Abstract: A vehicle door unit comprises a rotating lever supported rotatably about a first shaft at a first end, a door mounting coupled rotatably about a second shaft to a second end of the rotating lever, a door attached to the door mounting and being configured to cover an opening in a vehicle and to close off a vehicle interior, and a drive unit configured to rotate the rotating lever about the first shaft between a closed position and an open position. The rotating lever is configured to move the second shaft, on a movement from the closed position to the open position, on a circular path, due to which the door mounting is first moved into the vehicle interior and, on further rotation of the rotating lever, out of the vehicle interior.

Abstract: An eco-wood formulation finds new uses as construction materials. A rigid polymer material sheet for use in building construction comprises a polymer mixture of ultrafine particles of polyvinylchloride (PVC) impact modifier, plant fiber, coupling agent, smoke suppressant, activated clay, lubricant, an activator, environmentally friendly flame retardant, heat stabilizers, odorless crosslinking agent, foaming agent, desmopressin agent. Alternatively, the rigid polymer material sheet is composed of: a polymer mixture of PVC, plasticizer, nitrile rubber, PCC, stearate, zinc oxide, retardant heat, heat stabilizers, crosslinking agent, vesicant; whereby said rigid polymer material sheet provides enhanced thermal resistance and sound attenuation properties for use in building construction, aviation and marine industries.

Abstract: Illustrative embodiments may provide for an apparatus and method of controlling the folding of a wing. The apparatus may include a sensor, an actuator, and a wing fold controller. The method may include receiving a status of at least one of an aircraft and a wing fold system of the aircraft by the wing fold controller of the wing fold system. The method may also include receiving an automated command by the wing fold controller in response to receiving the status. The method may also include operating the wing fold system by the wing fold controller based on the automated command and the status. The method may also include transitioning a wingtip of a wing of the aircraft to one of a flight position and a folded position by an actuator of the wing fold system in response to commands from the wing fold controller.

Abstract: A hinged propeller comprising a hub and one or more blades is disclosed. In various embodiments, a blade is connected to the hub via a hinge, wherein at least a substantial part of the blade has a longitudinal axis that is substantially parallel to a line extending radially from a center of the hub, and wherein the hinge has an axis of hinge rotation that is oriented at a non-zero acute angle to a line that is perpendicular, in a plane of rotation of the hub, to said longitudinal axis.

Abstract: An aircraft hand controller is disclosed. The hand controller includes a set of finger controls on a single hand grip structure, the set of finger controls including a first finger control configured to control throttle of the aircraft and a second finger control, separate from the first, configured to control rotation about a first rotational axis of the aircraft.

Abstract: An oscillating pump system includes a pump operable to circulate a fluid. The pump has a first port stage including an inlet port and an outlet port and a second port stage including a first oscillating port and a second oscillating port. An oscillator disk is disposed between the first port stage and the second port stage. The oscillator disk is rotatable relative to the inlet port, the outlet port, the first oscillating port and the second oscillating port. During rotation, the oscillator disk alternatingly routes the fluid to the inlet port from the first and second oscillating ports and alternatingly routes the fluid from the outlet port to the first and second oscillating ports, thereby generating oscillating fluid flow.

Abstract: An electrified propulsion system for a rotary wing aircraft includes a flight control computer that receives a signal indicative of a power demand on an engine; an engine control system that is in communication with the engine and is configured to control operation of the engine at a selected operating point; a generator that is in mechanical communication with the engine and is configured to receive mechanical power from the engine and convert the mechanical power to electrical power; an electric motor that is in electrical communication with the generator and is configured to receive the electric power; and a rotor that is in mechanical communication with the electric motor; wherein the electric motor is configured to control rotation and provide the mechanical power demand of the rotor at the selected operating point in response to the received signal.

Abstract: A rotor hub assembly for a rotary-winged aircraft includes a spool portion and a plurality of hub arms extending radially outwardly from the spool portion. A rotor blade is connectable to each hub arm. Each hub arm includes a spine portion and at least two leg portions extending from the spine portion. The spine portion and the at least two leg portions defining an I-shaped cross-section of each hub arm. A rotor assembly includes a rotor hub assembly including a spool portion and a plurality of hub arms extending radially outwardly from the spool portion. Each hub arm includes a spine portion and at least two leg portions extending from the spine portion. The spine portion and the at least two leg portions define an I-shaped cross-section of each hub arm. A rotor blade is secured to each hub arm.

Abstract: A bond fixture for bonding a component includes a frame defining a chamber for receiving the component. A first pad and a second pad are mounted to the frame. At least one of the first pad and the second pad is movable relative to the frame to adjust a pressure applied to the component. A caul assembly is adapted to be disposed in thermal communication with the component. The caul assembly heats a localized portion of the component.

Abstract: A monolithic blade of a rotorcraft rotor, the blade comprising at least locally an airfoil zone having a pressure side face and a suction side face. The invention is remarkable in that the blade has a root zone including a finger with a spherical bearing surface arranged at a root end of the blade, a recess suitable for receiving a laminated spherical bearing, and a flexible portion having a preferred direction of deformation in bending about a flapping axis of the blade, the flexible portion being arranged between the finger and the recess.

Abstract: A linkage assembly configured for use on a rotor blade having a first section and a second section, the second section being configured to rotate about a blade fold axis between an aligned position and a rotated position relative to the first section is provided. The linkage assembly includes a bracket having a first portion rotatably coupled to the first section about the blade fold axis and a second portion mounted to the second section. A spacer assembly is positioned between the bracket and an adjacent wall of the second section. The overall thickness of the spacer assembly is adjustable to control a distance between the second section and the bracket to adjust the rotated position.

Abstract: This invention discloses an aerial device (AD) for manned or unmanned flight, comprising a fuselage main body coupled with two or more aerodynamic units via bearings. Each aerodynamic unit is independently moveable and controllable, and thus able to create their own unique aerodynamic vectors, all of which are combined in varying manners to control the flight of the AD. Each unit comprises a structural part, a thruster with a propeller, and a servo wing positioned behind the propeller. More aerodynamic units may be combined with the main body in order to create more control. The units may be programmed or controlled manually to offset or otherwise account for varying environmental conditions such as slope, wind, and turbulence. The apparatus may further be coupled with a PID controller with a multidimensional field of input and output parameters.

Abstract: The present application discloses an apparatus capable of walking and flight. This apparatus includes a central section supported by a plurality of limbs, wherein a distal end of each of the plurality of limbs defines a contact surface. These limbs are configured to generate a walking-type motion in which the contact surfaces of the limbs cooperate with an environmental surface in a manner sufficient to propel the central section relative the environmental surface. The apparatus further includes a motor operably coupled to at least one limb of the plurality of limbs, wherein the motor is drivingly coupled to a propeller, and wherein the motor and propeller are configured to propel the central section in flight.

Abstract: An unmanned aerial vehicle is described and includes a computer carried by the unmanned aerial vehicle to control flight of the unmanned aerial vehicle and at least one sensor. The unmanned aerial vehicle is caused to fly to a specific location within a facility, where the unmanned aerial vehicle enters a hover mode, where the unmanned aerial vehicle remains in a substantially fixed location hovering over the specific location within the facility and sends raw or processing results of sensor data from the sensor to a remote server system.

Abstract: Described is system and method for determining a location of a client device. In one implementation, an unmanned aerial vehicle (UAV) receives an image of the UAV, obtained by the client device. The image is processed to determine a source area of the client device. As the UAV navigates toward the area, it scans the area for the client device and/or obtains additional information from the client device to aid in determining the location of the client device.

Abstract: In some embodiments, systems, apparatuses and methods are provided to enhance delivery of packages. Some embodiments provide an unmanned delivery system comprising: a rotational drive shaft; a crane motor cooperated with the drive shaft that is rotated by the crane motor; a first crane system with a first cord fixed with the first crane system, wherein the first crane system is configured to cooperate with the drive shaft to control the first crane system in controlling the spooling and retraction of the first cord; a control circuit coupled with the crane motor; and a stop switch electrically coupled with the control circuit and positioned to be contacted by a package release hanger secured with the first cord when the first cord is retracted to a first threshold; wherein the control circuit is configured to stop the crane motor in response to receiving a signal from the stop switch.

Abstract: In some embodiments, systems, apparatuses and methods are provided to enhance delivery of packages and/or cargo through the use of unmanned delivery aircraft. In some embodiments, a mechanical package release system is provided that comprises: a package release hanger configured to couple with and suspend from an unmanned delivery aircraft; and one or more tension supports each configured to secure with a package and to releasably couple with the package release hanger wherein a decrease of at least a threshold amount of a force being applied by the weight of the package on the one or more tension supports induces a mechanical release of the coupling between the one or more tension supports and the package release hanger resulting in a release of the package from the unmanned delivery aircraft.

Abstract: Unmanned vehicles can be terrestrial, aerial, nautical, or multi-mode. Unmanned vehicles may efficiently accomplish tasks by autonomously charging or replacing its power source.

Abstract: A fact checking system utilizes social networking information and analyzes and determines the factual accuracy of information and/or characterizes the information by comparing the information with source information. The social networking fact checking system automatically monitors information, processes the information, fact checks the information and/or provides a status of the information, including automatically modifying a web page to include the fact check results. The fact checking system is able to be implemented utilizing a drone device.

Abstract: An example package is disclosed for carrying a load external to a UAV. The package may be generated by folding a sheet of material and include a cavity formed by a top surface section, a bottom surface section, a first side surface section, a second side surface section, a leading edge section, and a trailing edge section of the sheet. The top surface section may include an attachment feature for attaching the package to the UAV. The leading edge section may include leading edge surfaces formed from folds along creases of the sheet to define a front end of the cavity and deflect airflow over a top surface and under a bottom surface of the package. The trailing edge section may include upper and lower surfaces formed from folds along creases and extend from the top and bottom surfaces to intersect and define a back end of the cavity.

Abstract: A modular lavatory monument assembly configured to be positioned in the interior of an aircraft. The modular lavatory monument assembly includes first, second, third and fourth walls that cooperate to form an outer shell that defines a lavatory interior. The fourth wall includes an alcove extending outwardly therefrom. The assembly also includes a sink module positioned in the alcove, a mirror module positioned above the sink module in the alcove, and a door positioned on one of the second or third walls.

Abstract: A plurality of personal units for aircraft passengers is provided. Each personal unit is arranged to define a longitudinal axis. The personal units are arranged to form first and second columns along a floor to define respective first and second column axes, the personal units in each column being arranged side-by-side in a longitudinally offset relationship at an acute angle to the respective column axis. Each personal unit is arranged to define a personal space for accommodating a person in a seated position and accommodating the person in a recumbent position. At least some of the personal units are arranged such that a portion of the personal space of the respective personal unit is arranged in a stacked relationship, in a direction perpendicular to the floor, with respect to a portion of the personal space of a personal unit in the respective other column.

Abstract: Described are commercial aircraft cabin arrangement comprising a plurality of seat units (14), each seat unit including a primary seat (16) and a secondary seat (18) arranged facing one another. The primary seat (16) and the secondary seat (18) are configured to combine into a single bed position for the seat unit. The plurality of seat units (14) are arranged in two columns separated by a wide central aisle (72).

Abstract: An aircraft tray table assembly includes a recessed storage compartment covered by a pivoting lid which becomes an integral part of the tray table surface upon closing. A mirror may be fixedly attached to the inside of the lid. A passenger may be provided a mirror surface by flipping open the pivoting lid when positioned in a passenger seat within an aircraft. A retractor may be configured to closing of the pivoting lid when a passenger manually translates the tray table into a stowed position, thereby avoiding contact of the deployed lid with aircraft fixture surfaces proximate the stowed position of the tray table.

Abstract: A brush wear indicating arrangement is provided. The brush wear indicating arrangement includes an insert, a first electrically conductive brush, and a wear indicator. The insert is disposed within a brush block housing and defines a first aperture. The first electrically conductive brush is movably engaged within the first aperture. The electrically conductive brush is configured to move outward from the first aperture as a wear surface of the first electrically conductive brush wears. The wear indicator is coupled to the first electrically conductive brush. The wear indicator is configured to extend beyond a first insert face of the insert as wear condition of the wear surface of the first electrically conductive brush exceeds a wear threshold.

Abstract: It is described a movable pylon, associated with a lower portion of aircraft wing and with an aircraft engine to change the height of this engine between a flying position and a ground position, the movable pylon comprising: a main unique structure formed by a first movable structure pivoted to a second fixed structure, the first movable structure associated with the engine, the second fixed structure associated with the wing, and a pivot mechanism connecting the first movable structure to at least one point on the wing.

Abstract: Methods and related apparatus for improving synchronization of two or more engines on an aircraft are disclosed. Such method may be used where each engine comprises a first spool and a second spool, and, where a rotational speed of a first spool of a first engine has been substantially synchronized with a rotational speed of a first spool of a second engine. An exemplary method comprises receiving a value of a sensed parameter useful in controlling the first engine; adding a bias to the value; and using the biased value for controlling the first engine to cause a change in rotational speed of the second spool of the first engine in relation to the rotational speed of the first spool of the first engine.

Abstract: An aircraft fuel system includes one or more fuel cells adapted to contain fuel, a fuel cell receiving assembly having an inner surface adapted to receive the one or more fuel cells and a fuel cell cushion disposed between the inner surface of the fuel cell receiving assembly and the one or more fuel cells. The fuel cell cushion is machined from a foam substrate to form a shaped foam substrate that is substantially covered with a cushion coating. The cushion coating is sprayable onto the shaped foam substrate such that the fuel cell cushion is substantially nonabsorbent of fuel. The fuel cell cushion is interposable between the inner surface of the fuel cell receiving assembly and the one or more fuel cells to cushion the one or more fuel cells from damage.

Abstract: A fuel tank system comprising a fuel tank, a number of fasteners, and a number of covers. The number of fasteners has a number of ends extending into an interior of the fuel tank. The number of covers is configured to cover the number of ends of the number of fasteners. A cover in the number of covers comprises a housing configured to cover an end of a fastener in the number of ends, a deformable material associated with an interior side of the cover, and cells that are present within the deformable material. The deformable material is configured to contain energy within the cover in which the energy is caused by an electromagnetic event.

Abstract: A purge system includes an airflow source to provide an airflow, and a fuel tank, including: a tank volume including a tank ullage, at least one inlet, wherein the at least one inlet is in fluid communication with the tank ullage and the airflow source to provide the airflow as an inbound airflow to the tank ullage, and at least one outlet, wherein the at least one outlet is in fluid communication with the tank ullage and an overboard location outside the aircraft to direct the inbound airflow as an outbound airflow from the tank ullage to the overboard location.

Abstract: A method and configuration to optimize an entire traction system available on a helicopter including an auxiliary engine by allowing the engine to provide non-propulsive and/or propulsive power during flight. The auxiliary engine is coupled to participate directly in providing mechanical or electrical propulsive power and electrical non-propulsive power to the aircraft. An architecture configuration includes an on-board power supply network, two main engines, and a system for converting mechanical energy into electrical energy between a main gearbox to the propulsion members and a mechanism receiving electrical energy including the on-board network and power electronics in conjunction with starters of the main engines. An auxiliary power engine provides electrical energy to the mechanism for receiving electrical energy via the energy conversion system and a mechanism for mechanical coupling between the auxiliary engine and at least one propulsion member.

Abstract: The invention relates to an assembly comprising a structure (2) and a tubular element (6), which is mounted isostatically in the structure (2), said tubular element (6) comprising a first end (7) connected to said structure by at least four connecting rods 10a-10b-10c-10d, thus setting four first degrees of freedom, and a second end (8) connected to said structure (2) by an attachment means (20) that sets two second degrees of freedom, said connecting rods comprising a means for adjusting the length thereof. In particular, it relates to an exhaust suitable for an auxiliary power unit in the compartment thereof and to the mounting method for aligning them.

Abstract: Embodiments of methods and apparatus for close formation flight are provided herein. In some embodiments, a method for establishing situational awareness during formation flight includes exchanging transponder signals between at least two aircraft, establishing two-way communication links between the at least two aircraft, exchanging telemetry data between the at least two aircraft, and assigning the roles of a leader and a follower to the aircraft.

Abstract: An aircraft includes a fuselage, each wing with a movable flap element arranged on the wing, having a sensor element providing a sensor signal corresponding to vibrations on the flap element, and being movable between a retracted and an extended positions, drive means having a movable driven output connected by an actuation assembly with each of the flap element and configured such that a movement of the output effects a movement of each of the flap element between the extended and retracted positions. A control unit is adapted to compare for each sensor element during operation of an excitation means the amplitude of the vibrations in the frequency interval detected by that sensor element with a predetermined threshold of that sensor element and to provide a failure signal when for at least one sensor signal the amplitude is below the threshold of that at least one sensor signal.

Abstract: The present application relates to a static discharger and an aircraft including the static discharger. According to an aspect of the present application, a static discharger is provided which includes: a basement; and a discharger body adapted to be installed to the basement. The static discharger further includes a first fixing mechanism adapted to fix the discharger body to the basement. A pivoting mechanism is provided between the basement and the discharger body, the pivoting mechanism allowing the discharger body to pivot with respect to the basement so as to adjust an installation orientation of the discharger body with respect to the basement during an on-site-installation of the static discharger. According to the present application, for example, installation adaptation and universality of the static discharger can be improved.

Abstract: A dual mode light assembly for a forward position light of an aircraft includes a base, a visible light source mounted to the base that is configured to emit visible light, a covert light source mounted to the base that is configured to emit covert light, and a light shield mounted to the base. The light shield is configured to restrict transmission of the visible light to a visible light pattern and to restrict transmission of the covert light to a covert light pattern.

Abstract: Systems and methods for tracking moving objects in accordance with embodiments of the invention are disclosed. In one embodiment of the invention, an object tracking system comprises a processor, a communications interface, and a memory configured to store an object tracking application. The object tracking application configures the processor to receive a sequence of images; estimate and subtract background pixel values from pixels in a sequence of images; compute sets of summed intensity values for different per frame pixel offsets from a sequence of images; identify summed intensity values from a set of summed intensity values exceeding a threshold; cluster identified summed intensity values exceeding the threshold corresponding to single moving objects; and identify a location of at least one moving object in an image based on at least one summed intensity value cluster.

Abstract: A system for verifying an aircraft instrumentation value comprising: an Air Data Test Module (ADTM) configured to pneumatically simulate at least one instrumentation value based upon a pressure set-point. The pneumatically simulated instrumentation value corresponds to the pressure set point and is reported by an aircraft transponder. A receiver module receives the pneumatically simulated instrumentation value transmitted by the aircraft transponder. A signal processor, is operative to (i) control the ADTM, (ii) command a prescribed instrumentation value to be simulated by the ADTM, (iii) compare the prescribed instrumentation value to the pneumatically simulated instrumentation value, and (iv) issue a pass signal when the values match, and a fail signal when the values differ by a threshold value.

Abstract: A conical scanning method and system is provided for orienting a spacecraft with respect to a source. The system includes a spacecraft and an incidence angle sensor secured to the spacecraft to sense a signal from a source. The incidence angle sensor has a boresight that is canted with respect to the principal axis. A processor communicates with actuators on the spacecraft to adjust an attitude of the spacecraft based on information received from the incidence angle sensor and to thereby align a principal axis of the spacecraft with a direction from the spacecraft to the source. The method and system can also rely on information received from source presence sensors. The source may be the Sun, or a non-solar signal source.

Abstract: A packaging system for packaging a product into a plurality of bags or sacks includes at least one of a bagging unit, a pallet loading device, and a pallet securing device. The system also includes a device for storing and rendering available information regarding events that occurred in the system during the packaging.

Abstract: A packaging unit for packaging a product includes at least one of a bagging unit, a pallet loading device, and a pallet securing device. Also included is a device to provide information regarding the packaging unit, the packaging, and/or the product, allowing the information to be displayed with at least one terminal outside the device.

Abstract: A package for an item is disclosed. The package includes an outer box and a first insert panel. The outer box includes a base panel and a first flap extending from the base panel. The first flap is configured to open and close the package. The first insert panel is disposed within the outer box. The first insert panel has a first end attached to the first flap and a second end disposed over the base panel. The first insert panel is configured to support an item within the package. The first insert panel is configured to move relative to the base panel when the first flap is opened. The first insert panel is configured to keep the first flap in an open position by friction between the first insert panel and the base panel.

Abstract: A method and apparatus for vacuum packaging a product. According to one embodiment a film tube is generated, and, in the film tube a product (P) is introduced and at least one cut is made. In the method, a vacuum may also applied inside the film tube, and a transverse seal is formed therein, a film tube closed at one end being obtained upstream of the cut and a package closed at both ends being obtained downstream. Furthermore, the film tube is transversely pinched, a portion the inside of the film tube which is isolated from the inside of the rest of the film tube being obtained, and a chamber is demarcated around at least part of said portion, the vacuum being applied and the transverse sealing operation being performed inside said chamber.

Abstract: A cap for a cup includes a piston seat which includes a room, and an aperture is defined through the lower end of the piston seat. An air path communicates with the aperture. A check valve is movably engaged with the lower end of the piston seat and includes a plate which is deformable to control the air path to be opened or closed. A suction device is located in the piston seat and includes a position rod whose lower end is connected to a piston head which is located in the room of the piston seat. The upper end of the piston rod protrudes beyond the top end of the piston seat and is connected to a handle. By pulling and pushing the handle, the air in the cup is sucked out.

Abstract: A packaging assembly (10) including a weighing machine (11) that includes buckets (12, 13) to provide batches of product to be delivered to a former (41), with the former (41) delivering tubular bag material with product to a packaging machine (18). The tubular bag material is delivered to the packaging machine (18) by means of a film drive assembly (17).

Abstract: There is described a shutter for a valve for controlling an air flow; shutter is selectively rotatable about an axis and adapted to be housed inside a body of valve, and comprises a surface disposed about axis; surface comprises at least one first curved portion shaped eccentrically relative to axis so as to define, in use and together with body, at least one first passage for the air flow.

Abstract: Provided is a method and apparatus for applying a bail handle to a container. The applicator includes a pickup mandrel for picking up the bail handle to be applied to a container; a stationary mandrel for receiving the bail handle from the pickup mandrel, the stationary mandrel having an engaging surface which has a diameter larger than an inner diameter of the bail handle when picked up by the pickup mandrel; and an applicator mandrel for receiving the bail handle from the pickup mandrel, the applicator mandrel having an engaging surface which has a diameter equal to or smaller than the stationary mandrel.

Abstract: The present disclosure relates to methods and systems for processing isolated mammalian tissue for use in surgical grafting, implantation, or transplantation procedures. The method employs electron beam sterilization, the collagen tissue is partially submerged in rHSA (Recombinant Human Serum Albumin), the tissue is stored in specially designed packaging, and the tissue is stored at ambient temperatures without requiring refrigeration. The terminal sterilization using electronic beams takes place in the special packaging. This inventive technology offers advantages including being biologically safe, maintaining tissue integrity while minimizing size, increasing scalability, increasing shelf life, increasing the amount of tissue usable for transplantation, and reducing of costs associated with processing and storing tissue for long periods of time.

Abstract: The present disclosure provides an automatic labeling apparatus and method, as well as an assembly jig and method, the automatic labeling apparatus includes an attachment platform provided with an attachment surface, an attachment unit provided with a label receiving surface, and a separation unit, wherein the separation unit is configured to separate a label from a label base paper to the label receiving surface with a glue surface of the label away from the label receiving surface, the label receiving surface being configured to make the glue surface of the label higher than the attachment surface when the label is on the label receiving surface.

Abstract: A drink container has multiple integrated storage compartments removably secured below an openable chamber configured to receive contents for consumption by a user of the drink container. A top assembly covers the chamber and includes a removable top member, an openable cap and a clip. The drink container also includes a first retaining member and a displaceable base with a second retaining member and an internal storage compartment. In an assembled state, the first and second retaining members secure the storage compartment in an intermediate cavity below the chamber. The storage compartment is separated from the cavity by applying a radially outward disconnection force on the compartment. Once disconnected, the integrated storage compartments can be filled within contents, or the contents of the integrated storage compartments can be added to the chamber for consumption by the user or directly consumed by the user.