Abstract: An electric pedal control device for an aircraft, the device comprising several pedal transmission assemblies, each of the pedal transmission assemblies comprising an electric motor, an elastic connector, a transmission mechanism, an angular displacement sensor, and a pedal, wherein the angular displacement sensor is configured to acquire rotational position information about the pedal; transmission mechanism revolute pairs of the transmission mechanisms in the pedal transmission assemblies are connected via a mechanical connecting rod mechanism to effect linkage; and a controller of the electric pedal control device is configured to receive the rotational position information, and to control, according to the rotational position information, the electric motors to dampen the elastic connectors.

Abstract: A method of moving a door of a well for an aircraft undercarriage during sequences of deploying or retracting the undercarriage includes: using a temporary mechanical connection between the door and the undercarriage that is effective when the undercarriage is close to its retracted position, causing the door to be opened by the undercarriage while the undercarriage is being deployed and causing the door to be closed by the undercarriage while the undercarriage is being retracted, but releasing the door from the undercarriage when the undercarriage is close to its deployed position, and using a door actuator acting on the door to close and open the door when the undercarriage is in its deployed position and the temporary mechanical connection is interrupted.

Abstract: An emergency braking method for aircraft, comprising using a progressing parking brake controlled by a lever (10) that can be actuated by the pilot between a “0%” position in which the brakes are connected to the return pressure of the aircraft, and a “100%” position in which the brakes are connected to the feed pressure of the aircraft, the lever being blockable in the 100% position in order to provide parking braking when the aircraft is stationary.

Abstract: An aircraft including: a pair of wings rotatably coupled to opposing lateral sides of the fuselage and being rotatable relative to each other; a pair of servo motors, each connected to a corresponding wing and configured to rotate the corresponding wing in two rotational directions; a pair of thrust motors, each of which mounted on a corresponding wing; and a flight controller connected to the servo motors and to the thrust motors, and configured to control each servo motor and each thrust motor, such that the aircraft can be selectively operated in a cruising mode, such that the pair of wings are in a non-permanent-rotation-state about a yawing axis which extends at least substantially through the center of gravity, and a monocopter mode, in which the pair of thrust motors provide thrust in opposite directions so that the pair of wings are in a permanent-rotation-state about the yawing axis.

Abstract: An aerial vehicle including a housing, an outrunner motor including a stator mechanically coupled to the housing and a rotor rotationally coupled to the stator, and a propeller removably coupled to the rotor, the propeller including a hub and a plurality of propeller blades. A rotor, a propeller including a hub and a propeller blade, a radial alignment mechanism, a rotational retention mechanism, and an axial retention mechanism.

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 example rotating swashplate ring to rotor mast connection includes a polygon-shaped drive tube secured to the rotor mast and a gimbal joint connected between the rotating swashplate ring and the polygon-shaped drive tube, wherein the gimbal joint rotates with the rotor mast and can translate axially along the polygon-shaped drive tube.

Abstract: An actuator for aviation may include an electromechanical drive unit connected with an output drive via a gearbox. The drive unit may have at least two partial drives that can be operated independently from one another. The gearbox may be located at least partially between the at least two partial drives such that the at least two partial drives are spaced apart from one another.

Abstract: Systems and methods include providing a helicopter, with a fuselage, a tail boom extending from the fuselage, a main rotor system, and a tail rotor assembly disposed on an aft end of the tail boom. The tail rotor assembly includes a tail rotor housing, at least one normal ducted fan that generate anti-torque thrust to prevent rotation of the fuselage, and at least one canted ducted fan configured to generate both anti-torque thrust to prevent of the fuselage and lift to the tail boom in order to control the pitch of the helicopter. The canted ducted fans generate sufficient lift to prevent a nose-up orientation of the helicopter when the center of gravity of the helicopter is shifted rearward behind the main rotor system, while the normal ducted fans maintain sufficient anti-torque thrust to prevent rotation of the fuselage when the main rotor is operated.

Abstract: Propulsors, aircraft including the propulsors, and methods of directing a fluid stream in a propulsor. The propulsors include a housing defining a partially enclosed volume that extends from an inlet to both a first thrust outlet and a second thrust outlet. The propulsors also include a fan assembly including a plurality of blades and a blade pitch control mechanism that is configured to selectively vary a respective pitch angle of each blade in the plurality of blades. The fan assembly is configured to provide a motive force for fluid flow into the partially enclosed volume via the inlet. The propulsors further include an outlet flow control assembly configured to direct the fluid flow to preferentially exit the partially enclosed volume via a selected one of the first thrust outlet and the second thrust outlet. The aircraft include the propulsors. The methods include methods of operating the propulsors.

Abstract: Unmanned monitoring devices, such as unmanned aerial vehicles (UAV), drones or rovers may survey an area of interest (AOI) such an electric power distribution system including generation, transmission, and distribution elements to automatically determine components in the AOI to be monitored. Types, placements locations, and pathways taken by other unmanned monitoring devices to facilitate the monitoring of the components of the AOI are also automatically determined.

Abstract: A method of operating an aircraft according to an exemplary embodiment of this disclosure includes, among other possible things, communicating power from a storage device within an unmoved aerial vehicle (UAV) to an aircraft; controlling a propulsive device within the UAV with a control system of the aircraft to provide propulsive thrust to the aircraft; and detaching the UAV including the storage device and the propulsion device from the aircraft responsive to the energy within the storage device being below a predefined threshold.

Abstract: Aspects of the current subject matter relate to enhanced operation services provided by an unmanned vehicle with cloud-based connectivity for real-time exchange of data and command/control operations. Data collected during a mission for an operation service, such as a particular inspection activity, is transmitted in real-time to a server for analysis to provide real-time or near real-time feedback in the form of command and/or control signals to the unmanned vehicle to improve the operation service while it is being carried out. The collected data is also used for simulations and to create historical content for future operation services.

Abstract: A disclosed device allows a person to fly. A disclosed wearable flight system includes a plurality of propulsion assemblies including a left-hand propulsion assembly configured to be worn on a user's left hand and/or forearm and a right-hand propulsion assembly configured to be worn on a user's right hand and/or forearm. A further embodiment includes a body propulsion device that is configured to provide a net force along an axis defining a net body propulsion vector and a support device configured to support a user's waist or torso. The support device is configured to hold a user's body relative to the body propulsion device such that a line extending between center the of the user's head and the center of the user's waist extends, relative to the orientation of the net body propulsion vector during use, by a body propulsion elevation angle that is greater than zero.

Abstract: The aircraft (10) comprises a fuselage (11) and a rhombohedral wing structure (12) comprising front wings (13, 14) mounted on a front wing-root support (17) and rear wings (15, 16) mounted on a rear wing-root support (18). One end of each front wing is articulated to one end of a rear wing and at least one of the wing-root supports is able to move along the fuselage. The wing-root supports (17, 18) are positioned respectively underneath and on top of the fuselage (11). In some embodiments, the length (41) of the rear wings (15, 16) is strictly less than the length (48) of the front wings (13, 14), the angle (42) formed between the main longitudinal axis (44) of the fuselage (11) and the main axis (43) of the rear wings therefore being, in all flight configurations, more obtuse than the angle (46) formed between the main longitudinal axis of the fuselage and the main axis (45) of the front wings.

Abstract: PROBLEM: To provide a chemical spraying drone (unmanned air vehicle) in which minimizes chemical drift outside the field by a simple structure without additional equipment and complicated control. SOLUTION: To provide a chemical spraying drone that actively uses the air flow made by rotors for spraying, comprising chemical spray nozzles and rotors (preferably two-stage rotors), wherein the chemical spray nozzles are positioned under the rotors and under a circular area with its center at a point offset by a predetermined distance rearward with respect to the flying direction from the rotor's rotation axis, its radius 90 percent of the radius of the rotor blade, on a straight line with a depression angle of about 60 degrees rearward from the horizontal line passing through the rotor's rotation axis. The position of the chemical spray nozzles may be dynamically adjusted.

Abstract: A locking pin assembly for a cargo loading system includes a shaft, a first retention pin, a second retention pin, and a synchronizer. The shaft defines a first shaft groove and a second shaft groove. The first retention pin and the second retention pin are disposed within the shaft. The synchronizer is disposed about the shaft and defines a first synchronizer groove that crosses over the first shaft groove and a second synchronizer groove that crosses over the second shaft groove.

Abstract: A system for communicating between passenger seats and an aircraft galley. The system may include a control unit including a display area for interfacing with a crew member. The system may include a plurality of devices, each positioned at a respective passenger seat. The control unit may be adapted to display on the display area data related to a particular order, including a location of an associated passenger seat. The control unit may be further adapted to transmit to a particular device associated with the order notifications concerning a status of the particular order.

Abstract: A heatable leading-edge apparatus for an aircraft having a main structure and a heating layer. The heating layer comprises a fiber composite layer with fibers and with a matrix which surrounds the fibers. The fibers are at least partially formed as conducting fibers, such as carbon fibers, with an electrically insulating coating. Owing to the conducting fibers, which act as electrical heating elements, a desired surface temperature can be established on an outer side of the leading-edge apparatus.

Abstract: Provided is an airbag device for a flying object sufficiently having a performance of protecting a battery. An airbag device 1 is an airbag device for a flying object including an upper cover member 19 and a lower cover member 20 as a housing, and a battery 24 provided inside the housing and includes an expandable member 2 which is provided inside the housing of the flying object 10 and is expandable inside the housing, a gas generator 3 which is connected to the expandable member 2 and receives a predetermined amount of current to make gas flow into the expandable member 2, and a current supply section which supplies current to the gas generator 3 according to collision of the flying object 10.

Abstract: A propulsion system for an aircraft includes at least two gas turbine engines and at least one auxiliary propulsion fan. The at least one auxiliary propulsion fan is configured to selectively receive a motive force from either or both of the at least two gas turbine engines through at least one shaft operatively coupled to the at least one auxiliary propulsion fan.

Abstract: A gas turbine engine comprises a pylon attachment, a shaft defining an engine centreline which lies in an engine central plane intersecting the pylon attachment, a fan defining a fan plane normal to the engine centreline and an intake upstream of the fan plane. The geometric centreline of the intake coincides with the engine centreline at an axial position corresponding to the downstream end of the intake and curves away from the engine centreline upstream of said axial position. The engine may be mounted on one side of an aircraft such that the orientation of the highlight plane of the intake is aligned to the air flow field of the aircraft on that side during flight.

Abstract: A propulsion system for an aircraft includes at least one gas turbine engine, an electric auxiliary fan driving motor configured to selectively receive electric power input from one or more electric power sources, and at least one auxiliary propulsion fan configured to selectively receive a motive force from either or both of the at least one gas turbine engine and the electric auxiliary fan driving motor. The propulsion system also includes a controller configured to establish a plurality of takeoff thrust settings of the at least one gas turbine engine and the electric auxiliary fan driving motor such that a minimum total aircraft thrust required for takeoff of the aircraft is produced.

Abstract: A method for limiting torque on a rotorcraft. The rotorcraft comprises an installation having a rotor, the installation including at least three motors driving a power transmission gearbox, the MGB including a rotor mast for moving the rotor. The method comprises a step of determining a engine torque limit for each of at least the three motors, each engine torque limit being established by a control computer of the aircraft by taking into consideration the distribution among the at least three motors of the total power (Ptot) delivered by the at least three motors for enabling the rotorcraft to operate.

Abstract: An example system includes a fuel tank, fittings mounted through a wall of the fuel tank, and optical sensors positioned within the fittings. A respective optical sensor includes a first pressure sensing end inserted through a fitting and internally into the fuel tank and a second end extending externally from the fuel tank. The system also includes an optical fiber bundle mounted external to the fuel tank, and having an optical fiber connected to each of the plurality of optical sensors for guiding light to each of the plurality of optical sensors.

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 damaged portion determination device includes: a damage identification unit that identifies a damaged portion of an airframe of an aircraft; a position identification unit that identifies a reference position inside the airframe of the aircraft; and a damaged portion presentation unit that superimposes and presents an imaging result resulting from imaging of a state inside the airframe of the aircraft at the reference position by an imaging device, internal structural data representing an internal structure of the aircraft, and position information about the damaged portion relative to the reference position.

Abstract: A method for monitoring at least one engine of an aircraft wherein the aircraft includes a passenger cabin. The method includes a step of acquiring a signal that is at least in part representative of the activity of the engine, using a sensor during a flight of the aircraft, and searching for a defect in the engine by a processing unit using data obtained from the signal. In some embodiments, the sensor is in a mobile device located in the passenger cabin. In some embodiments, the health of the at least one engine uses the signal acquired by a plurality of mobile devices.

Abstract: An aircraft of the type disclosed here includes an aircraft fuselage, a wing assembly, a tail assembly, and a surface structure containing a lightning protection device. The surface structure is arranged on the aircraft fuselage, the wing assembly, and the tail assembly. The lightning protection device has a plurality of electrically conductive elements, which are arranged at least as a group of elements in the surface structure. The electrically conductive elements belonging to a group are arranged parallel to one another, at least in some section or sections, and have different spacings with respect to one another, at least in two regions.

Abstract: An airborne vehicle made of thermally non-conductive materials and method for thermal conduction in an airborne vehicle are disclosed. The airborne vehicle comprising at least one structural element made of material with high thermal conductivity coefficient embedded in the airborne vehicle body. In some embodiments wherein the thermally conductive structural element is a longitudinal profile with hollow center along it. The method comprising disposing structural element with high thermal conductivity embedded in the airborne vehicle and providing thermal pass with high thermal conductivity from the heat source to the structural element with high thermal conductivity, to allow heat to dissipate through the structural element with high thermal conductivity.

Abstract: An integrated aircraft lighting and display panel includes high-density arrays of micro-scale light-emitting diodes (LED) set into a flexible printed circuit board (PCB). The PCB and LED arrays may be set into structural layers corresponding to overhead panels, side panels, bin panels, divider panels, doorway panels, or other interior structural panels of the aircraft. The LED arrays may be activated by a controller to provide cabin lighting, indicate aircraft signage, display high-resolution image or video graphics, or any simultaneous combination of all three. The panel may have a translucent or transparent decorative outer skin which may mimic the outward appearance of wood, stone, bamboo, or other decorative materials while the integrated lighting and display panels are inactive. Highly reflective core materials, such as an aluminum core in a honeycomb pattern, may guide the luminous output of the LED arrays through the outer skin.

Abstract: An aircraft beacon light includes a mounting plate having a central portion; a plurality of light sources arranged on the mounting plate around the central portion and facing away from the mounting plate; and a lens structure arranged over the plurality of light sources, wherein the lens structure is configured to reflect a first portion of light emitted by the plurality of light sources laterally outwards via total internal reflection; wherein the aircraft beacon light is configured to emit flashes of red light in operation.

Abstract: The present disclosure provides an Unmanned Aerial Vehicle (UAV). The vehicle includes a main body; a supporting frame that is connected to the main body; two mounting brackets that are spaced apart; a plurality of shock absorbing structures that connect the supporting frame and the mounting brackets; and two gimbals configured to carry a plurality of payloads. The two gimbals are respectively connected to the two mounting brackets, and the shock absorbing structures absorb shocks on the gimbals.

Abstract: A self-leveling recovery platform for a landing operation of an unmanned aerial vehicle and a method for an unmanned aerial vehicle on a self-leveling recovery platform are described. The platform includes landing includes a base, a landing pad, first to sixth motors, first to sixth arms, an accelerometer, a gyroscope/inertial measurement unit, and a controller. The base is for fixedly mounting to a moving body. The landing pad has a landing surface on which an aerial vehicle can land. The first to sixth motors are attached to the base. The first to sixth arms control the first to sixth motors to the platform. The accelerometer and gyroscope/inertial measurement unit sense motion of the platform and output sensing signals. The controller is responsive to the sensing signals to control each of the motors to adjust the arms such that the landing surface is maintained in a substantially stable plane relative to a predetermined surface.

Abstract: Systems and methods are used to determine a defined fastener for fastening two parts together at an assembly fastener location. The defined fastener comprises fastener components selected from a plurality of different fastener components available for use in an assembled fastener. The fastener components of the defined fastener may be selected based on criteria defining characteristics of an assembly stackup including the two parts and the assembled defined fastener. Dimensions of the two parts at respective fastener locations forming the assembly fastener location may be used to determine a part stackup dimension for the assembled fastener at the assembly fastener location.

Abstract: A method for manufacturing an aircraft rear section including a tail cone and a vertical tail plane, the method includes: providing pre-cured frames (1) each of which includes a section of the tail cone (2) and a section of the vertical tail plane (3); providing pre-cured stringers (4); placing the pre-cured stringers (4) each in respective positions within the pre-cured frames (1); placing a skin (5) around an external surface of the pre-cured frames (1); and curing the pre-cured frames (1), the pre-cured stringers (4), and the skin (5), forming the final aircraft rear section.

Abstract: A method for manufacturing a composite assembly of an empennage and rear-fuselage having a continuous skin solution. The method obtains parts of the sub-structure. For each part, it is obtained a plurality of stringers performs and frames preforms by composite tooling. The frames are transferred to curing frames molds and a sub-structure skin is obtained. Furthermore, the method includes integrating the parts over an integration tool having cavities for locating the curing frames molds and the stringer performs. Furthermore, the method includes co-curing the integration tool in one shot on an autoclave, demolding the sub-structure skin sections and disassembling the curing frame molds to obtain the composite assembly of the rear section.

Abstract: A system is provided for performing an operation on a component of an engine. The component includes a first side positioned within an interior of the engine. The system includes a first robotic arm defining a first distal end and including a first utility member positioned at the first distal end, the first robotic arm moveable to the interior of the engine to a location operably adjacent to the first side of the component; and a second robotic arm defining a second distal end and including a second utility member positioned at the second distal end, the second robotic arm also moveable to the interior of the engine to facilitate the first and second utility members performing the operation on the component of the engine.

Abstract: Methods and apparatus to detect deicing heater conditions are disclosed. A disclosed example apparatus includes an interface to be electrically coupled between a heating element and a power supply, where the heating element associated with an external surface of a vehicle, and where the power supply is to provide power to the heating element. The interface includes a balanced current sensor to measure a differential between a first current of an electrical power line of the heating element and a second current of an electrical return line of the heating element, and a processor to compare the differential to at least one threshold to determine a condition of the heating element.

Abstract: A system and method for performing a test procedure on a system under test are provided. An actuation unit operatively coupled to the system under test is configured to perform at least one operation thereon. A visual recognition unit is configured to capture at least one image of the system under test in real-time. A test unit remotely interfaced with the system under test is configured to perform the test procedure. Using the test unit, the test procedure is retrieved from the memory, at least one control signal is output to the actuation unit for causing the at least one operation to be performed in real-time for testing the system under test in accordance with the one or more test instructions, and the at least one image of the system under test is monitored as the at least one operation is performed for validating the test procedure in real-time.

Abstract: Herein is disclosed an unmanned aerial vehicle sensor calibration device comprising a sensor shield, comprising an inner portion and an outer portion, and configured to shield a sensor of the unmanned aerial vehicle and to dampen transmission of a sensor input from the outer portion to the inner portion; and a sensor reference, configured to generate a reference value of the sensor input for sensor calibration within the inner portion of the sensor shield.

Abstract: A method of operating a sealing station of a packaging machine for producing, in the case of possibly varying filling degrees, packages with at least substantially similar package appearances, the method comprising the execution of a comparison between a detected pressure curve and a reference pressure curve, and the calculation of a filling degree of the package positioned within the sealing station on the basis of the comparison between the detected pressure curve and the reference pressure curve, and/or the calculation of a volume flow with respect to the pressure curve or the reference pressure curve, and the setting of at least one process parameter at the packaging machine with due regard to the calculated filling degree and/or the volume flow.

Abstract: A unit dose container production system (10) is disclosed where a unit dose container (130) is evacuated and thereafter loaded with a radioactive fluid while remaining at a single location. In this regard, the production system (10) uses a first conveyor (12) to sequentially load unit dose containers (130) into an empty container receptacle (24) of a second conveyor (20) at a first location (90). The second conveyor (20) may be operated to dispose a container receptacle (24) at each of the first location (90), a second location (100), and a third location (110). A unit dose container (130) at the second location (100) is evacuated and thereafter loaded with a radioactive fluid, and is thereafter moved to a third location (110) by the second conveyor (20). The unit dose container (130) is removed from the second conveyor (20) at the third location (110), and thereafter the radioactivity content of a unit dose container (130) may be determined, such as at an ionization chamber or the like.

Abstract: An apparatus for packaging a product comprises a packaging assembly to fix a film sheet to a support. The packaging assembly includes a lower tool having seats for receiving the support and an upper tool facing the lower tool and comprising a film holding plate for holding the film sheet. The film holding plate has an active surface for receiving the film sheet, where the upper and lower tools cooperating to define a packaging chamber. The packaging assembly is open to receive the film sheet in a first operating condition and is hermetically closed in a second operating condition. The film holding plate has a lateral surface extending substantially perpendicular to a plane defined by the active surface, the film holding plate comprising ejectors arranged in the lateral surface for ejecting a stream of gas substantially parallel to said plane and substantially away from a center of the active surface.

Abstract: A system for enhanced conveying of flexible packages includes a packaging system (12, 212), an inflation system (280), and a conveying system (250). The packaging system is configured to place an object in a flexible package. The inflation system is configured to insert a gas into the flexible package. The packaging system is further configured to seal an edge of the flexible package in an inflated state with the object and the inserted gas inside the flexible package. The conveying system is configured to convey the flexible package while the flexible package is substantially in the inflated state. The flexible package is configured to permit gas to escape the flexible package at a controlled flow rate such that the flexible package remains substantially in the inflated state while being conveyed by the conveying system and the flexible package transitions to being substantially in a deflated state after being conveyed by the conveying system.

Abstract: A system and method of transporting and loading coextruded meat products in a packaging machine are disclosed. A single line of the coextruded meat products are conveyed using a linear transfer conveyor to an orienting conveyor onto which they are transferred. The orienting conveyor establishes a group of coextruded meat products which is subsequently transported from the orienting conveyor into a cavity of the packaging machine using a pushing device. It is contemplated one or more of these processing lines may run in parallel and that various steps could involve batch operations, such as, for example, multiple groups being pushed into multiple cavities simultaneously.

Abstract: A method for operating a sealing station of a packaging machine, wherein the method may include one or more of the following steps: filling a packing volume of a package with a gas to create a desired atmosphere to a preset gassing target pressure for a finished package, wherein the packaging volume may be defined by a lower and an upper packaging material; discharging a partial amount of the gas introduced into the packaging volume from the packaging volume into a collection volume while retaining the packaging volume generated by the preceding filling, which reduces the pressure within the packaging volume; and reducing the packaging volume by moving the upper packaging material to an end position that corresponds to a desired appearance such that the pressure inside the package increases again to near the gassing target pressure. A sealing station that performs this method is also described.

Abstract: A system and a method for packaging compacted powders are provided, wherein the system comprises a first tube (TC), wherein a screw conveyor (C) is positioned inside the first tube (TC) which is configured so as to rotate around an axis (ac) inside the first tube (TC) in order to convey the powders towards an outlet (UT) of the first tube (TC); the system (100) comprises a rotatable terminal (TI, TIC) in the proximity of the output (UT); the rotatable terminal (TI, TIC) comprises in its inside cutting means (F) which are configured so as to cut the compacted powders leaving the first tube (TC) when the rotatable terminal (TI) rotates, wherein the rotatable terminal (TI, TIC) is positioned so as to contact the end of the first tube (TC) which defines the output (UT).

Abstract: Provided is a labeling apparatus that generates a label for labeling a drug container at a healthcare facility. The labeling apparatus includes a code reader that reads a computer-readable code encoding a drug to be stored by the drug container and transmits a signal indicative of the identity of the drug in response to reading the computer-readable code. A non-transitory computer-readable memory stores a drug formulary comprising a plurality of drug entries. A processing component is configured to identify, from the formulary, the identity of the drug corresponding to the computer-readable code and receives a patient identity from a computer-accessible source. A printer is operable to print label content identifying the specific drug onto a label that is to be applied to the drug container. The label content includes the identity of the drug and the patient identity encoded by a label code that is computer-readable.

Abstract: A portable hybrid hand labeler is disclosed that relies on mechanical motion, which eliminates the need for motors and the corresponding energy required to run the motors. The portable hybrid hand labeler also houses an ink jet head and a digital print mechanism, which offers the user infinite print flexibility via downloadable print bands. The portable hybrid hand labeler is preferably battery driven, and comprises a unique drive system and mechanism to harvest the kinetic energy from the trigger pull and a display panel with a solar panel to collect solar energy to trickle charge the battery pack, thereby increasing usage time between charges.