Abstract: A method of speed control of a wheel rotation drive device carried by aircraft landing gears, comprising the step of regulating an aircraft speed in accordance with a pilot-generated speed command, wherein the speed of the regulated aircraft is a speed (V) measured or estimated at a nose tip of the aircraft

Abstract: The invention relates to a method for controlling the torque of a drive device (1) for rotating wheels (2) of an aircraft comprising actuators for selectively driving rotating wheels of the aircraft to ensure its movement on the ground, comprising the step of regulating a torque generated by the drive device according to a torque setpoint (4) issued by the pilot. According to the invention, the method involves the step of generating, as long as the torque setpoint is not sufficient to guarantee a stable movement speed of the aircraft, a replacement torque setpoint (5) to allow the aircraft to move at a stable speed, and substituting the replacement torque setpoint for the torque setpoint generated by the pilot.

Abstract: Disclosed herein is a flying taxi for facilitating the transportation of payloads, in accordance with some embodiments. Accordingly, the flying taxi may include a pod, a processing device, a presentation device, and an aerial vehicle. Further, the pod may be configured to receive a payload. Further, the pod may include a weight sensor disposed on the pod. Further, the weight sensor may be configured to generate a weight data corresponding to a weight of the payload. Further, the processing device may be communicatively coupled with the weight sensor. Further, the processing device may be configured for analyzing the weight data. Further, the processing device may be configured for generating a notification based on the analyzing. Further, the presentation device may be communicatively coupled with the processing device. Further, the aerial vehicle may be detachably couplable with the pod using a coupling mechanism.

Abstract: The present invention relates to a hybrid helicopter comprising a fuselage, a main rotor, two wings situated on either side of said fuselage, and two propulsion propellers situated respectively on each wing. Each propulsion propeller is inclined, and when it rotates it generates a thrust force (Fd, Fg) along a thrust axis (Pd, Pg) that is inclined relative to a longitudinal direction (X) of said hybrid helicopter. As a result, a longitudinal component and a transverse component of said thrust force (Fd, Fg) of each propulsion propeller act, during hovering flight of said hybrid helicopter, to generate respective torques that combine to form a moment (Mstat) opposing a yaw torque (CR) of said hybrid helicopter.

Abstract: A folding propeller-hub assembly for VTOL aircraft provides two modes of operation, a vertical mode with unfolded propeller blades and a horizontal mode with propeller blades positionable in both an aerodynamic folded position and an active unfolded position. The propeller-hub assembly includes a plurality of propeller blades, a bedplate operably associated with a propeller-hub to fold or respectively unfold the propeller blades, the motor arranged between the propeller-hub and a rotating plate, a push rod positioned in the axis of the propeller rotation along the propeller-hub assembly. The bedplate is operably associated with a device which connects with the spinner bottom of the spinner to rotate the propeller blades. A restraint plate by virtue of the push rod is operably associated with the propeller blades to rotate each propeller blade about a propeller blade pin axis.

Abstract: A swashplate assembly includes: a mounting sleeve configured for coupling to and around an upper portion of a gearbox, wherein the mounting sleeve extends downwards from the upper portion of the gearbox; a tilt sleeve coupled to the mounting sleeve, wherein the tilt sleeve has a curved exterior surface; a non-rotating swashplate ring positioned around the tilt sleeve, wherein the non-rotating swashplate ring has a first set of pitch control connectors and an anti-rotation connector; a rotating swashplate ring rotatable about the non-rotating swashplate ring, wherein the rotating swashplate ring has a second set of pitch control connectors and a drive link connector; and a first bearing system mounted between the non-rotating swashplate ring and the rotating swashplate ring.

Abstract: An adjustable shape kite has a wing of a flexible material and an adjustable bridle system. The wing is a single layer wing that does not include structural support to provide its shape during flight. The bridle system is adjustable to adjust the wing curvature during flight. An aerodynamic shape is formed in the wing with a leading edge and side edges being rolled over by oncoming wind acting against the wing in conjunction with tensile forces acting thereon by the bridle lines of the bridle system.

Abstract: An imaging device for use on-board a reconnaissance vehicle comprises an image capturing unit configured to capture images of a photographic area. A control unit communicates via a serial communications interface with a control body unit of the reconnaissance vehicle, and operates in an image photographing mode that receives control information from the control body unit of the reconnaissance vehicle via the serial communications interface and in an image transfer mode that transfers the images to the control body unit of the reconnaissance vehicle via the serial communications interface in accordance with a data transfer protocol. The control unit responds to detecting mode switching conditions to switch autonomously from the image photographing mode to the image transfer mode. Only a single serial communications interface is needed both to control the imaging device and to transfer the captured images from the imaging device in the image transfer mode.

Abstract: Embodiments relate to reconfigurable unmanned vehicles (100). Such vehicles (100) comprise a fuselage (102) presenting a bay (118) for receiving a plurality of components (120-128), each of the plurality of components (120-128) relating to a respective entity for at least one of flight control or operation of the unmanned vehicle (100). The bay (118) comprising a bus to support communications between at least two of the plurality of components (120-128), the plurality of components (120-128) comprising a controller to determine a configuration or presence of one or more than one component of the plurality of components (120-128) when coupled to the bus.

Abstract: A remotely controlled VTOL aircraft includes an autopilot subsystem outputting helicopter control signals, and an autopilot subsystem outputting fixed wing control signals. A transition control subsystem is configured to receive said helicopter control signals, said fixed wing control signals, and a transition control signal. Control signals to be applied to the VTOL aircraft controls are calculated as a function of the transition percentage and weighting factors applied to the helicopter control signals and said fixed wing control signals.

Abstract: A vision system for a vehicle includes a forward viewing camera disposed at a vehicle and viewing forward of the vehicle through the windshield. A control is disposed at the vehicle and includes an image processor operable to process image data captured by the forward viewing camera. An aerial platform is detachably disposed at the vehicle and is operable to detach from and fly at least above the vehicle. The aerial platform includes a drone camera that captures image data and the image data captured by the drone camera is wirelessly communicated to the control. A video display is disposed in the vehicle and is viewable by a driver of the vehicle. The video display, with the aerial platform detached from the vehicle and flying at least above the vehicle, displays video images derived from image data captured by the drone camera for viewing by the driver of the vehicle.

Abstract: The present invention relates to a method and a device for lifting a load, wherein at least one aerial drone carries at least a portion of the load. In order to lift a load, it is proposed to yoke together a plurality of aerial drones or at least one aerial drone and a lifting hook of a crane, and provide a common control system for the plurality of aerial drones or the at least one aerial drone and the lifting hook of the crane, in order not to have to control a plurality of aerial drones at the same time, or also an aerial drone in addition to the crane hook, using separate control means, in a “multi-handed” manner.

Abstract: A passenger rest cabin situated in the overhead crown area of an aircraft provides individual rest compartments along either lateral side of a central longitudinal corridor of limited height. The corridor and entrance thereto is configured to minimize the risk of claustrophobia by providing sensory preparation systems and techniques. Sensory preparation including transitional compartments with variations in video, lighting and ventilation are presented to the passenger to create a more inviting space. The limited height corridor is equipped with a series of handholds, sized and spaced according to the size of the average passenger, to mitigate the strain of traversing the corridor in a bent over position.

Abstract: A modular lower lobe passenger rest cabin includes passenger rest compartments oriented longitudinally along the roll axis and laterally along the pitch axis. Partial passenger rest compartments are defined by the modular lower lobe passenger rest cabin such that when two modular lower lobe passenger rest cabins are installed in a cargo deck of an aircraft, the partial passenger rest compartments define a single passenger rest compartment or aisle from space that would otherwise be insufficient for the purpose.

Abstract: An aircraft partition system that includes a first partition assembly that includes a carriage assembly that is configured to be secured to at least one of first and second passenger service unit rails and a divider wall having first and second opposing sides and extending downwardly from the carriage assembly.

Abstract: A trash can device for an aircraft lavatory unit is provided, including: a waste container in a storage chamber of the aircraft lavatory unit; a chute, disposed above the waste container, including a trash feed opening formed at a section of the chute corresponding to a trash feed port of a panel sectioning off the storage chamber; and a waste flap that opens and closes the trash feed opening. A fire spreading prevention space is formed below the chute in a state when the waste flap is positioned in a closed position in which the trash feed opening is closed by the waste flap. The trash can device is provided with a holding/moving portion of the waste flap, the holding/moving portion holds the waste flap in an open position in which the trash feed opening is opened and moves the waste flap to the closed position when exposed to heat.

Abstract: An aircraft portion having a floor and a fuselage structure forming an arch above the floor is disclosed in which a monument is mounted within the fuselage. The monument is suspended from the fuselage structure by at least one suspension point, so that most of the weight of the monument is taken up by the fuselage structure. The monument includes a circular or a round section configured to take up the vertical forces than the horizontal floor, which bends under vertical loads.

Abstract: A track fitting for securing a seat pedestal of an aircraft seat to a floor of an aircraft may comprise a strut and a lock assembly. The strut may include an aft section configured to attach to an aft foot of the seat pedestal, a forward section configured to attach to a forward foot of the seat pedestal, and a central section extending between the aft section and the forward section. The lock assembly may be located proximate the aft section of the strut.

Abstract: Apparatus and methods for providing a desired volumetric conditioned airflow rate and for reducing noise level, airflow recirculation and airflow separation are disclosed. An example apparatus includes a nozzle housing having a pair of opposing sidewalls and a front and back wall that define an airflow passage. The airflow passage has a centerline extending between the inlet and the outlet and has a plurality of cross-sections taken perpendicular to the centerline that collectively define a smooth contour along a length of the airflow passage. The cross-sections each have a thickness between the front and back wall that is greater at side edges than at the centerline. The thickness of the cross-sections decreases along a length of at least a first portion of the nozzle housing. A width of each of the cross-sections between the sidewalls increases along the length of at least the first portion of the nozzle housing.

Abstract: An aircraft includes an aircraft heat source; a propulsion system including an electric propulsion engine, the electric propulsion engine including an electric motor and a fan rotatable by the electric motor, the electric propulsion engine further defining a fan air flowpath; a thermal management system including a heat source exchanger in thermal communication with the aircraft heat source, a heat sink exchanger in thermal communication with the fan air flowpath of the electric propulsion engine, and a thermal distribution bus extending from the heat source exchanger to the heat sink exchanger; and a control system operably connected to the thermal management system for selectively thermally coupling the heat sink exchanger with the heat source exchanger.

Abstract: Systems to produce cabin supply air for aircraft and related methods are described herein. An example system includes an air conditioning pack including a heat exchanger including a first flow path and a second flow path isolated from the first flow path. The second flow path is to receive cabin exhaust air from a cabin of an aircraft. The cabin exhaust air is to reduce a temperature of the cabin supply air flowing through the first flow path of the heat exchanger. The system also includes a turbine to receive the cabin supply air from the heat exchanger. The turbine is to reduce a temperature and pressure of the cabin supply air. A turbine outlet of the turbine is fluidly coupled to the cabin to provide the cabin supply air to the cabin. The system further includes a fan to direct the cabin exhaust air from the heat exchanger.

Abstract: An attachment for attaching an aircraft engine with a first receiving element to an aircraft structure with a second receiving element may include at least three fasteners and a stacked layer. Stacked layer may include at least two sheets, at least three holes through the stacked layer, a first connecting portion that includes a first hole of the at least three holes, a second connecting portion that includes second and third holes of the at least three holes, and a suspension portion that is located between the first connecting portion and the second connecting portion.

Abstract: An aircraft that includes a fuselage, an electric motor driven propulsion system, and a fuel cell system configured to provide electricity to the electric motor. The fuel cell system includes a fuel cell, a hydrogen tank, an oxygen tank, an air channel, and a cathode switch. The cathode switch being configured to convert between an air mode, wherein the fuel cell operates utilizing air from the air channel, and an oxygen mode, wherein the fuel cell operates utilizing oxygen from the oxygen tank.

Abstract: A fuel tank inerting system including: a catalytic reactor comprising an inlet, an outlet, a reactive flow path between the inlet and the outlet, a catalyst on the reactive flow path, and a temperature sensor located between the inlet and outlet, wherein the catalytic reactor is arranged to receive fuel from a fuel source and air from an air source that are mixed to form a combined flow, and to react the combined flow along the reactive flow path to generate an inert gas.

Abstract: Fuel tank inerting systems for aircraft are provided. The systems include a fuel tank, a catalytic reactor arranged to receive a first reactant from a first reactant source and a second reactant from a second reactant source to generate an inert gas that is supplied to the fuel tank to fill an ullage space of the fuel tank, a heat exchanger arranged between the catalytic reactor and the fuel tank and configured to at least one of cool and condense an output from the catalytic reactor to separate out the inert gas, and a controller configured to perform a light-off operation of the catalytic reactor by controlling at least one light-off parameter and, after light-off occurs, adjusting the at least one light-off parameter to an operating level, wherein the at least one light-off parameter comprises a space velocity through the catalytic reactor.

Abstract: Fuel tank inerting systems for aircraft are provided. The systems include a fuel tank, a catalytic reactor arranged to receive a first reactant from a first reactant source and a second reactant from a second reactant source to generate an inert gas that is supplied to the fuel tank to fill an ullage space of the fuel tank, a heat exchanger arranged between the catalytic reactor and the fuel tank and configured to at least one of cool and condense an output from the catalytic reactor to separate out the inert gas, and a controller configured to perform a light-off operation of the catalytic reactor by controlling at least one light-off parameter and, after light-off occurs, adjusting the at least one light-off parameter to an operating level, wherein the at least one light-off parameter comprises an inlet temperature of a gas at an inlet of the catalytic reactor.

Abstract: Fuel tank inerting systems for aircraft are provided. The systems include a fuel tank, a catalytic reactor arranged to receive a first reactant from a first reactant source and a second reactant from a second reactant source to generate an inert gas that is supplied to the fuel tank to fill an ullage space of the fuel tank, a heat exchanger arranged between the catalytic reactor and the fuel tank and configured to at least one of cool and condense an output from the catalytic reactor to separate out the inert gas, and a controller configured to perform a light-off operation of the catalytic reactor by controlling at least one light-off parameter and, after light-off occurs, adjusting the at least one light-off parameter to an operating level, wherein the at least one light-off parameter comprises a temperature of the catalytic reactor.

Abstract: Fuel tank inerting systems for aircraft are provided. The systems include a fuel tank, a catalytic reactor arranged to receive a first reactant from a first reactant source and a second reactant from a second reactant source to generate an inert gas that is supplied to the fuel tank to fill an ullage space of the fuel tank, a condensing heat exchanger arranged between the catalytic reactor and the fuel tank and configured to at least one of cool and condense an output from the catalytic reactor to separate out the inert gas, and a controller configured to perform a light-off operation of the catalytic reactor by controlling a light-off parameter and, after light-off occurs, adjusting the light-off parameter to an operating level, wherein at least one light-off parameter comprises an air-to-fuel ratio.

Abstract: A high-fidelity, multi-point, full-mission sonic-boom propagation tool that includes functionality to handle aircraft trajectories and maneuvers, as well as, all relevant noise metrics at multiple points along the supersonic mission. This allows efficient computation of sonic-boom loudness across the entire supersonic mission to allow pilots and aircraft operators to plan the aircraft flight path to manage the sonic boom footprint.

Abstract: A method for detecting and reporting anomalies in operation of an aircraft. The method including the steps of: receiving real time data indicative of the operation of the aircraft, the real time data including at least one of the following parameters: ground speed, rate of deceleration of the aircraft, touchdown location, aircraft route, timing of aircraft route, ground movement activities and a maximum landing distance; based on the collected real time data, calculating a predicted performance of the aircraft, and alerting an operator when the predicted performance is outside of an acceptable performance for the aircraft.

Abstract: A system and a method for autonomous hydrogen refueling of vertical lift aircraft using a landing pad with sensors, a hydrogen storage tank, a refueling arm configured to couple the hydrogen storage tank to the aircraft and a controller configured to control a flow of fuel from the hydrogen storage tank to the aircraft.

Abstract: An integrated monitoring system and method are provided with the capability for monitoring ground surface movements of electric taxi drive system-driven aircraft, ground vehicles and personnel, and objects within airport ramp areas. Monitoring units may include a scanning LiDAR device with and without cameras or other sensing devices to transmit meshed real time encrypted data from multiple locations to an artificial intelligence-based processing system that generates a visual display of the monitored area for communication to aircraft cockpits and locations responsible for controlling ramp operations. Monitoring units may be mounted in single or multiple exterior locations on aircraft and/or in locations on ground vehicles and equipment, ground personnel, and the airside portion of an airport terminal.

Abstract: A method and a system for detecting and positioning an intruder within a specified volume are provided herein. The method may include the following steps: periodically scanning using a laser detection and ranging (LADAR) device directing a laser beam, within the specified volume; collecting reflections of the laser beam arriving from objects within the volume; converting the reflections to LADAR signal indicative of spatiotemporal presence of objects within the volume; applying signal processing algorithms to the LADAR signals, to determine a presence of an intruder and respective orientation parameters, based on predefined criteria; directing a camera based on the orientation parameters associated with the intruder for continuously capturing images of the intruder; and analyzing the images by a computer processor and instructing the camera to track the intruder based on the analysis, to yield real-time tracking parameters of the intruder.

Abstract: A method for assembling at least two parts includes using transparent welding using an energy input beam which travels a trajectory in a closed loop. The trajectory of the energy input beam and/or at least one parameter of the energy input beam is configured so that the weld bead has mechanical and/or geometrical characteristics that are substantially constant over all its length. A method for assembling a primary structure of an aircraft pylon which uses this assembly method to link the panels of the primary structure to one another, a primary structure of an aircraft pylon thus obtained, as well as an aircraft comprising at least one such primary structure is also described.

Abstract: A spray containment system for a wing-body section includes a forward module, a center module, and an aft module. The forward module has a forward closeout panel configured to engage a forward end of a fuselage center section of the wing-body section. The center module has opposing module side panels each configured to engage a wing lower surface of a wing of the wing-body section. The aft module has an aft closeout panel configured to engage an aft end of the fuselage center section. The forward module and the aft module are independently movable and are configured to be assembled around the wing-body section to define an internal environment that is sealed from an external environment for containing contaminants including at least one of vapors, overspray, and liquids generated during application of one or more of coatings, sealants, and adhesives to localized areas of the wing-body section.

Abstract: Devices for maintaining crawler alignment on complex-shaped blades and for enabling the blade crawler to traverse over trailing edge protrusions. Using ball and socket bearings or air pads in place of alignment wheels, the crawler will be able to track along complex-geometry rotor blades, propellers and other airfoils. Using an oversized-diameter roller, a semi-flexible roller, or a dual-roller arrangement, the crawler will be able to traverse over trailing edge protrusions.

Abstract: In an example, a method for determining whether to perform aircraft maintenance is described. The method comprises selecting groupings of sensors and/or parameters associated with an aircraft type. The method comprises receiving feature data that corresponds to each grouping of sensors and/or parameters. The method comprises determining, from the feature data, values for predetermined operational metrics. The method comprises comparing the values to values for predetermined operational metrics that correspond to at least one other flight of the aircraft. The method comprises determining, based on comparing the values for the predetermined operational metrics, values of additional operational metrics. The method comprises training a machine learning model using at least the values for the additional operational metrics.

Abstract: A flight control system for an aircraft is disclosed. The flight control system includes one or more processors and a memory coupled to the processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the flight control system to receive as input a plurality of first operating parameters that each represent an operating condition of the aircraft. The flight control system is further caused to determine a drag coefficient and a lift coefficient based on the plurality first of operating parameters. The flight control system is also caused to determine an estimated dynamic pressure based on both the drag coefficient and the lift coefficient.

Abstract: Provided are embodiments including a method, system and computer program product for collecting aircraft performance data using smart applications. Some embodiments include receiving sensor data from one or more sensors of one or more user devices associated with an aircraft, and detecting an aircraft event of the aircraft based at least in part on the sensor data. Embodiments can also include analyzing performance of the aircraft by comparing the sensor data with historical data for the aircraft event responsive to detecting the aircraft event, and mapping the performance of the aircraft to the received sensor data.

Abstract: Pre-flight and episodic aircraft inspections to ensure operational safety and effectiveness are made faster, less costly and more effective by utilizing mobile model and data-driven sensor platforms inspecting known-state target vehicles. For autonomous aircraft, an inspection unmanned aerial vehicle (I-UAV) containing sensors inspects a utility unmanned aerial vehicle (U-UAV). Failure and system models of the U-UAV and the flight history of the U-UAV carried in the sensor data captured by the U-UAV's aircraft health management system are combined to guide the I-UAV to appropriately attend to the systems of the U-UAV and to drive the U-UAV systems into target states that will reveal otherwise hidden or latent failures.

Abstract: A fatigue level calculating device includes an environment information acquiring unit that acquires environment information pertaining to an environment in the surroundings of equipment, and a fatigue level calculating unit that calculates a relationship between an operation condition of the equipment and a fatigue level of the equipment based on the environment information.

Abstract: The invention discloses an industrial perfume quantitative charging machine in a factory. A casing is provided with a working cavity therein. A charging component is provided on an inner wall at the rear side of the working cavity. The charging component includes a fixed component. The spice box on the inner wall of the rear side of the working chamber, the spice chamber provided in the spice box, a conduit connected between the spice chamber and the working chamber, and slidingly connected to the inner wall of the back side of the working chamber Loading slider. The present invention uses a charging slider to effectively control the communication between the fragrance cavity and the container. Using components such as electromagnets and left-right symmetrical ratchet teeth, it can peel skinned containers of different weights and ensure industrial spices.

Abstract: A bulk container vacuum filing system includes a base portion and movable portion. The bulk container vacuum filing system serves to position and maintain a bulk container within a chamber, seal the interior of the chamber, dispense material into the bulk container, and draw a vacuum or create positive pressure within the chamber and/or the bulk container during at least a portion of the dispensing process. Base portion of the bulk container vacuum filing system includes a vacuum source and a material supply line along with electronic controls and sensors for operating and monitoring the filling process. The moveable portion include a support structure for supporting the bulk container, such as a bulk bag, in the proper place.

Abstract: Described and illustrated is a device for at least partially unfolding package sleeves, having a magazine comprising a stack formed from package sleeves, wherein the package sleeves of the stack are folded flat around at least two folding edges extending in the longitudinal direction of the package sleeves and wherein a gripper is provided for gripping a side of the package sleeves facing away from the stack and for moving, in particular pulling, the package sleeves along a withdrawal transport path with the folding edges into grooves of at least one receptacle of a moulding station and wherein the grooves are spaced so that the folding edges of the package sleeves are spaced apart further in the magazine than in the grooves.

Abstract: The present disclosure is directed to a non-traceable vent tube and a traceable vent tube cap apparatus, system and methods incorporating a traceable material such as a Radio Frequency Identification (RFID) tag or a magnet for use in conjunction with a filling machine during container filling operations for a quicker and more accurate detection of the location of the non-traceable vent tube or the traceable vent tube cap after becoming detached from a filling machine during filling operations, and to increase the safety of the filling operation and reduce costs and time when a malfunction occurs.

Abstract: The present disclosure relates to a positioning unit for positioning a container element in a container body comprising a base plate of a rigid material, and a plunger skirt of a resiliently deformable material. A footprint surface of the base plate has a circumferential edge with a side edge portion comprising an inwardly curved segment. The plunger skirt is transformable between an unexpanded state and an expanded state by relative movement in relation to the base plate. The disclosure further relates to an attachment unit for attaching a container element to a container body and to an apparatus for attaching container elements to container bodies in a flow of containers. In addition, the disclosure relates to a method of positioning a container element in a container body by means of the positioning unit.

Abstract: A wrapping machine with rotary platform for wrapping products with one band includes a base, a rotary platform defining a supporting plane and mounted on the base to rotate about a rotation axis perpendicular to the supporting plane, and supporting rollers interposed between the base and platform and distributed around the rotation axis. The machine also includes a guiding upright parallel to the rotation axis, a supporting slide movable along the guiding upright for receiving and retaining a reel of band, an intermediate disc mounted between and coupled to the base and platform to rotate about the rotation axis, the supporting rollers being mounted on the intermediate disc and in contact with the base and platform, and a transmission system for rotating the platform and intermediate disc about the rotation axis.

Abstract: A cable tie tensioning and severing tool includes: a cutting member, a pulling member with a pivotable pushing block abutting against the cutting member, a trigger with a stop block abutting against the pushing block, a pivotable pressing hammer, a turning knob, and an elastic member compressed between the pressing hammer and a spirally ramped end face of the turning knob such that the pressing hammer applies to the cutting member a pressing force whose magnitude can be adjusted by rotating the turning knob. The stop block can be driven by the trigger to push the pushing block, which in turn pulls a cable tie through the pulling member and, once the pressing force is overcome, pivots the cutting member to sever the cable tie.

Abstract: The invention relates to a method and a device for packaging a flexible hydrophilic intraocular lens (1) placed flat on an injection support (4) which is adapted to carry out folding of the lens (1) during its implantation. The lens is immersed in a bath of liquid conserving solution contained in a sealed flask (30) which is itself enclosed in a packaging envelope (48), the assembly being steam-sterilized.

Abstract: Systems and methods for reinforcing physical structures with composite reinforcement systems are disclosed herein. According to aspects of the present disclosure, a composite reinforcement system includes a carrier formed of a plurality of fibers and a blend of at least two reagents impregnated within the carrier. The at least two reagents are chemically configured to react to form a moisture-curable prepolymer.