Abstract: The invention relates to a secure wire-based system for a drone. Said system ensures suitable traction on the wire during normal control of the drone and automatically locks the wire to a maximum length predefined by the user. The locking is in one direction: it locks the unwinding of the wire without preventing the winding thereof. The drone thus moves within a half-sphere, the radius of which is the maximum length defined by the user. Said system is made up of a motor (13) and a drum (14) on which a wire (10), having a one-direction locking mechanism, for example (X2), is wound. The system according to the invention makes it possible to limit the possible drone crashing area if the drone malfunctions, and is intended in particular for operations on airports or critical populated or industrial regions.

Abstract: In one aspect, an example system includes: (i) a base including a bottom surface and a first coupling-point; (ii) a vertically-oriented elongate structure comprising a lower end, an upper end, and an inner channel, wherein the inner channel comprises an upper access-point disposed proximate the upper end, wherein the base is coupled to the elongate structure proximate the lower end; (iii) a deployable cushioning-device coupled to the elongate structure; and (iv) a tether comprising a first portion, a second portion, a third portion, and a fourth portion, wherein the first portion is coupled to the first coupling-point, the second portion is coupled to a second coupling-point of the UAV, the third portion extends through the inner channel, the fourth portion extends from the upper access-point to the second coupling-point, and the fourth portion has a length that is less than a distance between the upper access-point and the bottom surface.

Abstract: Unmanned aerial vehicles and related methods and systems are disclosed. An example apparatus includes a processor to determine whether a first location of an unmanned vehicle and a second location of a virtual event is within a threshold distance; and a game experience controller to: control the unmanned vehicle based on a first command associated with a non-augmented state of the unmanned vehicle in response to the first location of the unmanned vehicle and the second location of the virtual event being outside of the threshold distance; and in response to the first location of the unmanned vehicle and the second location of the virtual event being within the threshold distance, control the unmanned vehicle based on a second command associated with an augmented state of the unmanned vehicle to simulate the unmanned vehicle being affected by the virtual event.

Abstract: To avoid interfering with a participant when information on a venue of a competition or an event is provided by using an unmanned aerial vehicle, participant position information acquisition means of an unmanned aerial vehicle escape system acquires participant position information on a position of the participant in the venue of the competition or the event. Movement instruction means instructs an unmanned aerial vehicle for providing information on the venue to move to a position defined based on the participant position information. Layout information acquisition means acquires layout information on a layout of the venue. Escape destination determination means determines an escape destination of the unmanned aerial vehicle based on the participant position information and the layout information. Escape means causes the unmanned aerial vehicle to escape to the escape destination determined by the escape destination determination means.

Abstract: A seal assembly for use with a door within a frame of a galley of an aircraft includes a seal configured to be movably coupled to the door and a seal holder holding the seal. The seal assembly includes a biasing mechanism coupled to the seal holder and configured to hold the seal in an open position by applying a biasing force to the seal holder. An activation mechanism is operably coupled to the seal holder that overcomes the biasing force to move the seal from the open position to a sealed position.

Abstract: An aircraft seat device includes at least one seat bottom unit, which at least partly implements a seat surface and includes a mounting unit, which is configured to be mounted on a mounting plane, and includes at least one carrier element, which extends at least over a large portion of a seat depth of the seat surface and is configured for coupling the seat bottom unit with the mounting unit.

Abstract: Example devices for the rapid attachment of a track mounted product to a track and methods of use are described herein. An example device includes an elongated member having a flange and a body. A first side of the body includes a protruding lip extending from at least a portion of the body between the first end and the second end of the elongated member. The device also includes a first alignment bore coupled to the first side of the flange between the first end and the second end of the elongated member. The device also includes a first boss extending from a second side of the body between the first end and the second end of the elongated member.

Abstract: An environmental control system of an aircraft includes a ram air circuit including a ram air shell having at least one heat exchanger positioned therein, at least one dehumidification system arranged in fluid communication with the ram air circuit, a compressing device arranged in fluid communication with the ram air circuit and the dehumidification system, and an expansion device arranged in fluid communication with the ram air circuit and the at least one dehumidification system.

Abstract: An environmental control system of an aircraft includes a ram air circuit including a ram air shell having a plurality of heat exchangers positioned therein, the plurality of heat exchangers including a first heat exchanger, a second heat exchanger, and a third heat exchanger. The ram air circuit is configured and arranged so that a first medium received at the first heat exchanger passes through the first heat exchanger and then through the third heat exchanger and so that a second medium received at the second heat exchanger passes through the second heat exchanger. A compressing device is arranged in fluid communication with the ram air circuit.

Abstract: An air cycle machine for an environmental control system for an aircraft is provided. The air cycle machine includes a compressor configured to compress a first medium, a turbine configured to receive second medium, a mixing point downstream of the compressor and downstream of the turbine; and a shaft mechanically coupling the compressor and the turbine.

Abstract: An air cycle machine for an environmental control system for an aircraft is provided. The air cycle machine includes a compressor configured to compress a first medium, a turbine configured to receive second medium, a mixing point downstream of the compressor and downstream of the turbine; and a shaft mechanically coupling the compressor and the turbine.

Abstract: A breakaway cover for providing emergency access to a release mechanism for a life raft on a vehicle includes a housing configured to be attached the vehicle. The housing includes a recess wherein the release mechanism may be located. The recess is protected by a cover. The cover has a first end attached the housing and a second end retained to the housing but capable of being pulled free. The cover is configured to fracture along a series of slots proximate the first end when pulled by a user.

Abstract: A hybrid-electric propulsion system includes a turbomachine and an electrical system, the electrical system including an electric machine coupled to the turbomachine. A method for operating the propulsion system includes receiving, by one or more computing devices, a command to accelerate the turbomachine to provide a desired thrust output; receiving, by the one or more computing devices, data indicative of a temperature parameter approaching or exceeding an upper threshold; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine to provide, or assist with providing, the desired thrust output in response to receiving the command to accelerate the turbomachine and receiving the data indicative of the temperature parameter approaching or exceeding the upper threshold.

Abstract: The vehicle receives batteries comprising cells arranged into at least one pack configured to be held in a vehicle structure, the pack being alternatively chosen from among at least one pack(P) and at least one pack(E) which are mechanically interchangeable and electrically substitutable. The pack(P) cells exhibit a maximum power density substantially higher than the pack(E) cells exhibit, and comprise cells exhibiting an energy density per unit mass substantially less than the pack(E) cells exhibit. The maximum electrical power of the pack(P) corresponds to the maximum electrical power needed to accomplish a first vehicle mission and the energy storage capacity of the pack(P) is at least sufficient to accomplish the first mission. The electrical energy storage capacity of the pack(E) corresponds to the electrical energy storage capacity needed to accomplish a second vehicle mission and the maximum electrical power is at least sufficient to accomplish the second mission.

Abstract: A method of operating a hybrid-electric propulsion system for an aircraft includes determining a flight phase parameter for the aircraft is equal to a first value, and operating the hybrid-electric propulsion system in an electric charge mode in response to determining the flight phase parameter for the aircraft is equal to the first value. The method also includes determining the flight phase parameter for the aircraft is equal to a second value different from the first value, and operating the hybrid-electric propulsion system in an electric discharge mode in response to determining the flight phase parameter for the aircraft is equal to the second value.

Abstract: A hybrid-electric propulsion system includes a propulsor, a turbomachine, and an electrical system, the electrical system including an electric machine coupled to the turbomachine. A method for operating the propulsion system includes operating, by one or more computing devices, the turbomachine such that the turbomachine rotates the propulsor; receiving, by the one or more computing devices, a command to accelerate the turbomachine while operating the turbomachine; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to the received command to accelerate the turbomachine.

Abstract: A hybrid-electric propulsion system includes a propulsor, a turbomachine, and an electrical system having an electric machine coupled to the turbomachine. A method for operating the propulsion system includes operating, by one or more computing devices, the turbomachine to rotate the propulsor and generate thrust for the aircraft; receiving, by the one or more computing devices, data indicative of an un-commanded loss of the thrust generated from the turbomachine rotating the propulsor; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to receiving the data indicative of the un-commanded loss of thrust.

Abstract: A thrust reverser assembly and a method of operating an aircraft during a taxi mode of operation are provided. The thrust reverser assembly includes one or more actuator assemblies configured to modulate a position of a moveable portion over a continuous range of travel between a fully stowed position and a fully deployed position, such that an air flow through said thrust reverser bleed passage is correspondingly varied. The thrust reverser assembly also includes a throttle device that includes a first, ground idle power level position and a second, forward thrust mode position. Movement into the second position may be actuated separately and differently from movement into the first position. An actuator intermediate lock may inhibit actuation of the intermediate forward thrust mode of operation until a plurality of preconditions is met.

Abstract: An example ullage-recirculating catalytic inerting system includes: (i) a plurality of fuel tanks having (a) respective inert gas ports for discharging the inert gas within a respective fuel tank, and (b) respective ullage gas ports for drawing ullage gas from the respective fuel tank; and (ii) an inert gas generating system including (a) an ullage gas inlet port fluidly coupled to the respective ullage gas ports, (b) an inert gas outlet port fluidly coupled to the respective inert gas ports, (c) a catalytic reactor for chemically converting ullage gas received through the ullage gas inlet port to inert gas for discharge through the inert gas outlet port, and (d) a prime mover for moving gas through the inert gas generating system.

Abstract: The present invention relates to a method for monitoring the ageing of a landing gear of an aircraft, implemented by an autonomous measurement device installed on said landing gear and comprising sensors and a memory for storage, and comprising: after a landing of the aircraft, a stand-by step comprising detection by means of said sensors of the position of the landing gear at a first sampling frequency, for as long as the position of the landing gear is detected as vertical; after detection of a horizontal position of the landing gear, a sleep step comprising detection by means of said sensors of the position of the landing gear at least at a second sampling frequency, for as long as the position of the landing gear is detected as horizontal; after detection of a vertical position of the landing gear, a measurement step comprising acquisition by means of said sensors of physical parameters relating to the ageing of the landing gear, and detection of a landing of the aircraft at a third sampling frequency unt

Abstract: Methods and systems for detecting skew in a wing slat of an aircraft are provided. At least one pair of sensors associated with the wing slat is excited via at least one first electronic device. In response to the exciting and at the at least one first electronic device, at least one pair of signals indicative of at least one pair of state-change counts for the at least one pair of sensors is obtained. The at least one pair of state-change counts is transmitted to at least one second electronic device communicatively coupled to the at least one first electronic device. At the at least one second electronic device, a skew level of the wing slat is determined based on the at least one pair of state-change counts.

Abstract: According to an aspect of the invention, a method of optimal safe landing area determination for an aircraft includes accessing a probabilistic safe landing area map that includes a plurality of probabilistic indicators of safe landing areas for the aircraft. A processing subsystem that includes one or more processing resources generates a list of candidate safe landing areas based on the probabilistic safe landing area map and one or more constraints. At least two of the candidate safe landing areas are provided to a path planner. The list of candidate safe landing areas is ranked based on results from the path planner indicating an estimated cost to reach each of the candidate safe landing areas. Based on the ranking, an indicator of an optimal safe landing area is output as a desired landing location for the aircraft.

Abstract: An aircraft landing gear assembly (112) including a shock absorber strut (114), a bogie (120), a link assembly (124), and a movement detector (132). The shock absorber strut includes an upper and a lower telescoping parts (118, 116), the upper part being connectable to the airframe of an aircraft and the lower part being connected to the bogie such that the bogie may adopt different pitch angles. The link assembly extends between the upper and lower telescoping parts, such that relative movement between the upper and lower telescoping parts causes relative movement between parts of the link assembly. The movement detector is arranged to detect movement of the link assembly relative to the bogie. The movement detector detects movement by sensing a change in linear displacement of, or angle between, one or more members.

Abstract: A method, system, apparatus, and/or device for capturing an image from an aerial vehicle. The method, system, apparatus, and/or device may include a boom, a motor, a propeller, a controller, a top plate, a bottom plate, and an image capturing device. The boom may be an arm that extends outwardly. The motor may be connected to an end of the boom. The propeller may be connected to the motor. The motor may be configured to rotate the propeller to lift the system, the apparatus, and/or the device into flight when the motor is engaged. The controller may be configured to control the motor. The top plate may be connected to a first end of the boom. The bottom plate may be connected to a second end of the boom. The image capturing device may be mounted to the top plate or the bottom plate.

Abstract: A stabilizing platform for stabilizing a payload includes a frame assembly, a plurality of actuators, and a plurality of electronic speed control (ESC) units. The frame assembly includes a plurality of frame components movable relative to one another and is configured to support the payload. The plurality of actuators are configured to permit the plurality of frame components to move relative to one another. The plurality of actuators include a first actuator that is configured to control movement of the payload about a first axis and a second actuator that is configured to control movement of the payload about a second axis. Each of the plurality of ESC units is electrically coupled to a corresponding actuator of the plurality of actuators and is configured to control actuation of the corresponding actuator. At least one of the plurality of ESC units is received in the payload.

Abstract: A portable, lightweight, sturdy and compact aircraft cover that is suspended above the aircraft to provide protection from the damaging effects of the sun and other elements is described. The compact and lightweight aircraft cover is capable, when not deployed, to be carried within the cargo area of the airplane while the aircraft is in operation, and then deployed once the aircraft arrives at its destination. The aircraft cover is very lightweight while at the same time very strong, to allow for the cover to be carried inside the airplane while not adversely impacting the airplane's ability to carry additional fuel or additional passengers and baggage. Furthermore, the cover is designed to be quickly and easily deployed over an aircraft with minimal amount of user effort.

Abstract: A solution to the problem of short battery life of drones and operation in isolated or distant areas of service, by means of docking station/stations that allow for the autonomous landing/takeoff, storage, recharging and/or battery swapping for the drone/drones. The station is multi-cell station for drones with one or more landing/takeoff cells; at least two docking/storage cells; a transitioning closed-loop system configured for transporting the drones within the landing/takeoff cells and docking/storage cells; and control means configured for autonomous control, operation and management of the multi-cell station, where each one of the one or more landing/takeoff cells and at least two docking/storage cells shares at least two sides with neighbouring cells. Recharging mechanism for recharging the stored drones and transitioning mechanism for circulating the drones within the cells of the station are also provided.

Abstract: An unmanned aerial vehicle (UAV) ground station, comprising: a landing surface having a perimeter and a center; a plurality of pushers held above the landing surface by a plurality of linear actuators; at least one electro-mechanical connector attached to one of the plurality of pushers, mechanically adapted to be electrically connected to a compatible electro-mechanical connector of a UAV; and a landing detection controller adapted to instruct the plurality of linear actuators to move the plurality of pushers simultaneously from the perimeter toward the center when a landing event related to the UAV is detected.

Abstract: A landing pad receives and stores packages delivered from an aerial vehicle are awaiting pickup from an aerial vehicle. The landing pad can be placed outside of a window and can contain a transmitter for sending out an identification signal via radio frequency to aid aerial vehicles in finding the landing pad. The landing pad contains a landing platform with a trapdoor that leads to a storage compartment. The trapdoor can be configured to only open when it receives a signal from an authorized aerial vehicle. The storage compartment can be accessed via a storage compartment door which can contain a locking mechanism. The storage compartment can be climate controlled. The landing pad can also have a transmitter that emits sounds to discourage animals from nesting on or near the landing pad. The landing pad can also include a solar power generator as a source of electrical energy.

Abstract: A gantry system for processing an aircraft includes a gantry receiving a fuselage of the aircraft having a gantry frame with an arched member. The gantry system includes first and second locating arms extending between inner and outer ends movably coupled to the gantry frame. The gantry system includes a bracket assembly having a first locating arm bracket pivotably coupled to the first locating arm, a second locating arm bracket pivotably coupled to the second locating arm, and a head assembly bracket with a head assembly coupled thereto having an end effector for processing the fuselage. The head assembly is variably positionable by the first and second locating arms moving along the gantry frame for positioning the end effector relative to the fuselage.

Abstract: A device and a method of assembly by brazing or diffusion-welding under a gaseous pressure is provided to make structures for a nacelle of an aircraft turbojet engine such as an inner fixed structure. Sealing of the assembly space inside which the parts to assemble are disposed is provided by tie members exerting a mechanical pressure on mold elements. The tie members include jaws made of a first material and a holding element made of a second material. The first material has a thermal expansion coefficient higher than that of the second material.

Abstract: Apparatus, systems, and methods for placing a part may automatically self-align the part relative to a target along multiple axes of movement, such as along the width of the part, and normal to one or more target surfaces of the target. Devices may include one or more installation heads each having a respective retaining portion configured to selectively support and retain the part in association with the respective installation head as the device moves the part from a first location located apart from the target, towards the target. The installation head may be configured to automatically align the part with the target, in response to engagement between one or more part surfaces of the part and one or more target surfaces of the target. The retaining portion may be configured to selectively release the part once the part is automatically aligned with and operatively at the target.

Abstract: Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example apparatus includes means to use an electric propulsion system coupled to a frame of a spacecraft, the electric propulsion system including at least a first thruster and a second thruster, the first thruster adjacent a first side of the frame, the second thruster adjacent a second side of the frame, and means to allow at least one of the first thruster or the second thruster to control the spacecraft without using a chemical propulsion system.

Abstract: Lightweight spacecraft dispenser (1), which consists of a ring structure with several payload ports (2), the surface (3) of the ring structure being at least partially spherical.

Abstract: The present disclosure relates to a method for producing, filling and sealing a medicament container (2?), the method comprising a blow-fill seal process comprising: a molding step, in which a parison (2) is inflated within a mold (1) to form the medicament container (2?), a filling step, in which a medicament (M) is filled into the medicament container (2?), and a sealing step, in which a distal end of a neck (2.2?) of the medicament container (2?) is sealed, wherein the mold (1) is dimensioned such that the neck (2.2?) is formed with an internal radius small enough to allow for a capillary effect of the medicament (M) so that an air bubble remaining in the neck (2.2?) after the filling step and the sealing step is fixed within the neck (2.2?) by capillary forces. The present disclosure also relates to a medicament container (2?) produced by said method.

Abstract: A method of providing filled product bags of sterile and particulate-free fluid includes securing a product bag to one of a plurality of movable cradles, wherein the product bag has a bladder, a stem fluidly connected to an opening of the bladder, and a filter disposed in-line with the stem. After securing the bag, an inlet of the stem is connected to an outlet of a nozzle assembly and at least partially filling the product bag with a fluid through a nozzle of the nozzle assembly to create a filled product bag, wherein filling the product bag includes passing the fluid through the filter and into the bladder. After filling, the stem of the filled product bag is sealed at a location below the filter. The stem is cut at a location above the seal and below the filter.

Abstract: Systems, methods, and apparatus for converting a sheet material into packaging templates can include a converting machine that performs conversion functions, such as cutting, creasing, and scoring, on the sheet material. Items to be packed into boxes formed of the packaging templates can be used as the pattern for determining the location of performance of the conversion functions on the sheet material. Accordingly, no intermediate measuring of the items may be required prior to performance of the conversion functions. Instead, longheads can be positioned adjacent to opposing sides of the items and cross heads can be advanced inward to the positioned longheads.

Abstract: A self-propelled wrapping machine movable around a load, for wrapping the latter with a film of plastic material, comprises a self-propelled carriage with guide means, a column fixed to the carriage and slidably supporting an unwinding unit of the film, sensor means to detect surfaces and/or external edges of the load in their total extension and along a detection direction and process related signals, a control unit to receive the signals from the sensor means, calculate a peripheral outline of plan maximum overall dimension of the load on the basis of the surfaces and/or external edges detected by the sensor means, and process a wrapping path of the wrapping machine around the load on the basis of the peripheral outline so as to avoid collisions with the load; the control unit controls the guide means to guide the wrapping machine along the wrapping path.

Abstract: A reinforcing bar binding machine is provided with a feed means for feeding a wire from a wire reel rotatably mounted on a binding machine body, a braking means for braking a rotation of the wire reel, and a control means that starts a braking to the rotation of the wire reel by the braking means after the wire is fed to a predetermined amount by the feed means.

Abstract: Methods are provided for storing and preserving comestible mollusk material, preferably so as to extend shelf life of the same. In one optional method, comestible mollusk material is placed in a product containing space of a storage container atop a platform of a support structure. The storage container includes an internal compartment having the product containing space. The support structure defines the platform for supporting the comestible mollusk material. The internal compartment further includes a reservoir, configured to retain liquid, below the platform. The platform and/or support structure are configured to direct liquid exuded from the comestible mollusk material to the reservoir. Optionally, the reservoir comprises an absorbent material for absorbing liquid in the reservoir.

Abstract: A developer filling apparatus includes a bag setting portion where a developer bag in which a developer containing toner and a carrier is sealed is set, an accommodation case setting portion where a developer accommodation case for accommodating the developer is set, and a transfer path constructed to initially fill the developer accommodation case set in the accommodation case setting portion with the developer taken out of the opened developer bag while the developer bag is set in the bag setting portion.

Abstract: A method of manufacturing a flexible film container (10) from a flexible sheet of thermoplastic material. A gaseous mixture of fluoride gas and nitrogen gas is then introduced into the interior of the flexible film container, thereby expanding the flexible film container to an inflated configuration. The gaseous mixture is maintained within the flexible film container for approximately 15 seconds to 2 minutes so as to react to form a fluorinated barrier layer or surface. The fluoride gas is then removed from the flexible film container and the flexible film container is deflated to a collapsed configuration. The deflated flexible film container is then provided with a final seal and flattened for final shipment.

Abstract: An automated wrapping technique for vehicle components is disclosed. A component to be wrapped is secured to a fixture, which in turn is coupled to an actuator. A grabber arm grabs a length of wrap from a feed roll. The grabber arm removes the backing and spreads the wrap over the component. The actuator pushes the component upward until the wrap contacts the component surface. An applicator may concurrently smooth the wrap and evacuate trapped air. The wrap may be cut around the periphery of the component, and hemmed. A controller provides instructions to automate the wrapping mechanism.

Abstract: Methods, articles, and apparatus that provide a dual function closure/opening system that utilizes a tape serving as both a sealing closure and as an opening mechanism. For example, in one embodiment, a single adhesive tape is introduced between a container flap and a container panel and then the container flap and the container panel are pressed together forming a bond between the flap and the panel via the adhesive tape thereby closing the container. In another embodiment, one end of a container includes two overlapping flaps and a single adhesive tape is introduced between the overlap of the two container flaps and then the container flaps are pressed together forming a bond between the flaps via the adhesive tape thereby closing the container. The methods and apparatus disclosed herein are directed to any container with at least one flap that overlaps a side panel of the container or that overlaps another flap.

Abstract: A method of applying a tape to an article. The method includes contacting a first activatable adhesive composition of an adhesive tape with a placement device. The adhesive tape has a carrier substrate, the first activatable adhesive composition disposed on a first surface of the carrier substrate, and a second activatable adhesive composition disposed on a second surface of the carrier substrate. The method includes activating the first activatable adhesive composition such that the adhesive tape adheres to the placement device through the first activatable adhesive composition, separating the adhesive tape from a tape delivery system, activating the second activatable adhesive composition, contacting an article with the second activatable adhesive composition, and separating the placement device from the adhesive tape such that the adhesive tape remains adhered to the article.

Abstract: A method of sealing a peelable lid (2) to a flange (4) provided within a metal can body (1) which involves inserting an induction coil (6) into the can body to primarily heat the sealing surface (5) of the flange, whilst keeping the exterior wall of the can relatively cool to avoid tin reflow and decoration degradation of the exterior wall. The induction coil is subsequently removed from the can body and a peelable lid applied to the flange, whereby residual heat in the flange aids the sealing of the lid to the flange, e.g. by allowing activation of a bonding material.

Abstract: A method for quality control of a packaging system is provided. The method comprises receiving a record of packaging identification data, wherein the record of packaging identification data being related to a package. Next, identifying and receiving a record of machine data using said record of packaging identification data, wherein said record of machine data being related to a machine set up used when producing said package. Thereafter, identifying a packaging quality parameter to be checked based on said record of machine data, and requesting a record of packaging quality data related to said packaging quality parameter.

Abstract: A glove stacking apparatus forming a stack of folded gloves has a supporting surface for supporting the stack as folded gloves are added to the stack along a stacking axis. First and second flaps are pivotable about first and second pivot axes on opposite first and second sides of a glove stacking area. The supporting surface is relatively movable as folded gloves are added to the stack. A cyclic flap actuation system is configured to drive a folding action of each flap in which the flaps alternately pivot about the corresponding pivot axis so that each flap folds a first portion of a deposited glove overlapping a flap towards a second portion of the glove at the glove stacking area; the folding action alternating as gloves are added to the stack. Each flap in addition to being pivotable is also laterally movable both towards and away from the stacking area.

Abstract: A pallet wrapping device includes an elongated shaft having a fixed handle along a first end, and a diameter for slidingly receiving the hollow central channel of a roll of stretch film. A stopper is positioned along the second end of the elongated shaft, and includes a dimension that is greater than the dimension of the central channel of the roll of stretch film. A sliding handle unit having a first handle segment, a second handle segment and a hollow interior channel is slidingly positioned along the elongated shaft, and functions as a guide for dispensing the stretch film. A ring shaped member having a high friction material along one surface is disposed between the handle segments, and each handle segment includes an outside dimension that is positionable within the central channel of the roll of stretch film.

Abstract: This disclosure provides methods, systems and devices that may be used to measure, calculate, and orient a device such as a drill bit in a downhole environment. To that end, disclosed are fiber optic gyroscopes, wherein the fiber optic gyroscopes comprise elliptical fiber optic cable coils in a mutually orthogonal arrangement that is tilted relative to a length of a supporting shaft, e.g., tube. Light travels in opposite directions within each of the elliptical fiber optic cable coils, and, subsequently, sensors detect differences in time for each light path of the light that traveled in opposite directions within each one of the elliptical fiber optic cable coils. The elliptical nature of the fiber optic cable coils minimizes the cross-sectional area of the mutually orthogonal arrangement, and thereby makes it well-suited for use in downhole environments where space is at a premium. This disclosure also may provide an inertial measurement unit.