lock members are disengaged, thereby allowing rotation of the mast. The lock assembly has a second position in which the first and second lock members are engaged, thereby preventing rotation of the mast. The lock assembly is actuatable between the first and second positions.

Abstract: A contoured class divider for dividing an aircraft cabin includes a panel positioned between an aft seat and a forward seat, the panel having a convex contour closely matching an aft-facing contour of a seatback of the forward seat and configured to enhance space utilization. The contoured class divider may include multiple panel portions that are coupled together and articulate relative to one another. The contoured class divider may include an articulation system to articulate the panel portions with respect to one another from a first position (normal operation) to a second position (emergency landing). The contoured class divider may provide up to an additional 12 inches of space which can be used to reduce seat pitch (and thereby enhance passenger comfort) or increase the number of rows of seats on a given aircraft.

Abstract: A trolley compartment for an on-board kitchen intended for installation in a transport vehicle comprises a frontal access aperture as well as a rear wall that lies opposite the access aperture. A worktop forms an upper boundary of the trolley compartment. A first cooling fluid duct, which is connectable to an interior space of the trolley compartment via at least one first cooling fluid aperture, is integrated into or arranged adjacent to the worktop. At least one first removable cooling fluid aperture cover is selectively mountable in the first cooling fluid duct over the first cooling fluid aperture to separate the first cooling fluid duct from the interior space of the trolley compartment, or demountable from the first cooling fluid duct to connect the first cooling fluid duct to the interior space of the trolley compartment via the first cooling fluid aperture.

Abstract: An interior configuration for an aircraft, comprising a bed positioned adjacent to one side of a fuselage on a floor of a cabin within the aircraft; and a movable table positioned in relation to the bed so that the movable table may be positioned over at least a portion of the bed.

Abstract: Described are seating arrangements having at least one aisle column with at least one high bed seating unit and at least one low bed seating unit, and at least one non-aisle column having at least one high bed seating unit and at least one low bed seating unit. The at least one high bed seating unit in the at least one aisle column is positioned laterally proximate the at least one low bed seating unit in the at least one non-aisle column, and the at least one low bed seating unit in the at least one aisle column is positioned laterally proximate the at least one high bed seating unit in the at least one non-aisle column.

Abstract: The invention mainly concerns a headrest, in particular for an aircraft seat, including a central portion and at least one wing positioned at at least one end of the central portion, wherein the headrest includes at least one hinge interposed between the wing and the central portion, the hinge being configured to allow at least two relative movements of the wing relative to the central portion about at least one axis.

Abstract: A pressurization system includes a first compressor that receives a ram air, a fan air, or engine air; a first turbine that is on a common shaft with the first compressor and wherein the first turbine receives an engine air; a main heat exchanger downstream of the first compressor and the first turbine; an internal environment suitable for human occupants and downstream of the main heat exchanger; a second turbine downstream of the internal environment; the second turbine may be on the common shaft with the first compressor and first turbine; or a generator downstream of the second turbine; a motor downstream of the generator; and wherein the motor drives the first compressor.

Abstract: Inadvertent in-flight inflation of an inflatable slide associated with a non-co-located over-wing emergency door of an aircraft fuselage is prevented by a system having a source of compressed gas (e.g., a compress air cylinder) and a 3-way valve having an input port and a pair of output ports each being individually connectable to the input port. The 3-way valve is operable in response to a control signal so as to fluid-connect the source of compressed gas with either a vent line which vents the compress gas overboard or a supply line the inflatable slide. When the control signal fluid connects the gas source to the vent line, the system will be in a safe in-flight mode indicative of inflight operation of the aircraft in which case inadvertent inflation of the slide is prevented.

Abstract: An aircraft propulsion assembly includes: a gas generator coupled by a coupling mechanism to a thrust generator having a structural torque transmission gearbox, and a rigid cradle rigidly supporting the thrust generator in a first suspension plane and the gas generator in distinct second and third suspension planes, the cradle being for securing to a structural element of the aircraft via a vibration-filtering flexible connection.

Abstract: A system and method for reducing a psychoacoustic penalty of acoustic noise emitted by an aircraft, including a plurality of propulsion assemblies coupled to the aircraft, wherein each of the plurality of propulsion assemblies includes a motor, and a plurality of blades defined by a propeller, wherein the plurality of blades can define an asymmetric blade spacing; a control subsystem coupled to the aircraft and communicatively coupled to the motor of each of the plurality of propulsion assemblies, wherein the control subsystem is operable to rotate each of the plurality of propulsion assemblies at a different frequency to modulate the acoustic power distribution of the emitted acoustic signature.

Abstract: Methods and apparatus for cryogenic fuel bayonet transfers are disclosed. A disclosed example fuel transfer system includes a fuel tank. The example fuel transfer system also includes a bayonet receptacle extending into an internal volume of the fuel tank, where the bayonet receptacle is to receive a fuel transfer bayonet to fill the fuel tank with fuel and a fuel discharge bayonet to discharge the fuel.

Abstract: A fuel cell system for an aircraft includes at least one fuel cell having a first inlet for providing a fuel, a second inlet for providing an oxidant, an outlet for removing exhaust air and a voltage outlet, an electrically operable hydraulic pump, which is integratable into a hydraulics network of the aircraft and connectable to the voltage outlet of the at least one fuel cell and a controllable hydraulic energy converter with changeable operating behaviour. The hydraulic energy converter is adapted for generating such a power demand in the hydraulics network, that the at least one fuel cell provides a predetermined volume flow of oxygen depleted air at the outlet through delivering electrical power to the hydraulic pump.

Abstract: A method and a system for anticipating entry of a rotorcraft into a vortex domain, the rotorcraft having a main rotor with blades. After previously determining a specific frequency characterizing the proximity of a vortex domain, measurements are acquired of at least one parameter serving to characterize variation of the flow of air in the environment of the main rotor. Thereafter, the measurements are analyzed in order to isolate frequencies characteristic of the variation of each parameter, and the presence of the specific frequency is detected among the characteristic frequencies. Where appropriate, an alarm can then be issued in order to inform a pilot of the rotorcraft of the proximity of the vortex domain.

Abstract: A case body of a fan case in a jet engine is formed by use of a composite material of carbon fiber reinforced plastic. Metal rings are respectively attached to a leading edge and a trailing edge of the case body. The metal rings are electrically connected together by a conductive cable. Both of the metal rings and the conductive cable constitute a path of a lightning current.

Abstract: Components having fibre-reinforced composite structures are disclosed. The component comprises a plurality of structural fibres embedded in a cured matrix material and a plurality of nanostructures such as carbon nanotubes extending from one or more of the structural fibres. In some embodiments a density of the nanostructures is at least 107 nanostructures per cm2 of surface area of the one or more structural fibres. In some embodiments, the nanostructures extend from an outer fibre proximal to an outer surface of the component but not from an inner fibre distal from the outer surface. In some embodiments the one or more structural fibres from which the nanostructures extend are free of a sizing agent.

Abstract: A lamp unit is attached to an exterior panel of an aircraft and configured by accommodating a light source into a lamp chamber formed by a metallic housing and a cover attached to the housing. The cover includes a cover body having a light transmissive region that transmits light emitted from the light source and a metallic body support that supports an outer peripheral portion of the cover body. A holding cable that electrically and mechanically connects the housing and the body support is arranged in the lamp chamber. A grounding terminal that electrically connects the holding cable to a fuselage side structural member of the aircraft is provided in the housing.

Abstract: An unmanned aerial vehicle (UAV), a stand for launching, landing, testing, refueling and recharging a UAV, and methods for testing, landing and launching the UAV are disclosed. Further, embodiments may include transferring a payload onto or off of the UAV, and loading flight planning and diagnostic maintenance information to the UAV.

Abstract: An aircraft wing assembly including a wing having a main body 5 and a movable portion 6, so that the wing may be folded when taxiing. A lighting system is provided with a light source 9; a light emitter 11 arranged on one of the main body and the movable portion, and a light guide 10 arranged to transmit light from the light source along a path between the main body and the movable portion to the light emitter. The provision of a light guide between the light source and the emitter allows for light to be transmitted to the emitter across the joint 8 between the wing main body and the movable portion. Thus, lighting on the wing may be provided without the need to provide electrical wiring across the joint. A single light source 9 may be employed to illuminate multiple light emitters 11, 13 on the wing.

Abstract: The present invention relates to the field of aircrafts and provides a photographic assembly applied to an aircraft, where the aircraft includes a vehicle body. The photographic assembly includes: a vibration absorption member, a frame provided at the periphery of the vehicle body and connected to the vehicle body through a vibration absorption member, a gimbal connected to the frame and a camera connected to the gimbal. The frame of the photographic assembly in embodiments of the present invention can be mounted on unmanned aerial vehicle bodies of different specifications and the frame is sleeved over the vehicle body, so that the structure of the vehicle body can be designed compactly. The embodiments of the present invention further provide an unmanned aerial vehicle having the photographic assembly.

Abstract: Systems and methods for recovering unmanned aircraft and controlling post-recovery motion of the aircraft are disclosed herein. An aircraft recovery system for handling an unmanned aircraft in accordance with one embodiment of the disclosure includes a base portion and an elongated aircraft capture member having a first end movably coupled to the base portion and a second, free end opposite the first end. The aircraft capture member includes a first portion and a second portion at a distal end of the first portion and positioned to intercept an unmanned aircraft in flight. The first and/or second portions are generally flexible. The system further includes an energy capture and dissipation assembly operably coupled to the aircraft capture member and positioned to receive at least a portion of the landing forces from the aircraft.

Abstract: A chained flashlight system includes multiple flashlights; multiple lighting control devices that control lighting of the flashlights, respectively; a communication wire; and a traffic control device. The lighting control devices include receiving units, controlling units, and power supply units, respectively and are coupled to the traffic control device by the same communication wire. The traffic control device simultaneously sends a lighting signal to the lighting control devices via the communication wire. The receiving units of the lighting control devices receive the lighting signal. The controlling units of the lighting control devices turn ON the power supply units, respectively, on the basis of the time condition from reception of the lighting signal to turning ON of the power supply units, set for the respective flashlights. The flashlights are lit by turning ON the respective power supply units of the lighting control devices.

Abstract: A network is provided for recharging aerial drones during extended flight operations, without requiring a return to a centralized recharging station. Instead, autonomous recharging stations are provided which are self-sustained by using electricity from renewable energy sources located at the station. Operationally, a cone-shaped receptacle is mounted on the drone, and a cone-shaped probe is provided at the recharging station. The probe is connected with the renewable energy source. With this connection, an engagement for recharging the drone's battery is accomplished when the vertex of the probe is received through the open base of the receptacle to place an electrical connector on the probe in contact with the battery of the drone.

Abstract: An object is to simplify a structure of a holding fixture which holds the shape of an aircraft panel, and to hold the aircraft panel in an appropriate shape. A holding fixture includes: a plurality of gripping units configured to grip edge portions on two opposite sides of a fuselage panel including a skin; and a support body configured to integrally support the plurality of gripping units, the support body being provided corresponding to the fuselage panel to be gripped by the plurality of gripping units, wherein the plurality of gripping units hold the fuselage panel such that the gripping units grip the edge portions of the fuselage panel, and the fuselage panel has a curved shape in cross section taken in a direction perpendicular to a one axis direction, and the holding fixture is configured to be conveyable in a state of holding the fuselage panel.

Abstract: A method and system may be provided for determining a set of parameters for preparing a skin for assembly to a substructure. The skin may be nondestructively inspected to gather a data set relating to the skin thickness. Sets of as-built thickness values for the skin and of deviations from a nominal map of the skin thickness may be calculated. A mating area for the skin and substructure and a set of one or more locations for fastener holes in the mating area may be determined. A set of parameters for the one or more fastener holes and a set of one or more fastener lengths may be generated using the deviations. A tool may cut the one or more fastener holes using the set of parameters and the skin and substructure may be fastened using fasteners selected according to the generated set of one or more fastener lengths.

Abstract: A constellation of satellites includes a first plurality of satellites orbiting at a first inclination, wherein the first plurality of satellites are each in a discrete planar orbit to form a first snake of satellites, the first snake of satellites including adjacent satellites in adjacent orbits having adjacent RAAN (Right Ascension of the Ascending Node).

Abstract: A drug packaging unit is disclosed. The drug packaging unit includes a storage portion separately discharging a plurality of units of a drug, a supply portion supplying the drug to a drug packaging member, a detection portion detecting a drug supply error by detecting the drug passing through the supply portion, an adjustment portion adjusting the number of units of drug discharged out of the supply portion, and a driver/controller individually driving the storage portion and the supply portion, thereby putting the drug on standby to be discharged. With this structure, it is possible to reduce a drug packaging time and it is easy to control drug supply.