Abstract: An aircraft turbine engine has a pair of rotating and non-ducted propellers. An upstream propeller has an outer diameter D1 and a downstream propeller has an outer diameter D2. The engine further includes a system for varying the diameter D2. The downstream propeller includes an annular row of blades, each of which is configured to be mounted telescopically in the radial direction (R) in an outer fan duct.

Abstract: An actuator rod assembly for a blade pitch control system is provided herein. The actuator rod assembly includes a tubular outer rod and an inner rod. The outer rod has a first end and a second end. The inner rod has a first end and a second end and extends through the tubular outer rod. The inner rod is tensioned against the tubular outer rod so as to place the outer rod in compression.

Abstract: A quick release propeller for model airplanes is disclosed including two or more blades mounted to a hub. For each blade, the hub includes a slot and a shoulder. Each blade includes a base portion having pins which slide into the slot in the hub. The slots are curved which prevents the blades from being removed unless they are rotated at predefined threshold angle with respect to the hub.

Abstract: Disclosed herein is a monobloc and removable pedal module for an aircraft rudder bar. The pedal module, which is intended for a rudder bar, includes a pedal, at least one integrated adjustment system, and a connection device which enables a removable connection of the pedal module to be produced. The pedal module is a monobloc component in order to simplify and facilitate its replacement via the removable connection obtained by the connection device.

Abstract: A rudder bar includes a main module provided at least with pedals and with all the elements subject to maintenance, the main module being one-piece and detachable relative to a support frame integrated into the floor of the cockpit of the aircraft, so as to exhibit significant flexibility with respect to its maintainability, particularly in the event of the failure of a component, by allowing quick intervention both on a local level and an overall level.

Abstract: A rudder control unit includes a single-piece main module mobile on a curved support frame. The rudder control unit includes a curved support and guide frame to be mounted in a floor of the aircraft, and a unique main module including the pedals and a set of functionalities, the main module configured such that it is movable and positioned on the support and guide frame using a movement unit, thus making it possible to obtain an extremely simplified architecture with a reduced number of pieces.

Abstract: In one embodiment, a method is performed by a control computer. The method includes receiving a time series of control inputs in relation to a control axis of an aircraft, where the control computer causes actuation in response to each control input in the time series as the control input is received. The method also includes determining aircraft oscillation over a sample period corresponding to the time series. The method also includes evaluating information related to the determined aircraft oscillation using engagement settings associated with a control filter. The method also includes engaging the control filter responsive to the information satisfying the engagement settings, where the engaged control filter systematically attenuates future control inputs in relation to the control axis prior to actuation responsive thereto.

Abstract: The present disclosure provides a slotted entry gimbal including an inner ring with a first side and a second side. The inner ring includes a first pin extending from the first side of the inner ring and a second pin extending from the second side of the inner ring. The slotted entry gimbal also includes an outer ring including a first side and a second side. The outer ring includes a first opening on the first side configured to receive the first pin and a second opening on the second side configured to receive the second pin. The outer ring includes a first slotted entry opening on the first side extending from a first edge of the outer ring to the first opening, and the outer ring includes a second slotted entry opening on the second side extending from a second edge of the outer ring to the second opening.

Abstract: A backup actuation control unit for controlling an actuator dedicated to a given surface. The backup actuation control unit comprises a processing unit operatively connected to one of a flight control computer and a backup flight control computer, to an actuator used for actuating a given surface and to at least one primary actuation control unit, each of the at least one primary actuation control unit for controlling a corresponding actuator used for actuating the given surface, wherein the processing unit receives a surface position command signal from one of the flight control computer and the backup flight control computer and an actuator position signal received from the actuator and provides a corresponding command signal to the actuator if an engagement signal is received from the flight control computer or the backup flight control computer and from the at least one primary actuation control unit.

Abstract: A multirotor aerial vehicle (MAV) is disclosed. The MAV includes a housing, a plurality of rotatable arms, wherein each of the plurality of rotatable arms has a proximal end coupled to the housing and a distal end configured to rotate about a vertical axis passing through the proximal end of the corresponding arm, a plurality of thrust-generating rotors, each coupled to a corresponding one of the plurality of rotatable arms at the corresponding distal end, a flight controller configured to selectively control each of the plurality of thrust-generating rotors, and a flight trim controller configured to control rotation of the plurality of rotatable arms in order to adjust the geometric center of the rotors of the MAV from a first center of gravity (CoG) associated with the MAV in an unloaded state to a second CoG associated with the MAV in a loaded state.

Abstract: Described herein are methods and systems to dampen oscillations of a payload coupled to a tether of a winch system arranged on an unmanned aerial vehicle (UAV). For example, the UAV's control system may dampen the oscillations by causing the UAV to switch to a forward flight mode in which movement of the UAV results in drag on the payload, thereby damping the oscillations. In another example, the control system may cause the UAV to reduce an extent flight stabilization along at least one dimension, thereby resulting in damping of the detected oscillations due to energy dissipation during movement of the UAV along the dimension. In this way, the control system could select and carry out one or more such techniques, and could do so during retraction and/or deployment of the tether.

Abstract: A detection system 100 for detecting the integrity of an uplock system of a landing gear system 10. The detection system 100 includes: an uplock sensor 110 configured to detect whether the uplock is in the unlocked state or the locked state and to issue a first signal indicating whether the uplock is in the unlocked state or the locked state; one or more sensors 120 configured to detect a parameter of the landing gear system and to issue a second signal to indicate the parameter detected; and a controller 130 configured to issue a warning when the controller determines, based on the first signal and the second signal, that the uplock is in the locked state and the parameter detected indicates that the element is not in the first position, the warning indicating a loss of integrity of the uplock.

Abstract: Systems and methods for tuning power transmission circuits may sweep a power frequency applied to a transmission coil across a plurality of frequencies. The transmission coil may be inductively coupled to a receiving coil and separated from the receiving coil by an air gap. A current and/or voltage at the transmission coil may be measured in response to the power frequency being at each frequency of the plurality of frequencies. A transmission frequency may be selected based at least in part on the measured current and/or the measured voltage.

Abstract: An unmanned aerial vehicle (“UAV”) is provided for the lifting and carrying payloads of up to 100 kg. The UAV can include a pair of counter-rotating propellers enclosed in a cage with attitude control motors for providing directional thrust mounted on the top of the cage. One or more motors can rotate the propellers via co-axially concentric vertical output shafts. The motor can include an internal combustion motor or an electric motor.

Abstract: The present invention provides an unmanned aerial vehicle (“UAV”) operations system for cleaning one or more designated surfaces such as a solar panel installed on a roof, or the surface of a window, wall, billboard, scoreboard, etc., which may be too high or too far away from a position on the ground which is easily and safely accessible by a person. For solar panels, such cleaning is not only for aesthetic purposes, but must be performed regularly in order to keep the solar panel functioning at peak performance. The system may also include a ground companion vehicle such as an ATV, golf cart, or the like, which can follow an approximation of the UAV's flight path and provide cleaning media and power to the UAV via a tether, allowing the UAV to clean a large number of surfaces before returning to refill or recharge.

Abstract: An airborne space anti-missile system provides an offensive anti-missile system that provides a supersonic jet flying in space at 10 times the speed of ultra-high speed jet to deliver air-to-surface missiles towards launch site of an attacking missile. The launching missile is targeted prior to launching or during flight. The supersonic jet comprises: a nuclear plasma jet engine operational in thermosphere, and a stamping jet fusion vector engine or anti-material vector engine for flying in lower atmospheres, no vertical tail and rudder, a pointed wing structure; a fuselage having a length of 60 meters and height of 15 meters, a variable swept wing configuration having a 100° range of wing positions, including a forward position where the wing is disposed forwardly, and wingspan is 200 meters from the fuselage, and a full rearward swept position where wingspan is 60 meters from the fuselage; and electromagnetic space for stealth operations.

Abstract: A substrate working system includes a plurality of substrate working apparatuses, a component storage that stores a device and a component to be used by the substrate working apparatuses, and a component conveyance flight vehicle. The component conveyance flight vehicle conveys a conveyance article by flying from the component storage to a predetermined position corresponding to a predetermined substrate working apparatus while holding the conveyance article based on necessary article information of the substrate working apparatuses.

Abstract: A payload retrieval apparatus including a structure having an outwardly facing portion, a payload support member adapted for having a payload positioned thereon, one or more magnets or a metal positioned on or within the outwardly facing portion of the structure adapted to magnetically engage one or more magnets or a metal positioned on a payload retriever attached to a tether suspended from a UAV, wherein when the payload is positioned on the payload support member, the payload support member is movable to position a handle of the payload adjacent the one or more magnets or the metal on or within the outwardly facing portion of the structure.

Abstract: Systems and methods for operating a hoist and hook assembly may determine a position of a target using a position sensor. A hook assembly may be positioned in response to the position of the target as detected by the position sensor. Positioning the hook assembly may include articulating a boom coupled to a hoist, using one or more local thrust sources on the hook assembly, and/or moving an airframe relative to the position of the target.

Abstract: A passenger seat, such as an aircraft passenger seat, includes a seat base and an entertainment system. The seat base includes a cushioning member and a cover covering the cushioning member. The entertainment system is positioned between the cushioning member and the cover and is removably connected to the cushioning member. The entertainment system is configured to determine a force caused by a passenger's legs in at least two locations on an upper surface of the seat base when used.

Abstract: An aircraft lavatory complex incorporating lavatories accessible to passengers of reduced mobility (PRM) is disclosed. Left-side and right-side full service lavatory units are accessible via left-side and right-side lavatory access doors opening in opposing directions. The left-side and right-side full service lavatory units are separated by a common central partition repositionable by cabin crewmembers (but protected from independent repositioning by occupants of either lavatory unit) to enlarge either of the left-side or right-side lavatory units for enhanced PRM accessibility.

Abstract: A modular aft galley and lavatory complex is disclosed. The galley complex is situated aft of an aircraft passenger cabin and incorporates left-side, right-side, and aft galley structures together partially enclosing an interior workspace, the left-side and right-side galley structures separated by a center aisle. Each galley structure includes trolley bays capable of securing trolleys therewithin. Each trolley can be removed from its trolley bay into the interior workspace or central aisle for use in catering or service operations inflight. Each galley structure includes storage bays accessible from the interior workspace. Between the upper and lower portions are flat workdecks and galley insert bays capable of accepting ovens, chillers, beverage makers, and other galley insert devices. Either the left or right galley structure includes a lavatory complex adjacent to the passenger cabin, incorporating aft lavatory units and a galley extension housing additional storage and cart space.

Abstract: A vehicle seat includes a seat with a seat pan and a backrest with a backrest bottom edge articulately being disposed adjacent to a seat pan rear edge. The seat pan and the backrest are positionable with respect to one another such that the seat is configurable into at least one of a taxi, takeoff and landing position, a napping position, and a sleeping position. A swivel is disposed beneath the seat. Base tracking also is disposed beneath the seat, permitting the seat to move in a lateral and a longitudinal direction. The seat also includes a first control to lock and unlock movement of the seat in lateral or longitudinal directions and a second control to lock and unlock the swivel. The swivel may be unlocked while movement of the seat in the lateral and the longitudinal direction is locked.

Abstract: A partition system (and method of forming the same) that is configured to be secured to a seat assembly. The partition system includes a barrier that is configured to be moved between a stowed position and a deployed position. The barrier is moveably coupled to an armrest of the seat assembly. The stowed position is proximate to a rear end of the armrest. The deployed position extends towards a front end of the armrest.

Abstract: An aircraft environmental control system (20) comprises a first heat exchanger (24) configured to exchange heat between air provided by a pressurised air source (13) and a working fluid of a closed cycle refrigeration system, and an air turbine (32) configured to receive cooled air from the first heat exchanger (24). The closed cycle refrigeration system comprises a closed cycle refrigeration system compressor (35) driven by the air turbine (32), a closed cycle refrigeration system expander (36), and a second heat exchanger (33) configured to exchange heat between working fluid of the closed cycle refrigeration system and air downstream of the air turbine (32). The air turbine drives a further load (39).

Abstract: An aircraft environmental control system (20) comprises a first heat exchanger (24) configured to exchange heat between air provided by a pressurised air source (13), and a working fluid of a closed cycle waste heat recovery system, and an air turbine (32) configured to receive cooled air from the first heat exchanger (24). The closed cycle waste heat recovery system comprises a waste heat recovery compressor (35), a waste heat recovery turbine (31), and a second heat exchanger (33) configured to exchange heat between working fluid of the closed cycle waste heat recovery system and air downstream of the air turbine (31). The air turbine is configured to drive a load (39), and the waste heat recovery turbine (31) is configured to drive the waste heat recovery compressor (35).

Abstract: A thermal ice protection system including a spray tube for spraying engine bleed air on an interior surface of an aircraft wing leading edge. The engine bleed air impinges simultaneously at multiple locations on the interior surface heats the aircraft leading edge so as to inhibit the formation of ice on the aircraft leading edge at the predetermined ice susceptible areas. The spray tube is particularly intended to be used to heat a wing slat leading edge skin/surface without using a nose beam or other internal structure to direct the flow of the engine bleed air.

Abstract: A system for mounting a gas turbine engine to a pylon on a wing of an aircraft. A temporary forward link, being length-adjustable, and at least one temporary rearward link, being length-adjustable, are provided. These are for temporarily attaching the gas turbine engine to the pylon. The temporary forward link and the temporary rearward link are each adapted to resist tension and compression, to maintain a positional relationship between the gas turbine engine and the pylon in the absence of adjustment of the lengths of the temporary forward link and the temporary rearward link. Adjustment of the length of the temporary links brings engine mounts into alignment with pylon mounts for service attachment of the gas turbine engine to the pylon.

Abstract: An aircraft has at least one cowling, a fixed structure, and a hinge system connecting the cowling to the fixed structure. The hinge system includes at least two hinges and at least two stops, including a first stop integral with the fixed structure and a second stop integral with the cowling, the first and second stops being configured to be in contact one against the other when the cowling is in the closed position and to ensure an absorption of a part of the loads between the cowling and the fixed structure at least along a direction perpendicular to the pivot axis of the hinge system.

Abstract: A pivoting connection device connecting at least two components and comprising an end fitting having first and second branches, an arm positioned between the first and second branches of the end fitting, a cylindrical axle connecting the end fitting and the arm and having, at one of the ends thereof, a first portion configured to expand radially, a cylindrical rod configured to be screwed into a tapped portion of the cylindrical axle, an insert fitted on the cylindrical rod and movable between a first position, in which the first portion is not expanded, and a second position, in which the first portion is expanded radially, and a nut configured to be screwed on the cylindrical rod to urge the insert into the second position.

Abstract: A variety of refueling devices, systems and methods are disclosed for use in in-flight refueling. In one example one such device is towed by a tanker aircraft via a fuel hose at least during in-flight refueling, and has a boom member with a boom axis. The boom member enables fuel to be transferred from the fuel hose to a receiver aircraft along the boom axis during in-flight refueling. The device maintains a desired non-zero angular disposition between the boom axis and a forward direction at least when the refueling device is towed by the tanker aircraft in the forward direction via the fuel hose.

Abstract: A method of and a system for presenting an operating status of an aircraft engine. The method comprises accessing a first indication indicative of a position of an aircraft engine start switch and accessing a second indication indicative of an aircraft engine start operating mode, the second indication having been generated based on an analysis of a parameter associated with an operating condition of the aircraft engine. The method, upon determining that the position of the aircraft engine start switch is an “on” position and the aircraft engine start operating mode is a healthy start causes the display of a visual indication indicative of the healthy start. The method upon determining that the position of the aircraft engine start switch is an “on” position and the aircraft engine start operating mode is an abnormal start causes the display of a visual indication indicative of the abnormal start.

Abstract: System for reducing likelihood of an aircraft-induced lightning strike on an aircraft. The system includes a plurality of electric field sensors distributed on surfaces of the aircraft to monitor continuously the electrical environment to which the aircraft is subjected. A plurality of ion emission sources are distributed on selected aircraft surfaces, the ion emission sources adapted to emit either positive or negative ions. A computer runs an algorithm to control net charge level of the aircraft by commanding the emission of positive or negative ions from selected surfaces to retard inception of corresponding leader discharges.

Abstract: A multi-mode aircraft navigation light includes a first light source of a first color; a second light source of a second color; and a common optical system, which is arranged over the first light source and the second light source for conditioning light emitted by either one of the first light source and the second light source; and a switching circuit configured to effect power supply to a selected one of the first light source and the second light source depending on a color selection signal.

Abstract: An aircraft light comprises at least one light source; at least one sensor, an operating mode selector, and a transmitter. The sensor is configured for detecting current operational conditions and providing at least one corresponding sensor signal. The operating mode selector configured for determining a suitable light emission of the at least one light source based on the at least one sensor signal. The operating mode selector is further configured for determining the amount of electrical power needed for generating the determined light emission. The transmitter configured for transmitting a power request signal indicating the determined amount of electrical power to a power supply.

Abstract: Locking line capture devices for unmanned aircraft are disclosed. An example line capture device is configured to be attached to a wing of an unmanned aerial vehicle (UAV). The example line capture device includes a body having a line capture slot. The line capture slot has an open end and a closed end. The example line capture device further includes a retainer having a first lobe, a second lobe, and a third lobe. The retainer is movable relative to the body between a first position in which the first and third lobes are positioned on opposite sides of the line capture slot and the second lobe is positioned over the line capture slot, and a second position in which the first and second lobes are positioned over the line capture slot and the third lobe is positioned clear of the line capture slot.

Abstract: The disclosed inventions include personal Unmanned Aerial Vehicles (UAV's) and UAV universal docking ports “docking ports” to be incorporated into and/or attached to headwear, including helmets, hard hats and hats and face masks, as well as footwear including boots and shoes, clothing and outerwear, devices, gear and equipment, land, air, water and space vehicles, buildings, wireless towers and other mobile or stationary objects and surfaces referred to collectively as “docking stations”. A docking station may have one or more docking ports for docking, networking and charging or refueling compact personal UAVs, and for providing data communications between said UAVs and other electronic devices that remain with the person while the UAV is in flight or driving or landed on terrain. Said docking ports may also incorporate wireless power transmission for remote wireless charging of one or more UAV's.

Abstract: A system for mounting a gas turbine engine to a pylon on a wing of an aircraft. At least one temporary forward link, being length-adjustable, and at least one temporary rearward link, being length-adjustable, are provided. These are for temporarily attaching the gas turbine engine to the pylon. The temporary forward link and the temporary rearward link each comprise a respective winch operable to adjust pay out of a respective tension member thereby to provide length adjustment. The temporary forward link and the temporary rearward link maintain a positional relationship between the gas turbine engine and the pylon in the absence of adjustment of the lengths of the temporary forward link and the temporary rearward link. Adjustment of the length of the temporary links brings engine mounts into alignment with pylon mounts for service attachment of the gas turbine engine to the pylon.

Abstract: Cradle assemblies for supporting a door for one of uninstalling and installing the door to a fuselage of an aircraft, and arrangements and methods for the same are provided. In one example, a cradle assembly includes a first contoured board configured to support a first outer section of the door. A second contoured board is spaced apart from the first contoured board and is configured to support a second outer section of the door. The cradle assembly is configured to be positioned proximate to the fuselage.

Abstract: A deployable wrapped rib assembly is disclosed, comprising a hub, a plurality of ribs each being connected to the hub at a fixed angle such that each rib is inclined with respect to a perimeter of the hub, each one of the plurality of ribs being capable of being wrapped around the hub in a stowed configuration and configured to extend from the perimeter of the hub in a deployed configuration, and sheet material connected between the ribs. In a deployed configuration, the sheet material is held taut between the ribs. The ribs may have a lenticular cross-section, and/or may be attached to the hub at an angle with respect to the outer surface of the hub. A method of fabricating the deployable wrapped rib assembly is also disclosed.

Abstract: Systems, methods, and apparatus for advanced cooling for cryogenic powered vehicles are disclosed. In one or more embodiments, a disclosed method for cooling a vehicle comprises routing, by a bypass line, boil-off of a cryogenic fuel of the vehicle past a cold plate to cool a subsystem mounted proximate the cold plate. The method further comprises purging the boil-off in a direction away from the vehicle, after the boil-off passes the cold plate. In one or more embodiments, the cryogenic fuel comprises liquid hydrogen (LH2), liquid oxygen (LO2), and/or liquid methane (LCH4). In at least one embodiment, the boil-off of the cryogenic fuel comprises gaseous hydrogen (GH2), gaseous oxygen (GO2), and/or gaseous methane (GCH4). The vehicle is a space vehicle, an airborne vehicle, a terrestrial vehicle, or a marine vehicle. In at least one embodiment, the vehicle is a fuel cell vehicle (FCV).

Abstract: A cable (130) includes an electrical wire band (134). A parallel electrical wire (133) is formed by arranging a pair of a first electrical wire (131) and a second electrical wire (132) without being twisted together. The electrical wire band is formed by arranging a plurality of parallel electrical wires in a lateral row. In addition, between two adjacent parallel electrical wires, a second electrical wire of one parallel electrical wire is arranged adjacently to a first electrical wire of the other parallel electrical wire. Further, the electrical wire band is wound and accommodated in a spiral spring shape in a cable wrap mechanism (100).

Abstract: A space-debris capturing device includes a harpoon driven into target debris as space debris to be removed. The harpoon includes a first harpoon part having a large diameter, and a second harpoon part having a diameter smaller than the diameter of the first harpoon part and protruding from a leading surface in the direction of the drive of the first harpoon part into the target debris.

Abstract: An object of the invention is to provide a technique in which a decrease in physical properties is suppressed or consumer complaints are diminished. A method for filling a particulate water absorbing agent includes a filling step of filling a particulate water absorbing agent into a filling container and a vibrating step of vibrating the filling container at the outside of the filling container, the vibrating step being conducted at least one time between the start and the end of the filling step, in which a vibration condition in the vibrating step satisfies the following conditions (a) and (b): (a) vibration by a vibrating body in contact with the filling container has a vertical directional component and a vibrational angle is within 90°±30°; and (b) total amplitude at no load and a vibration frequency at no load of the vibrating body are set so as to satisfy Equation 1-1 and Equation 2 or Equation 1-2 and Equation 2.

Abstract: A food article loading system including a shuttle conveyor mounted for reciprocal movement having a first paddle belt for receiving food articles, and upper and lower drives engaging the upper and lower passes of the first paddle belt; a loading head having a second paddle belt for receiving the food articles from the first paddle belt lower pass; a slide gate for receiving groupings of food articles from the loading head; and a control for independently actuating the upper and lower drives to operate at selected speeds, to cause rotation of the first belt and the shuttle conveyor to reciprocate longitudinally to receive and retain a first predetermined number of the food articles, deposit a second predetermined number of the elongate food articles onto the second belt at a selected frequency, and selectively open the slide gate to allow groupings of food articles to fall into receptacles.

Abstract: The present invention refers to a packaging apparatus (1) wherein a conveyor (3) moves one or more supports (4) towards a packaging station, while a plastic film to be applied to said one or more supports is simultaneously transported to the packaging station itself. A longitudinally cutting unit longitudinally cuts the plastic film in order to form two or more film strips, and a compensating device exerts a tensioning action on one or more portions of said film strips. It is also described a packaging method wherein it is provided to longitudinally cut the plastic film into strips and a compensating step destined to suitably tautly hold the film strips during their movement.

Abstract: A method of loading articles in cartons. The method can comprise moving a carton in a generally flat configuration in a downstream direction with a carton opening carousel, at least partially opening the carton while moving the carton with the carton opening carousel, and transferring the carton from the carton opening carousel to a carton loading carousel in a transfer region. The transferring the carton can comprise moving the carton in an upstream direction. The method further can comprise loading a plurality of articles into the carton while moving the carton in a downstream direction with the carton loading carousel.

Abstract: A packaging system for the selection, grouping and loading of varying size and/or configuration product packs into cartons as provided. The packaging system includes a selection area having a primary selector for forming an initial product pack configuration, and a secondary selector adapted to select and direct an additional grouping of products into a nested arrangement against the initial product pack so as to form a nested product pack. The nested product packs thereafter can be engaged by loader arms of a pair of opposed loading assemblies, which move the nested product packs into a series of cartons moving through the packaging machine. Thereafter, the ends of the cartons can be closed and sealed to complete the packaging of the product packs therein.

Abstract: In embodiments of the invention, a tamper-evident bag includes multiple side walls, a closed bottom, and an opening defined by a top edge of the multiple side walls. A handle feature is disposed on two side walls. A pressure-sensitive adhesive strip is disposed proximate to the top edge of a first side wall. A perforation line of uniform height is disposed in the multiple side walls above the handle feature and below the pressure-sensitive adhesive strip. Methods for using and manufacturing a reusable tamper-evident bag are also disclosed.

Abstract: A compartmentalized container loading and management system for loading compartmentalized containers, such as blister cards. A single system may be utilized to hand-load many different types of blister cards having different numbers of wells arranged in different patterns. Systems of the types described herein may include a docking station, a container locator, and a controller. The docking station may include visible information locations which provide visible information proximate wells of a docked blister card to indicate the well which should be loaded. The visible information locations may be changed to match the number, arrangement and pattern of the wells. A container locator may locate the blister card with wells at known positions of the docking station so that visible information may be associated with each well. A controller may control the visible information locations to provide visible information matching the pattern of the wells of each blister card.