Abstract: A flow guide body for an aircraft includes a main body having an outer aerodynamic surface having a plurality of outlet openings, and flow control devices, each having an inlet, an interaction chamber, a first outlet and a second outlet. A first control inlet is connected to the interaction chamber at the first side of the chamber axis. The outlets are each connected to outlet openings in the aerodynamic surface. Each outlet has a control outlet. A second flow control device is arranged such that one outlet is connected with the inlet of the first flow control device. One of the control outlets of the first flow control device is connected to the first control inlet of the first flow control device, and the other of the control outlets of the first flow control device is connected to the first control inlet of the second flow control device.

Abstract: A nacelle defining an intake is provided for channelling and conditioning freestream airflow to a fan of a ducted fan gas turbine engine. The nacelle intake comprises in flow series an intake lip, and a diffuser. The intake lip has at its forwardmost end a highlight which is a closed loop defining a boundary between inner and outer surfaces of the nacelle, and the diffuser terminates at its rearwardmost end at a front face of the fan. The intake has a circumferentially extending shock control bump or a series of circumferentially spaced shock control bumps formed thereon.

Abstract: An electrically powered STOL aircraft having dedicated motors energized to deploy movable landing gear driven to propel short takeoffs and to actively rotate downwardly to engage the runway surface as the aircraft approaches touchdown on landing. The front and rear landing gear, or both, may be powered and actuated in the landing process with braking to shorten the landing distance, each driven landing gear wheel having a dedicated electric motor and coaxial brake. The landing gear modules are configured and controllable to differentially deploy downwardly so as to enable countersteering during taxi maneuvers and turns.

Abstract: In some examples, an assembly includes a vehicle wheel that defines an interior and an exterior surface, where the interior surface defines a first protrusion and a second protrusion. The first protrusion defines a first aperture extending in a substantially axial direction. The assembly further includes a rotor drive key on the interior surface, the drive key defining a first and second feature, and the first feature defines a second aperture extending in the substantially axial direction and is configured to align with the first aperture. The assembly includes a fastener configured to be inserted through the first and second aperture in the substantially axial direction to attach the key to the interior surface of the wheel, where the second aperture is configured to form a threaded connection with an end of the fastener. When the fastener is tightened via the threaded connection, the second feature engages the second protrusion.

Abstract: Methods and apparatus to recover rotorcraft are disclosed. A disclosed example apparatus includes a rotor of a vehicle, a rotatable hub to support the rotor, and a rotor hook disposed on the rotor. The rotor hook has a groove to receive a recovery line. The rotor is to contact the recovery line when the vehicle is flown toward the recovery line.

Abstract: An inner middle rotor is rotated while an inner front rotor, an inner back rotor, and an outer rotor are not rotated. The inner middle rotor is surrounded by the inner front rotor, the inner back rotor, the outer rotor, and a fuselage. After rotating the inner middle rotor while not rotating the inner front rotor, the inner back rotor, and the outer rotor, the inner middle rotor, the inner front rotor, the inner back rotor, and the outer rotor are simultaneously rotated.

Abstract: A propulsion assembly for a rotorcraft includes a mast including a distal ridge and a proximal ridge forming a retaining pocket therebetween, a raceway receivable by the retaining pocket to form a press fit between the mast and the raceway and a mast bearing assembly including a plurality of bearings facing the mast to engage the raceway. The distal and proximal ridges are operable to reduce axial motion of the raceway along the mast, thereby securing the raceway in the retaining pocket.

Abstract: An embodiment includes a system for controlling blade pitch in a rotorcraft having an engine; a drive shaft with a first end and a second end and connected at the first end to the engine; a rotor with two or more blades connected to the second end of the drive shaft; and one or more actuators positioned adjacent to the rotor blades operable to change a blade pitch of the rotor blades.

Abstract: The present invention is a companion unit and companion system. The companion unit comprises an UAV that further comprises one or more of the following elements: propulsion units, circuit boards, navigation sensors, cameras, speakers, microphones, chassis, processors, and batteries. The companion system comprises one or more bases wirelessly connected to the companion unit and in possibly to one or more computer devices and/or to the Internet. The elements thereby facilitate one or more of the following Internet connectivity, wireless local area network (WiFi) connectivity, computer device connectivity (e.g. connectivity to a cell phone, a smart phone, a laptop, a tablet, a smart television, a WiFi enabled appliance, or any other computer device), base connectivity, and cloud storage connectivity. The companion system and/or the companion unit is connected to an artificial intelligence module. The companion unit and system are programmed to function as a companion to a human user.

Abstract: Systems and methods for countering an unmanned air vehicle are disclosed. An example method includes detecting a target UAV via a first component of a target acquisition system. The example method further includes, in response to detecting the target UAV, directing, by executing one or more computer-readable instructions of a launch control system in communication with the target acquisition system, an interceptor UAV to launch. The example method further includes, subsequent to the launch, tracking the target UAV via a second component of the target acquisition system, the second component carried by the interceptor UAV. The example method further includes, when the target UAV is within a target range of the interceptor UAV, deploying a disabling element from the interceptor UAV toward the target UAV.

Abstract: Provided are embodiments that include techniques for a wireless portable cargo control panel with physical controls. The techniques include a portable electronic device (PED) including a display, the PED configured to communicate with a master control panel (MCP) that controls a cargo handling system and a portable control panel (PCP). The PCP includes an interface configured to couple the PED, one or more dedicated physical input selection devices, a directional controller, and one or more orientation indicator displays, wherein each of the one or more orientation indicator displays are configured to be updated based at least in part on orientation information associated with the cargo handling system, PCP, and PED.

Abstract: A storage bin assembly includes a fixed bin portion, an articulating bin portion, and an articulation system. The fixed bin portion is configured to be mounted to an aircraft, and has a cavity configured for storage of luggage. The articulating bin portion is coupled to the fixed bin portion, and includes a shelf configured for supporting luggage. The articulation system movably couples the articulating bin portion to the fixed bin portion. The articulating bin portion is movable from a first position in which the articulating bin portion is proximate to the fixed bin portion to a second position at which the articulating bin portion is separated from the fixed bin portion and lower than the fixed bin portion.

Abstract: In a lavatory arrangement comprising a vacuum flushing system, the lavatory arrangement comprises a folding toilet bowl.

Abstract: A life vest stowage device comprises a receptacle with a receptacle opening. The device has first and second tabs with first and second tab apertures. In a closed configuration, a closure flap is in a folded position in which it at least partially covers the opening. The first and second tabs are exposed through the closure flap to allow access to the tab apertures from an outer side of the closure flap. A pull strap extends from the interior volume through the opening and over the outer side of the closure flap. The pull strap has a pull strap aperture securable to the first and second tab apertures by a frangible seal, such that the closure flap can only be moved to an unfolded position by moving the pull strap aperture and the first and second tab apertures away from one another so as to break the frangible seal.

Abstract: An avionics unit assembly for an aircraft can include an avionics unit (e.g., an underwater locator device, “ULD”), and a battery to power the avionics unit. The avionics unit assembly can further include a housing that encases the avionics unit and the battery. The housing includes a vent port for exhausting an emission from the housing during a failure of the avionics unit. The avionics unit assembly can further include one or more of a suppressor that filters the emission, a shield element that is resistant to chemical and/or thermal effects of the emission, and a bracket for mounting the avionics unit to a surface. A method integrating the avionics unit assembly onto a forward aircraft bulkhead at a mount location under an aircraft radome and for manufacturing the avionics unit, and an aircraft including the avionics unit are also described.

Abstract: A joint for connecting a first aircraft structure to a second aircraft structure such that relative rotation and relative translational movement of the first and second aircraft structures along a first axis is permitted, whilst relative translational movement of the first and second aircraft structures along axes orthogonal to the first axis is substantially prevented. The joint includes a bracket having an opening aligned with the first axis; a pin aligned with the first axis and extending through the opening; and a bearing mounted in the opening. The bearing has an inner bearing surface defining a bore through which the pin extends, which is configured for translational sliding contact with the pin, and a part-spherical outer bearing surface configured for rotational sliding contact with the opening.

Abstract: An active laminar flow control arrangement may comprise a modular arrangement comprising a plurality of frames and cover panels coupled to an outer skin having a plurality of hat stiffeners and stringers. A first cover panel may be coupled between a first frame and a first hat stiffener. A second cover panel may be coupled between a second frame and a second hat stiffener. A third cover panel may be coupled between the first cover panel and the second cover panel. The cover panels may enclose associated plenums whereby a flow of air is pumped into the arrangement for maintaining a laminar flow across an aerodynamic surface of the outer skin.

Abstract: An active laminar flow control arrangement may comprise an outer skin having an inner surface, an outer surface, and a perforated area, and a panel coupled to the inner surface. The panel may comprise a longitudinal wall, a sidewall extending from the longitudinal wall, a ridge intersecting the sidewall, a cavity disposed in the panel and at least partially defined by the sidewall and the longitudinal wall, and a division wall disposed in the cavity and extending from the longitudinal wall, wherein the division wall divides the cavity into a first plenum and a second plenum. The longitudinal wall, the sidewall, the ridge, and the division wall may comprise a single, monolithic piece.

Abstract: A panel for an active laminar flow control arrangement may comprise a longitudinal wall and one or more division walls extending from the longitudinal wall and extending between the first end and the second end. The panel may be coupled to a nacelle outer skin via a plurality of adhesive fasteners pre-installed onto an inner surface of the outer skin and onto stiffeners and/or stringers associated with the outer skin.

Abstract: A device for an aircraft powerplant de-icing system making it possible to reduce or eliminate a tonal noise generated by a flow of air along a surface having an orifice opening into a cavity extending on the side opposite this surface, the orifice having a downstream edge relative to the direction of flow of the air, includes a deflector positioned next to the downstream edge, extending towards the inside of the cavity, and oriented perpendicularly to the direction of flow of the air to divert towards the outside of the orifice vortices formed in the shear layer due to the flow of the air along the surface over each orifice. The deflector at the downstream edge of each exhaust orifice of the de-icing system makes it possible to redirect the vortices outside the cavity while preventing them from being greatly deformed when they pass over the downstream edge.

Abstract: A method and device for protecting an adjacent rupturable component including positioning a sheet of puncture resistant, flexible material including one or more openings at or about the structure opening wherein the one or more openings accommodate the rupturable component; permanently or semi-permanently attaching the sheet to the structure at a first portion of an area of the sheet; and positioning the rupturable component through the one or more openings, such that one or more portions of the rupturable component near the one or more openings are protected by the sheet if the structure becomes frayed; wherein the sheet prevents damage to the rupturable component if the structure frays or fractures at or about the structure opening.

Abstract: A system and method for providing dried inert gas to a protected space is disclosed.

Abstract: Cable retainer apparatuses for retaining a cable, and aircraft and methods including such apparatuses are provided. In one example, a cable retainer for retaining a cable proximate a surface of an aircraft includes a cable retainer. The cable retainer is configured to retain the cable. A fairing is disposed about the cable retainer and is configured to couple to the aircraft to support the cable retainer adjacent to the surface of the aircraft.

Abstract: Provided is an abnormality detection device for a rotary wing unit. The rotary wing unit includes a plurality of rotary wings that is coaxially disposed. The abnormality detection device includes a controller configured to acquire at least one of a correlation at the time of normal operation between operation parameters related to the rotary wings and a correlation at the time of abnormal operation between the operation parameters and detect abnormality of the rotary wing unit, based on a correlation at the time of actual operation between the operation parameters and at least one of the correlation at the time of normal operation and the correlation at the time of abnormal operation.

Abstract: A washer assembly including a metallic washer and a polymer seal. The metallic washer defines a cylindrical void and an axis therethrough. The polymer seal is attached to the metallic washer and is positioned radially inward thereof. The polymer seal includes a lower seal portion positioned at least partially within the cylindrical void and defining a counter-bore, and an upper seal portion extending axially from the lower seal portion. The lower seal portion is configured to engage, at the counter-bore, a fastener to form a seal to reduce escape of energized particles. The upper seal portion is configured to engage a counter-bore of a counter-bored nut to form a seal inside the counter-bored nut to reduce escape of energized particles.

Abstract: A method of protecting an air vehicle against lightning strikes includes inserting a fastener through a hole in conjoined structures, the fastener defining an axis along its length and having a threaded end and a sleeve, and installing a washer assembly over the threaded end and the sleeve, the washer assembly having a metallic washer and a polymer seal radially inward of the metallic washer. The seal includes a lower seal portion defining a counter-bore, and an upper seal portion extending axially from the lower seal portion. The method includes installing a counter-bored nut on the threaded end, and applying torque to the nut to compress the lower seal portion against a surface of the conjoined structures and around the sleeve at the counter-bore of the seal, and to compress the upper seal portion of the seal into a counter-bore of the nut and around the threaded end.

Abstract: An aircraft lighting system includes a light unit configured to emit light, a portable measurement device, and a control unit. The portable measurement device is configured to measure at least one attribute of the light emitted from the light unit and output the measured attribute of the light in an output signal. The control unit is configured to receive the output signal and control the light unit based on the measured attribute. In some aspects, the light unit is positionable in an aircraft, in certain examples, a method of controlling a lighting system includes measuring at least one attribute of light of a light unit with a portable measurement device, transmitting the measured attribute to a control unit, and controlling the light unit based on the measured attribute. In some cases, the method includes measuring the at least one attribute of a light unit in an aircraft.

Abstract: A method for deploying a drone including transporting a drone from a first location to a second location with a vehicle and supplying electricity from the vehicle to the drone while the drone is being transported. A launch command can be initiated from within the vehicle to direct the drone to ascend and hover above the vehicle. The drone can be transported in a drone port mounted to the vehicle.

Abstract: A modular staircase is disclosed. The modular staircase includes a first staircase section having a plurality of steps and a first support member detachably connected to the first staircase section. Further, the modular staircase includes a second stair module having a second staircase section including a plurality of steps and a second support member detachably connected to the second staircase section and to the first support member. The modular staircase further includes a third stair module having a third staircase section including a plurality of steps and a retractable third support member detachably connected to the third staircase section and to the second support member. The third support member may be configured to raise or lower the third staircase section relative to the second staircase section.

Abstract: A device that provides conditioned air to an aircraft may include a housing with a housing outlet end, a longitudinally collapsible hose that has a hose outlet for attachment to the aircraft and is partially received within the housing, a hose drive for extracting and retracting the hose by selectively pushing the hose in an outward or inwards directions, a drive control for controlling the hose drive, an outward marker attached to the hose, and a sensor for detecting the presence of the outward marker. The hose may have an extracted length that is at least twice a length of the housing. The hose may pass through the housing outlet end. The drive control may be adapted to respond to signals from the sensor to control the hose drive. Further, the marker may be adapted to provide a magnetic signal or a radio signal for detection by the sensor.

Abstract: A method is for detecting a blockage of a wind vane (12) of an aircraft, with the wind vane (12) including a support (20), a paddle (22) mounted rotating relative to the support (20) along an axis (A), a motor (28) able to exert a rotational torque on the paddle (22) along the axis (A), the motor (28) being connected to a processing unit (18). The method includes applying a predetermined blockage detection torque on the paddle (22) by the motor (28); measuring at least one piece of information representative of a resistance of the paddle (22) to the predetermined detection torque; and generating, via the processing unit (18), a blocking information signal, if a predetermined condition based on the representative information is verified.

Abstract: A method of adjusting an interior component to be received in a fuselage of an assembled aircraft, including determining a deformed configuration of a fuselage portion of a test rig, the fuselage portion in the deformed configuration being bent along its longitudinal axis and being representative of at least part of the fuselage of the assembled aircraft, deforming the fuselage portion to the deformed configuration so that the fuselage portion maintains the deformed configuration in a rigid manner, installing the interior component within the fuselage portion in the deformed configuration, determining changes required in a nominal configuration of the interior component based on a fit of the interior component within the fuselage portion in the deformed configuration, and applying the required changes to the nominal configuration of the interior component before installing the interior component within the fuselage of the assembled aircraft. A test rig is also discussed.

Abstract: A method of supplying a receiving tank of a receiving spacecraft with a supply gas. The method includes coupling a second end of a transfer line in flow communication with the receiving tank. The transfer line extends from a first end to the second end. The first end is coupled to a transfer tank disposed on a supply spacecraft. The transfer tank holds a transfer quantity of the supply gas. The supply spacecraft includes a heating system coupled in thermal communication with the transfer tank and a transfer valve operatively coupled to the transfer line. The method also includes activating the heating system while the transfer valve is closed such that a pressure of the transfer quantity of the supply gas is increased.

Abstract: A stackable pancake satellite that is configured so that a plurality of the satellites can be stacked within a payload fairing of a launch vehicle. Each satellite includes sections that are folded or rotated together prior to launch, and unfolded or rotated away from each other when deployed. A first section is a satellite body having a first side that acts as a thermal radiator and a second side opposite the first side that includes an antenna. A second section includes one or more solar panels attached adjacent to the first side of the satellite body. A third section includes a splash plate reflector attached adjacent to the second side of the satellite body that reflects signals between Earth and the antenna. When deployed, the solar panels are pointed towards the Sun and the splash plate reflector directs the signals between the Earth and the antenna.

Abstract: Spacecraft thruster systems are disclosed. In some instances, a spacecraft thruster system may include stacked ion thrusters and/or ion thruster layers. The ion thrusters and/or ion thruster layers may be sequentially activated and jettisoned from the thruster system after use.

Abstract: A fuel cell-based power system comprises a fuel cell configured for continuously receiving a first reactant and a second reactant to produce chemical reactions that generate electrical power, water, and heat, a coolant subsystem configured for circulating a primary coolant in association with the fuel cell, thereby absorbing the generated heat, a tank configured for storing a reactant, and a reactant distribution subsystem configured for conveying the reactant from the tank to an independent system, the fuel cell as the first reactant, and the coolant subsystem as a secondary coolant to remove the absorbed heat from the primary coolant and/or a water accumulator. The secondary coolant may be conveyed to a gas thruster as a gas after the absorbed heat has been removed from the secondary coolant. The reactant may boil off of a cryogenic liquid or vapor or gas transformed from a cryogenic liquid via a heater.

Abstract: A spacecraft docking system and method thereof are provided. The system comprises an active docking device and a passive docking device. The active docking device comprises an active docking ring and a docking frame. The active docking device further comprises three sets of buffer mechanisms, each set of the buffer mechanisms comprises a main buffer, two screw nut assemblies, and a self-difference buffer. An upper end and a lower end of the screw nut assembly are movably connected to the active docking ring and the docking frame, respectively. The two screw nut assemblies in each set are simultaneously driven and stretched by the main buffer, being also connected to each other through the self-difference buffer, and able to be relatively adjusted and stretched through the self-difference buffer.

Abstract: This invention discloses a process for forming a pouch having an evacuated headspace containing a flowable material. The process relates to optimizing both, the evacuation of the headspace in the pouch and the accuracy of the flowable material filled in the pouch. Specifically, the present invention employs a process that includes a multiple-step or a continuous compression of the pouch headspace to accomplish the goals. Also disclosed is a vertical form-fill-seal apparatus for forming a pouch containing a flowable material and having an evacuated headspace.

Abstract: The present invention relates to an automatic tying machine for automatically tying binding wires in order to fix crops in a farmhouse or tie bundles or bundled products during distribution. More specifically, the present invention relates to an automatic tying machine which can use binding wires of different thicknesses, in which after a binding wire is drawn into a slot of a whirling binding wire guide device, the binding wire does not slip off from the slot during rotation of a slewing gear to prevent malfunctioning of the automatic tying machine for crops, such that it is possible to accurately and quickly tie crops, bundles or bundled products. Due to these features, the automatic tying machine has remarkable effects that can improve the productivity of work of tying crops, bundles or bundled products and improve work convenience.

Abstract: A handheld tool for installing wire on a fence, the tool having a frame, a sprocket system that is situated at least partially within the frame and engaged by an actuator, a T-post alignment unit that is configured to position a vertical T-post against the tool, a clip storage magazine that is attached to a top of the frame, a tube assembly that is movably mounted within the frame, and a presenter that is configured to present clips from the magazine. The sprocket system and tube assembly are configured to cause the clip presented by the presenter to be pushed into position against the T-post and a horizontal fence wire, tension the fence wire against the T-post, lock the fence wire into position against the T-post by straddling the T-post with the clip, and wrap two ends of the clip around the fence wire to attach it to the T-post.

Abstract: A packaging device (1) for packaging substantially round articles into a dimpled package (100) having an array of pockets to receive the round articles. The packaging device comprising a supply conveyor (2) for the articles and a package conveyor (15) located below the supply conveyor for conveying the packages. A filling buffer (4) is located between the supply conveyor and the package conveyor having multiple sub-buffers (5). The device furthermore comprises a collector (8) for receiving articles from the buffer, and a setter (12) wherein, in use, the setter reciprocates between an upper position to a lower position, wherein in the upper position the articles can be received from the collector and in the lower position the articles can be discharged into the pockets of the package.

Abstract: The invention discloses an automatic canning device for canned food, which includes a machine body. The weighing device includes a rotation shaft that is rotatably installed on the front and rear side walls of the transportation cavity. A large gear is fixed on the rotation shaft. The rear side wall of the transport chamber is provided with a long plate chute. The bottom side of the long plate chute is provided with a hydraulic pipeline. The power motor is turned on, thereby driving the large gear, pinion, and symmetrical pulley to rotate. The device can add jam to the glass jar through a mechanical structure. Compared to manually adding jam, the content of jam added by the device can be kept consistent, so that the product Standardization can be guaranteed, and the device can automatically seal glass bottles and then tighten them.

Abstract: Packaging apparatuses for loading and sealing products into a web of interconnected bags, and methods of using them, are provided. In one aspect, the packaging apparatus includes an intermittently advancing web conveyor that also indexes vertically to facilitate stacked loading of products into the bags. In another aspect, the packaging apparatus includes a dividing seal station that applies a center seal dividing the bag into separate sealed subcompartments, some of the bag contents being distributed to each compartment, such as one of two trays to each subcompartment. To facilitate distribution of contents and even sealing, the dividing seal station may include a dividing sealer lower support that oscillates vertically to promote settling of contents and gases in the bag before applying a dividing seal.

Abstract: An apparatus to facilitate bagging of a bag, the apparatus including an upper ring having a first circumference, the upper ring being disposed parallel to a ground surface, a center ring having a second circumference, the center ring being disposed below the upper ring, and a plurality of legs extending from a bottom surface of the upper ring towards the ground surface such that each of the plurality of legs contacts an inner circumferential surface of the center ring and a bottom surface of each of the plurality of legs contacts the ground surface.

Abstract: A deep-drawn tray, in particular an aluminum tray, having a rolled edge and an encircling sealing face, by means of which it can be sealed to a plate. In order to provide readily visible markings or to improve the appearance, the rolled edge of the tray is provided with a lacquer.

Abstract: A cup is disclosed which may form its own closure. The cup is formed to define two flaps which may be folded inward to cover the cup opening. The flaps define a first drinking spout and a second vent spout to allow air to enter as fluid is removed. The present cup allows for a disposable cup to be formed of a single material without the need for a separate cover.

Abstract: A carton for holding one or more articles, the carton including a plurality of panels extending at least partially around an interior of the carton and at least partially forming a body portion of the carton, a plurality of impact-resistant panels foldably connected to a respective panel of the plurality of panels, and a plurality of end flaps for forming a closed end of the carton. The plurality of end flaps includes a first end flap foldably connected to an impact-resistant panel of the plurality of impact-resistant panels and a second end flap foldably connected to a panel of the plurality of panels, a lateral edge of the second end flap is a folding edge about which the first end flap is folded to at least partially form the closed end.

Abstract: A child-resistant container includes an outer housing defining a cavity and an inner receptacle configured to be slidably received in the cavity of the outer housing and move between a closed position and an open position.

Abstract: A paper inner container for storage of a refilling liquid content, the paper inner container including a body (11), which includes a body front panel (7), a body right side panel (6), a body left side panel (8), and a body back panel (5). A top surface (12) includes: a top surface forming panel (14) which is continuously provided on an upper edge of the body back panel; a top surface formation assisting panel (16), which is continuously provided on an upper edge of the body front panel, and is folded up on a lower side of the top surface forming panel; and right and left side panels (19, 20), which are continuously provided on upper edges of the body right side panel and the body left side panel, and are folded up along with overlapping of the top surface forming panel and the top surface formation assisting panel.

Abstract: A blank includes a top, the top connected to a first top side tab, a second top side tab, a top front tab, and a back tab; a bottom, the bottom defining at least one connection aperture, the bottom connected to a first bottom side tab, a second bottom side tab, a bottom front tab, and the back tab; the first bottom side tab connected to a first cover tab, the first cover tab connected to a first connection tab; the second bottom side tab connected to a second cover tab, the second over tab connected to a second connection tab; the blank formable into a box by connection of the first connection tab to at least one connection aperture and by connection of the second connection tab to at least one connection aperture.