Abstract: The present invention relates to an aircraft (100) comprising: a fuselage (101) comprising a plurality of panels (105) adapted to define an aerodynamic shape for a cockpit or a cargo hold of the aircraft (100); at least one wing (103) structurally connected to the fuselage (101) and adapted to allow flying of said aircraft (100), the wing (103) comprising a plurality of wing surfaces and at least a frame configured to support the wing surfaces; a propulsion system for the aircraft (100), comprising at least one electric motor, and batteries adapted to store electrical energy to supply the electric motor. The batteries comprise first structural batteries which constitute at least one surface (104a, 104b) of the wing surfaces, and further second structural batteries which constitute at least one panel (105) of the panels of the fuselage.

Abstract: A composite structural element comprising a substantially planar main section defining a coordinate system with a first axis extending along a longitudinal axis of the structural element and a second axis extending perpendicular to the longitudinal axis within the planar main section. The structural element contains a basic lay-up of single plies, each comprising a fiber-reinforced composite material with a substantially unidirectional fiber orientation. The lay-up comprises N plies arranged from top to bottom in the following form: [[?, ?]M; [?]K; [?, ?]M], wherein ?, ? and ? represent one ply having an angle enclosed between the first axis and the unidirectional fiber orientation of the one ply, respectively, [x]y means y plies each having angle x; [x, y]z means z pairs of plies, K and M are both positive integers equal to or greater than 1: N=4·M+K.

Abstract: Methods and apparatuses may include a stiffened beam assembly including a structural beam portion having a web and upper and lower flanges, and at least one continuous stiffening member extending back and forth between the upper and lower flanges on one side of the web, forming one or more trusses or other reinforcing structures. The beam portion and/or the stiffening member(s) may comprise formed sheet metal. The stiffening member(s) may be mechanically attached to the beam portion.

Abstract: A manually detachable locking mechanism for connecting parts of an unmanned aerial vehicle (UAV) having a first engaging means associated with a first part of the UAV; a second engaging means associated with a second part of the UAV, the first engaging means and the second engaging means being manually and releasably engageable to connect the first and second parts; a resilient means operatively arranged between the first engaging means and the second engaging means. The first engaging means is movable relative to the second engaging means along a direction of an axis from a first position to a second position and then from the second position to a third position angularly spaced from the second position about the axis to thereby lock the first engaging means with the second engaging means under a restoring force exerted by the resilient means. An unmanned vehicle having a manually detachable locking mechanism is described.

Abstract: In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, a phase adapter fulcrum, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the plurality of actuators and the swashplate, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the plurality of actuators and the plurality of lower pitch links, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.

Abstract: A propeller system including a propeller including a central attachment member and a plurality of blade apparatuses, each including a blade body attached to the central attachment member and a magnetic coupling member attached to a radially outward end of the blade body. The propeller system further comprises a propeller frame configured to at least partially circumscribe the magnetic coupling member of each blade apparatus and a plurality of electromagnets positioned on the propeller frame and operable to generate magnetic fields to suspend the magnetic coupling members, laterally translate the magnetic coupling members, rotate the magnetic coupling members along the radial axis of the propeller system, thereby rotating the blade bodies.

Abstract: A cyclic stick for transmitting control commands to blades of a rotorcraft via at least one transmission member, including a grip configured for engagement with a pilot's hand, a control arm and at least one locking mechanism. The control arm has a bottom end configured for connection to the transmission member(s) and for rotational connection to a base support structure, and a top end pivotally connected to the grip. The control arm includes first and second arm portions pivotally connected to each other, the first arm portion defining the bottom end, the second arm portion defining the top end. The locking mechanism(s) selectively prevent a relative pivoting motion between the first and second arm portions and a relative pivoting motion between the second arm portion and the grip. A method of adjusting a position of a grip of a cyclic stick in a rotorcraft cabin is also discussed.

Abstract: A method and system for actuating an aircraft component is disclosed including an actuating material in which an actual deformation change undergone by the actuating material in response to an activation input signal is determined by analysis of an output signal generated by the actuating material in response to the actual deformation. At least a portion of the aircraft component includes an actuating material which undergoes deformation in response to the application of an electrical signal thereto, and which generates an electrical signal in response to a deformation of the actuating material.

Abstract: Methods and apparatus for controlling landing gear retract braking are described. A controller determines wheel speed data corresponding to a speed of a wheel of a landing gear. The controller determines wheel deceleration data corresponding to a rate of change of the wheel speed data. The controller generates a first control signal in response to the wheel deceleration data being greater than a wheel deceleration threshold. The first control signal initiates a wheel deceleration regulation process, the wheel deceleration regulation process to cycle an antiskid valve between a first valve position to release brake pressure from the wheel and a second valve position to cease releasing the brake pressure from the wheel. The controller generates a second control signal in response to the wheel speed data being less than a wheel speed threshold. The second control signal terminates the wheel deceleration regulation process.

Abstract: A system for moving an aircraft door from an open position towards a closed position. The system includes an aircraft door actuator, an input receiving primary power from a primary power supply to power movement of the aircraft door from the open position towards the closed position, a secondary power supply to power the aircraft door actuator to move the aircraft door from the open position towards the closed position, and a controller configured to cause the secondary power supply to power the aircraft door actuator to cause the aircraft door actuator to move the aircraft door from the open position towards the closed position, on the basis of a determination that insufficient primary power is available from the primary power supply via the input to move the aircraft door from the open position towards the closed position.

Abstract: A drive system 20, 20? for rotating a wheel 11, 11? of an aircraft landing gear 10, 10?, is disclosed having a drive element 24, 24?, a motor 21, 21? operable to rotate the drive element, and a driven gear 25, 25? adapted to be attached to the wheel. The drive system has a drive configuration in which the drive element is capable of meshing with the driven gear to drive the driven gear, wherein the drive system further comprises a transmission error measurement apparatus 30, 40, the apparatus configured to obtain, over time, measurement data of one or more characteristics of the drive system when in the drive configuration, the measurement data providing an indication of a transmission error between a torque commanded by the motor and a resulting torque at the driven gear. An aircraft 100 and a method of providing an indication of a transmission error in a drive system is disclosed.

Abstract: The invention provides a drive system for rotating a wheel of an aircraft landing gear. The drive system includes a motor operable to rotate a drive pinion, and a driven gear adapted to be mounted to the wheel. The drive system has a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear and a second configuration in which the drive pinion is not capable of meshing with the driven gear. The drive system includes a linear positioning actuator for moving the drive pinion relative to the driven gear. The positioning actuator has a first end and a second end, the first end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the driven gear, and the second end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the drive pinion.

Abstract: A braking system and a method for applying one or more aircraft wheel brakes according to at least one of a plurality of wheel brake control functions are disclosed. The method includes receiving an indication of an aircraft speed from an aircraft speed indicator, controlling a wheel braking operation of the aircraft according to at least a first wheel brake control function if the aircraft speed indicated by the aircraft speed indicator exceeds a speed threshold, and controlling the wheel braking operation of the aircraft according to at least a second wheel brake control function if the aircraft speed does not exceed the speed threshold. Also disclosed is an aircraft including one or more aircraft wheel brakes and the disclosed braking system.

Abstract: Methods and apparatus for controlling landing gear retract braking are described. A controller is to determine an on-ground status of a wheel of a landing gear. The controller is to generate a control signal based on the on-ground status of the wheel. The control signal is to initiate a retract braking process for the wheel. The retract braking process is to decelerate the wheel from a first rate of rotation to a second rate of rotation less than the first rate of rotation.

Abstract: A vibration attenuator for a rotor is rotatable about a mast axis and has a frame configured for rotation about the mast axis relative to the rotor. A first mass is axially translatable in a first direction relative to the frame parallel to a first axis, and a first biasing force urges the first mass toward a first-mass rest position in which the first mass is symmetric about the mast axis. A second mass is axially translatable in a second direction relative to the frame parallel to a second axis, and a second biasing force urges the second mass toward a second-mass rest position in which the second mass is symmetric about the mast axis. A selected first or second mass moves radially outward from the rest position to oppose vibrations in the rotor.

Abstract: An unmanned aircraft capable of vertical takeoff, vertical landing, and/or flight in a hovering orientation is presented; its fixed-wing is positively-swept and of low aspect-ratio with suitable airfoils. The unmanned aircraft includes a thruster comprising two contra-rotating motors and propellers forward of the fixed-wing's leading-edge and a rudderless fin aft of the center-of-mass, all of which lie on the aircraft's plane-of-symmetry. Two elevons provide pitch and roll control. The unmanned aircraft can stand upright on its feet. A control system for aircraft with at least one wing is also presented. The control system includes a mount and attached thruster which lie on the plane-of-symmetry forward of the fixed-wing's leading-edge. A hinge axis approximately perpendicular to the aircraft's horizontal plane passes through the mount. The thruster rotates about the hinge axis for aircraft yaw control.

Abstract: A rotor or propeller may have rotor blades and a passive pitch angle adjustment apparatus. The passive pitch angle adjustment apparatus may include levers, rods, and central rod. Levers may be connected to rotor blades and rotate them around a respective pitch axis. Rods may be connected to levers and mechanically link levers with each other via central point that is located outside rotor plane. Central rod may connect central point with base point that is located in a longitudinal direction of rotor axis. The passive pitch angle adjustment apparatus may enable a cyclic pitch adjustment of the rotor blades and block a collective pitch adjustment of the rotor blades.

Abstract: Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using at least four, and more preferably at least six variable speed tilt rotors. In some embodiments one or more rotors cooperate to generate at least 50% of the lift, and more preferably at least 70% of the lift, during rotorborne flight (e.g., vertical takeoff, hover, etc). At least some of the blades of each of the at least four rotors are not feathered, retracted, or folded during forward flight. At least one of the variable speed tilt rotors is engineered to be optionally powered by multiple motors, and by multiple battery packs or other independently operating electric power sources. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45? diameter) footprint.

Abstract: An aircraft has a vertical takeoff and landing fight mode and a forward flight mode. The aircraft includes an airframe with first and second M-wings having first and second pylons extending therebetween, each M-wing forming a pair of leading apexes with swept forward and swept back portions extending therefrom at a swept angle. A propulsion system includes a plurality of propulsion assemblies each attached to the airframe proximate one of the leading apexes. Each of the propulsion assemblies includes a rotor assembly having a tilting degree of freedom. A flight control system is operable to control the propulsion assemblies including tilting the rotor assemblies to generate variable thrust vectors. In the vertical takeoff and landing fight mode, the aircraft operates responsive to thrust-borne lift from the propulsion system. In the forward flight mode, the aircraft operates responsive to wing-borne lift in a biplane orientation.

Abstract: A wing unit is used in a wing flapping apparatus to perform a swinging motion to thereby generate levitation force. The wing unit includes a nonwoven fabric that forms a wing surface; a frame body overlaid on the nonwoven fabric and extending along the wing surface; and a resin material disposed in a cavity included in the nonwoven fabric to integrate the nonwoven fabric and the frame body with each other. According to this configuration, a light-weight and high-strength wing unit that produces a suppressed wing flapping noise, a wing flapping apparatus including the wing unit, and a method of manufacturing the wing unit are provided.

Abstract: Embodiments of unmanned, rotary wing drones are described herein that include an insect trap for luring and capturing mosquitoes or other insects. The drone can include a set of propulsion units, each having a motor and propeller, and that collectively provide sufficient lift when operating to allow the drone to fly. A flight controller can be used to send and receive information and control a flight of the drone according to a flight plan stored on the drone. The insect trap includes a funnel or other mechanism to allow only for one-way movement of an insect into a container. To lure the insect into the trap, ultraviolet light can be shone on high-surface titanium dioxide powder that is stored within a mesh bag. A battery or other power source can be used to power the various components, and solar panels can be used to charge the battery when the drone has landed.

Abstract: A hybrid aircraft comprises at least three independent electric motors each arranged to drive a respective rotor; and an internal combustion engine arranged to drive at least two rotor, which are preferably horizontally spaced apart. There is also a controller for providing speed control signals to the electric motor driven rotors and a throttle control signal for controlling the throttle of the internal combustion engine, based on a flight control signal.

Abstract: A flying body 1 includes a fixed rotor supporting a first rotor blade to revolve, a movable rotor supporting a second rotor blade to revolve, and a drive unit for changing an angle of a second revolving plane Pr of the second rotor blade relative to a first revolving plane Pf of a first rotor blade by rotating the movable rotor. The drive unit changes operation modes of the flying body among a normal movement mode where the first revolving plane Pf becomes parallel to the second revolving plane Pr, a high-speed flight mode where the second revolving plane Pr is tilted towards the first rotor blade relative to the first revolving plane Pf, and a high-speed running mode where the second revolving plane Pr is tilted more towards the first rotor blade relative to the first revolving plane Pf than in the high-speed flight mode.

Abstract: Methods and systems of utilizing a drone for a package delivery are provided. An example method can include: receiving, by a central server, a request from a customer device, the request comprising one or more ordered items and a delivery destination; determining, by a processor at a central server and based on the request, instructions of a flight mission for a drone at a distribution center; instructing a first control system at a distribution center to place the ordered items into a bag; loading the bag into one of a plurality of cargo bays; providing the instructions of the flight mission to a second control system to control the drone to navigate to the delivery destination; and controlling the drone by the second control system to automatically release the bag with the ordered items from the cargo bay, the cargo bay remaining with the drone.

Abstract: An aerial vehicle for delivering a package includes a package deployment system coupled to the aerial vehicle, a package coupled to the securing point, and a monitoring system couple to one of the aerial vehicle or the package deployment system. The package deployment system includes a spool coupled to the aerial vehicle; a lowering line fixedly coupled to the spool at a first end, the lowering line having a bitter end at a second end, a securing point coupled to the lowering line between the first end and the second end, and the bitter end coupled to the aerial vehicle at a securing device. The package deployment system is configured to deliver the package at a delivery location and the securing device is configured to release the bitter end to deliver the package. A method for delivering a package with an aerial vehicle having the package deployment system.

Abstract: An aerial vehicle for delivering a package. The aerial vehicle having a package deployment system coupled to the aerial vehicle. The package deployment system having a spool coupled to the aerial vehicle, a lowering line fixedly coupled to the spool at a first end, the lowering line having a second end secured to a grasping device, and a cutting device coupled to one of the spool or the lowering line. The aerial vehicle also having a package coupled to the grasping device and a monitoring system couple to one of the aerial vehicle or the package deployment system. The package deployment system is configured to deliver the package at a delivery location. The cutting device is configured to sever the lowering line to deliver the package. A method for delivering a package with an aerial vehicle having the package deployment system.

Abstract: A drone control system in which a drone can move to a position where a purpose can be achieved and performs an action according to the purpose is provided. The drone control system 1 controls a drone 10 capable of performing a predetermined action on a predetermined object, and includes a state data acquiring module 201 that acquires state data indicating a state of the object, a purpose data acquiring module 202 that acquires purpose data which is a purpose of moving the drone, and a detecting module 203 that detects an action point, which is position information at which an action for the purpose is executed, based on the acquired state data and purpose data.

Abstract: A stowage bin assembly is configured to be disposed within an interior cabin of a vehicle. The stowage bin assembly includes a strongback, and a pivot bin moveably coupled to the strongback. The pivot bin is configured to be moved between an open position and a closed position. A bin drive system is configured to move the pivot bin from the open position to the closed position. The bin drive system includes a motor operatively coupled to a bin actuator through a motion link. The motor is configured move the bin actuator via the motion link to push the pivot bin from the open position to the closed position.

Abstract: A seat system for a passenger aircraft. The seat system includes a passenger seat frame having a backrest support assembly and a seat bottom support assembly. A quadrant assembly is connected between the backrest support assembly and the seat bottom support assembly. The quadrant assembly includes a quadrant member including a pivot point adapted to pivot the backrest with respect to the seat bottom support assembly and the quadrant member. The quadrant member is attached to the backrest and adapted to break away in the event of an impact with the backrest. The quadrant assembly may further include a pivot point brake assembly attached to the pivot point and adapted to provide a controlled stop of the backrest in the event of an impact with the backrest. In addition, a seat back tray table may be attached to the back of the passenger seat frame.

Abstract: A fragrance dispensing system for an aircraft that includes a fuselage defining a cabin interior and an environmental control system (ECS). The ECS includes a source of air that moves air between the source of air and the cabin interior along an airflow path, a mixer unit in airflow communication with the source of air and positioned downstream from the source of air in the airflow path, at least a first air duct positioned in the airflow path between the mixer unit and the cabin interior, and a fragrance dispensing unit positioned between the air source and the cabin interior along the airflow path. The fragrance dispensing unit is configured to dispense at least a first fragrance into the airflow path.

Abstract: A secondary power unit for an aircraft comprises a gas turbine engine having at least one drive shaft, a twin-load compressor including first and second load compressors both coupled with the drive shaft, a first ram-air intake in fluid communication with the twin-load compressor, and a flow regulating arrangement coupled with the first and second compressors outputs to individually regulate the generated flow of compressed air. The flow regulating arrangement is also adapted to be fluidly communicated with an Air Cycle Machine of an aircraft, and a control system is adapted to feed the flow of compressed air as bleed air to the Air Cycle Machine of an aircraft, both when the aircraft is on ground and in flight. The secondary power unit is capable of avoiding bleed air extraction from the main engines with the aim of reducing fuel consumption.

Abstract: An aircraft structure, for example a wing, including a skin. The skin has an external surface, on an outer face of the skin. The skin has an internal surface, located opposite the external surface on an inner face of the skin. The aircraft structure includes a laminar flow control system including a compressor. The aircraft structure is so arranged that the exhaust air from the compressor is directed onto the internal surface of the skin of the aircraft structure, for example thus providing hot exhaust air which function as an ice protection system (whether by de-icing or anti-icing). A method of providing ice protection on a surface of an aircraft using exhaust air from a laminar flow control compressor is also described.

Abstract: Implementations of an unmanned aerial vehicle (UAV) provided with detachable motor arms are provided. In this way, the UAV may be conveniently stored and transported, rapidly assembled in the field, and repaired in the event of a crash. Also, the motor arms are configured to separate from the fuselage of the UAV upon crashing into the ground and/or another object. In this way, damage to the motors arms and/or the fuselage of the UAV may be minimized or prevented. An example UAV comprises a fuselage having two motor arms detachably secured thereto, each motor arm is detachably secured to the fuselage by two mechanical connectors (or fuses) and comprises a tube having a rotary wing propulsion system on each end thereof. The mechanical connectors securing each motor arm to the fuselage of the UAV are configured to facilitate the separation of the motor arm from the fuselage during a crash.

Abstract: An inlet barrier filter system for a tiltrotor aircraft comprising a filter duct extending from a filter to a filter outlet, a ram air duct extending from a ram air inlet to an engine where the filter duct connects to the ram air duct at the filter outlet, and a closure member movable between a first position blocking the ram air duct and a second position blocking the filter outlet. In use, the inlet barrier filter system provides for two mutually exclusive air flow paths, one for introducing ram air to the engine while closing off the filter and another air flow path for introducing filtered air to the engine while closing off the ram air duct.

Abstract: A reinforced composite article includes a first ply, a second ply, and a third ply. A first interface material is between the first ply and the second ply. A second interface material is between the second ply and the third ply. A designated pattern of material property variation, geometric structure variation, spatial variation, or combinations thereof is distributed to selected locations identified in the first interface material or distributed between selected locations identified in the first interface material compared to the second interface material. The pattern is sufficient to measurably vary adhesion, toughness, strength, modulus, or combinations thereof. The article allows distribution of a load across the pattern when the first, second, and third plies receive a force from kinetic energy above a separation threshold by partially delaminating the first ply from the second ply, the second ply from the third ply, or both.

Abstract: A power supply and control system of a plurality of electrically controlled actuators on board an aircraft and an actuation system for an aircraft including the electrically controlled actuators and a system for their power supply and their control. The system includes: P electrical power supply units each capable of generating a power signal for powering an actuator, Q control units, each configured for executing at least one servo control algorithm driving a power module of an actuator, and a network communication module connecting each control unit to a computer network for communicating with each actuator.

Abstract: The present disclosure provides methods, systems, and apparatuses for controlling operation of a flight information recorder of an aircraft. A plurality of flight parameters, including a speed parameter, an engine operation parameter, an in-air parameter, and a descent parameter of the aircraft are monitored. When a shutdown condition associated with the flight parameters is satisfied, power to the flight information recorder is removed via an electrical system of the aircraft.

Abstract: A method and device for inspecting the structural damage on the skin of an aircraft after a lightning strike, the skin has marks derived from the lightning strike, wherein the marks represent a Visual Damage (VD) and a Structural Damage (SD). The method includes for every mark: measuring the area of paint that has been removed by the lightning strike, and comparing the measured area with an area threshold value, wherein the threshold value is related to the Structural Damage (SD) of every mark.

Abstract: A method for dynamic control of runway illumination on aircraft, suitable for controlling the illumination of a light equipment comprising a LED matrix and refraction optics during a flight phase. The method comprises the steps of a) determining predefined flight dynamic movement equations for the flight phase, b) obtaining real data from autonomous sensors independent from the aircraft sensors, c) using extended Kalman Filter and algorithm taking into account the data from the autonomous sensors to obtain the aircraft dynamics data. This step c) comprises the c1) predict phase and c2) update phase, and d) applying the obtained aircraft dynamics data to light control laws affecting the light equipment.

Abstract: An aircraft boarding apparatus has a passenger bridge that has a confinement structure coupled to the second passenger bridge. The confinement structure exerts a ground-anchoring effect on the second passenger bridge to offset the ultralight configuration of the passenger bridge.

Abstract: A system for storing one or more unmanned aerial vehicles is described herein. The system includes one or more shelves attached to a holding structure, the one or more shelves being configured to support one or more unmanned aerial vehicles (UAVs), the one or more shelves defining one or more shelf areas configured to receive the one or more unmanned aerial vehicles. The system also includes an electrical charging station configured to charge electrical batteries of the one or more unmanned aerial vehicles supported by the one or more shelves; and a data transfer and storage system configured to transfer and store data that is previously stored in a data storage device of the one or more unmanned aerial vehicles in a data storage unit.

Abstract: A component manufacturing method includes a step of calculating, for a plurality of keyholes formed on a skin and disposed in a row along a first axial direction on the skin, a first imaginary line that passes an average position in a second axial direction perpendicular to the first axial direction and is parallel to the first axial direction, a step of calculating, for a plurality of keyholes formed on a frame and disposed in a row along a third axial direction on the frame, a second imaginary line that passes an average position in a fourth axial direction perpendicular to the third axial direction and is parallel to the third axial direction, and a step of superimposing the skin and the frame such that the first imaginary line and the second imaginary line coincide.

Abstract: Exemplary deployable sheet material systems may be configured to stow and deploy sheet material. The systems may include one or more masts, one or more extendable booms, and one or more guys wires configured to function in conjunction with each other to deploy the sheet material and then to maintain the sheet material in the deployed configuration.

Abstract: A thruster control device has an opening degree estimating section and an opening degree control section. The opening degree estimating section calculates an estimated opening degree of a valve showing a rate at which the valve is opened, based on a balance of an acting force applied to a valve element of the valve to adjust a quantity of combustion gas to be ejected from a thruster and a fluid force applied to the valve element by the ejected combustion gas. The opening degree control section determines a target opening degree based on the estimated opening degree to control the opening degree of the valve.

Abstract: Disclosed is a spacecraft including: a housing defining an exterior space, the housing having a first face and a second face; and first and second radiators carried by the first and second faces, the first and second radiators each having an inner main face, an outer main face, and side faces. The spacecraft includes a first auxiliary radiator and a first auxiliary heat transfer device thermally connecting the first auxiliary radiator to the inner main face of the second radiator, the first auxiliary radiator being arranged in a first portion of the exterior space defined by the outer main face of the first radiator and by first planes containing the side faces of the first radiator. The first auxiliary heat transfer device includes a heat conducting device. The first auxiliary radiator is composed solely of one or two radiating panels supporting the heat conducting device.

Abstract: The system may be configured to receive a selection of a plurality of timepoints corresponding to an orbital object. The selection of the plurality of timepoints can include sets of identifiers within the selected time period. The system may further be configured to determine an orbital path of the orbital object associated with the selected plurality of timepoints. The orbital path may be determined over an orbital time period that includes a first time period that (i) overlaps the selected time period, (ii) precedes the selected time period, (iii) succeeds the selected time period, or (iv) any combination thereof. The system may generate a display interface that includes a longitude-time graph having a longitude axis spanning from a lower-longitude limit to an upper-longitude limit, a time axis spanning from the lower-time limit to the upper-time limit, and an indication of the orbital path spanning at least the first time period.

Abstract: A filling system includes a conveyance chamber in which a center wheel for conveying vessels is housed inside, a filling chamber where filling machines are housed inside, an inlet/outlet wheel that transfers the vessels from the center wheel to the filling machine, an opening that allows conveyance of the vessels, and a shutter that closes the opening. The inlet/outlet wheel includes grippers configured from a fixed section and a movable section. The movable section can be raised or lowered with respect to the rotational axis of the inlet/outlet wheel. When the shutter closes the opening, movable section is raised or lowered by a predetermined amount relative to the fixed section, after which the movable section is rotated by a predetermined amount to a position where it does not interfere with the shutter.

Abstract: A case forming, packing, and sealing apparatus is disclosed. The case forming, packing, and sealing apparatus includes a cardboard box handling area and a product handling area. In the cardboard box handling area, case forming sheets including flatly collapsed cardboard boxes are erected into boxes that has openings which open in one direction, products are received into the boxes, and thereafter the openings are closed and sealed. In the product handling area, plural products are aligned and a predetermined quantity of the products are pushed in an accumulated state through the openings into the boxes. The cardboard box handling area and the product handling area are interconnected in a state in which they are mutually independently separable.

Abstract: A tape-and-reel system for processing components is disclosed. In the embodiment, the tape-and-reel system includes a first carrier tape reel for holding unloaded carrier tape, a component loading system for loading components into pockets of the unloaded carrier tape, an air-guided cover tape feeder through which cover tape travels, an alignment tool for guiding the cover tape into alignment with the loaded carrier tape and adhering the cover tape to the loaded carrier tape to secure the components into the loaded carrier tape, and a second carrier tape reel for holding the loaded carrier tape.

Abstract: A case sealing device is disclosed. The case sealing device conveys a cardboard box and simultaneously closes a flap group provided on edges of opening of the cardboard box. The case sealing device includes a folding member, a drive unit, and a control unit. The folding member contacts a flap of the flap group that extends along a conveyance direction of the cardboard box and folds the flap. The drive unit moves the folding member. The control unit controls the drive unit. In operation of folding the flap, a longitudinal direction of the folding member is inclined with respect to the conveyance direction such that the folding member contacts a front edge of the flap in the conveyance direction before other portions of the flap.