Abstract: A flow body for an aircraft includes a recess in a surface of the flow body, a first structural component with a porous material and may also include a second structural component with a porous material. The recess includes a front recess region and a rear recess region. The first structural component is arranged in, or on, the front recess region and the second structural component may be arranged in, or on, the rear recess region. An aircraft having the flow body, a weapons system having the flow body and a method for manufacturing a flow body for a vehicle are also described.

Abstract: Provided is a G tolerance improvement device provided with: an estimation unit that estimates either or both of a body fluid volume in the head of a user and a change amount of the body fluid volume; and a pressurization unit that applies pressure to the user on the basis of either or both of the body fluid volume and the change amount estimated by the estimation unit.

Abstract: A method and apparatus for providing an occupant tracking lighting system including a first light, a second light and a third light within an aircraft cabin including detecting, by a sensor, a location and a velocity of a moving occupant, generating, by a processor, a control signal to illuminate the first light and the second light in response to determining that the location is proximate to the first location and that the velocity being towards the second location, and illuminating, by a controller, the first light and the second light in response to the control signal.

Abstract: A waste compartment system for an aircraft can include a motor operated door and a proximity sensor configured to sense an object near the door or approaching the door. The system can include a control module operatively connected to the proximity sensor and configured to open the door in response to the proximity sensor sensing an object near the door. The control module can be configured to close the door after a preset time after the proximity sensor senses an object.

Abstract: A seat assembly includes a backrest that is configured to recline over a reclination range, and a variable reclination range limiter that is configured to selectively adjust a limit of the reclination range limit. A variable reclination range limiting method for a seat assembly includes allowing a backrest of the seat assembly to recline over a reclination range, and selectively adjusting a limit of the reclination range by a variable reclination range limiter.

Abstract: A method for depressurizing a cabin of an aircraft on the ground from the outer side of the aircraft using a depressurizing system including a venting valve which can be actuated between open and closed positions by means of a shutter and which is connected in fluid terms to a vacuum pump and to a pressure tap port of the aircraft which is connected to a protection valve against excess pressure in the cabin. The method includes fluidly connecting the venting valve to the pressure tap port, the shutter being in the open position, moving the shutter to the closed position thereof and activating the vacuum pump to generate a reduced pressure in the region of the pressure tap port.

Abstract: Disclosed is an air intake of an aircraft turbine engine nacelle having a lip, a downstream portion and an internal partition separating the lip and the downstream portion, the lip delimiting an annular recess, the downstream portion having a downstream inner wall and a downstream outer wall, the air intake having an injection channel for injecting a hot air stream into the annular recess, a passage opening formed in the internal partition, an outlet opening formed in the downstream outer wall and a discharge channel for discharging the hot air stream mounted in the downstream portion and having a first end connected to the internal partition, a second end connected to the downstream outer wall and a main body having at least one flexible portion.

Abstract: An air data probe includes a probe head having an interior surface defining a cavity, a component positioned within the cavity of the probe head, a plurality of protrusions defining contact between the interior surface of the probe head and a peripheral surface of the component prior to brazing the component to the probe head, and a braze material located between the interior surface of the probe head and the peripheral surface of the component as a result of brazing the component to the probe head.

Abstract: An example hybrid aircraft propulsion system includes one or more power units configured to output electrical energy onto one or more electrical busses; a plurality of propulsors; and a plurality of electrical machines, each respective electrical machine configured to drive a respective propulsor of the plurality of propulsors using electrical energy received from at least one of the one or more electrical busses.

Abstract: Aircraft power plants and associated methods are provided. A method for driving a load on an aircraft includes: transferring motive power from an internal combustion (IC) engine to the load; discharging a flow of first exhaust gas from the IC engine when transferring motive power from the IC engine to the load; receiving the flow of first exhaust gas from the IC engine into a combustor; mixing fuel with the first exhaust gas in the combustor and igniting the fuel to generate a flow of second exhaust gas; receiving the flow of second exhaust gas at a turbine and driving the turbine with the flow of second exhaust gas from the combustor; and transferring motive power from the turbine to the load.

Abstract: A fuel oxygen reduction unit assembly for a fuel system is provided. The fuel oxygen reduction unit assembly includes: a fuel oxygen reduction unit located downstream from the fuel source and defining a stripping gas flowpath and a liquid fuel flowpath, the fuel oxygen reduction unit comprising a means for transferring an amount of oxygen from a liquid fuel flow through the liquid fuel flowpath to a gas flow through the stripping gas flowpath; and an oxygen conversion unit in flow communication with the stripping gas flowpath configured to extract a flow of oxygen from a gas flow through the stripping gas flowpath, the oxygen conversion unit defining an oxygen outlet configured to provide the extracted flow of oxygen to an external system.

Abstract: An aircraft includes a fuselage carrying a nacelle of the aircraft offset relative to a wing of the aircraft. The nacelle forms an air inlet fairing of a propulsion assembly. The nacelle includes a lower wall and an upper wall delimiting together a height of the nacelle. The lower wall includes an air inlet edge being contiguous with a trailing edge of the wing.

Abstract: Systems, apparatuses, and methods for overcoming the disadvantages of current air transportation systems that might be used for regional travel by providing a more cost effective and convenient regional air transport system. In some embodiments, the inventive air transport system, operational methods, and associated aircraft include a highly efficient plug-in series hybrid-electric powertrain (specifically optimized for aircraft operating in regional ranges), a forward compatible, range-optimized aircraft design, enabling an earlier impact of electric-based air travel services as the overall transportation system and associated technologies are developed, and platforms for the semi-automated optimization and control of the powertrain, and for the semi-automated optimization of determining the flight path for a regional distance hybrid-electric aircraft flight.

Abstract: A propulsion system includes a system for producing electricity that supplies electricity to at least one electric motor to which is mechanically coupled a propeller situated near a first longitudinal end of a nacelle that houses at least the system for producing electricity and the at least one electric motor. An air circulation channel, which receives a heat exchanger provided to allow the system for producing electricity to be cooled, extends inside the nacelle from a first end of the air circulation channel situated at the first longitudinal end of the nacelle. A part of the air circulation channel that is contiguous with its first end is delimited by an outer surface of cylindrical shape that surrounds the longitudinal axis of the nacelle.

Abstract: An aerial vehicle adapted for vertical takeoff and landing using mounted thrust producing elements. An aerial vehicle which is adapted to vertical takeoff with the forward rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses one or more thrust producing elements on both of the right and the left sides. The aerial vehicle may have one or more front thrust producing elements and one or more rear thrust producing elements on both of the right and the left sides of a main vehicle body.

Abstract: An assembly of an electric propulsion system with power harvesting system and a method of manufacturing the electric propulsion system are disclosed. The electric propulsion system may include a propulsor configured to generate thrust. The electric propulsion system may include an electric motor configured to power the propulsor. The electric motor may include a stator configured to produce a magnetic field, wherein the stator may include a winding comprising an electrically conductive material. The electric motor may further include a rotor configured to be rotated by the magnetic field from the stator, wherein the rotor may include a coil attached to the rotor configured to induce an electric potential and an airgap between the stator and the coil.

Abstract: An electric motor nacelle for a vertical take-off and landing (VTOL) aircraft includes a fairing wherein an electric motor is housed equipped with at least one propeller extending outwards from a top face of the fairing, and a cooling device designed to cool the electric motor when the aircraft is in take-off, cruise and landing phases and including a reversible coolant fluid supply and exhaust manifold, designed, alternately: in the cruise phase, to receive a stream of cold fluid generated by the movement of the aircraft and to convey this stream of fluid, through the motor, towards an outlet situated opposite the propeller, and in take-off or landing phase, to receive a stream of hot fluid transmitted by the propeller and having passed through the motor.

Abstract: A latching system for releasably securing a first structure relative to a second structure. The latching system includes a latch assembly coupled to the first structure and a keeper assembly coupled to the second structure. The latch assembly is selectively engageable with the keeper assembly to hold the first structure against movement relative to the second structure.

Abstract: A floor system designed for use with an aircraft is provided. The aircraft comprises a cabin characterized by a first capacity defined by the number of personnel in a predetermined position which may be accommodated therein, and comprises an auxiliary fuel port. The floor system is configured to be detachably installed within the cabin and comprises one or more top panels constituting, when the floor system is installed in the aircraft, a floor of the cabin, and one or more fuel tanks disposed below the top panels and defining an internal space for containing liquid fuel there within. At least one of the fuel tanks is configured for connection to the auxiliary fuel port for supplying the fuel to the aircraft. The cabin with the floor system installed therein is characterized by a second capacity being equal to the first capacity.

Abstract: An air to air refueling system that monitors and adapts the movement at an end of an air to air refueling hose of a tanker aircraft to counteract undesirable movements at the end of the hose though generating aerodynamic loads in the end of the hose. The system includes grid fins at the end of the hose that are automatically rotated to counteract the undesirable movements.

Abstract: Disclosed are systems and methods for reconnectably coupling an aft vehicle to a forward vehicle in flight. A docking structure is affixed to the forward vehicle. A coupler has a line connection portion, a probe receiver port, and a plurality of aerodynamic controls. The probe receiving port receives and releasably retains a probe portion of the aft vehicle. A tow line has a proximal end, a distal end, and a line extension length. The proximal end may be attached to the tow actuation element. The distal end is connectable to the coupler. The tow actuation element is configured to adjust the line extension length. The aerodynamic control elements are configured to adjust lateral and vertical positioning of the coupler with respect to the probe portion when the system is in flight. Movement of the coupler is restrained with respect to the docking structure when docked thereto.

Abstract: A flight augmentation system with optical sensors to capture information from aircraft instruments. The system may determine a status of the aircraft based on the captured information and provide guidance to an operator. The system may collect long term data and determine an operational history of a pilot or an aircraft. The system may provide instruction based on the data or provide to interested third parties.

Abstract: A visual system for an electric vertical takeoff and landing (eVTOL) aircraft is illustrated. The system comprises an exterior visual device, a flight controller, and a pilot display. The exterior visual device is attached to the aircraft and is configured to detect an input of views of the exterior environment of the electric aircraft. The flight controller is communicatively connected to the aircraft, receives input from the exterior visual device, and generates an output of the view of the exterior environment of the aircraft as a function of the input. The pilot display is in the aircraft, receives the output of the view of exterior environment of the electric aircraft, and displays the output to a user.

Abstract: A method for monitoring a condition of a VTOL-aircraft (1), preferably an electrically propelled, more particularly an autonomous, more particularly a multi-rotor aircraft, with a plurality of spatially distributed actuators (2i, 2o), preferably propulsion units, wherein a primary control (4.1) is used for controlling a flight state of the VTOL-aircraft (1) and at least one secondary control (4.2) is used for controlling the actuators (2i, 2o) of the VTOL-aircraft (1), preferably the propulsion units (2i, 2o); during operation. The primary control (4.1) generates a primary data set, which is subject to a first uncertainty, and is entered into an estimation algorithm, and the secondary control generates a secondary data set, which is subject to a second uncertainty, and is also entered into the estimation algorithm.

Abstract: According to one aspect, a system for midair deployment of payload may include an aerostat including an inflatable structure, at least one tether, and a trigger, the at least one tether extending between the inflatable structure and the trigger, and at least one unmanned aerial vehicle (UAV) including wings, the at least one tether mechanically coupling the at least one UAV to the inflatable structure, and the trigger actuatable to release mechanical coupling of the at least one tether between the at least one UAV and the inflatable structure in midair.

Abstract: Provided is a target member for accurately guiding a moving body to a target site. A target member 10 is used when performing control for guiding a moving body 20 to a target site, and the target member 10 is formed by using two or more different feature members 11, 12 that are set such that a shape of a target member image 44 that corresponds to the target member 10 captured by an image capturing unit 21 (an image capturing apparatus) that is mounted in the moving body 20 changes according to a measurement distance that indicates a distance between the target member 10 and the moving body 20.

Abstract: A method and system provide the ability to autonomously operate an unmanned aerial system (UAS) over long durations of time. The UAS vehicle autonomously takes off from a take-off landing-charging station and autonomously executes a mission. The mission includes data acquisition instructions in a defined observation area. Upon mission completion, the UAS autonomously travels to a target landing-charging station and performs an autonomous precision landing on the target landing-charging station. The UAS autonomously re-charges via the target landing-charging station. Once re-charged, the UAS is ready to execute a next sortie. When landed, the UAS autonomously transmits mission data to the landing-charging station for in situ or cloud-based data processing.

Abstract: Systems and methods for interlining checked bags between two unaffiliated airlines. The traveler may purchase the interlining service and be assured that the checked bags associated with that service will be automatically transferred from their first flight to their next flight. The traveler does not have to collect the checked bag, and then re-check it onto the second flight, which may allow a traveler to say with in the security zone of the airport, where permitted by airport flow.

Abstract: Systems and methods are provided for fabricating a fuselage of an aircraft. The method includes: disposing arcuate sections of fuselage at a track of a factory such that concavities of the arcuate sections of the fuselage face a floor of the factory, and bearing edges of the arcuate sections of fuselage directly contact the track; advancing the arcuate sections of fuselage synchronously along the track in a process direction; and performing work within concavities of the arcuate sections of fuselage during pauses between pulses of the arcuate section of fuselage via stations that are disposed beneath the concavities and that are directly mounted to the floor of the factory.

Abstract: A device to assemble a skin and a frame of an aircraft fuselage. The device includes first and second brace members that extend along opposing sides of a gap. Arches are spaced apart and fixedly connected to the first and second brace members and that extend across the gap. A strongback is attached to and movable along the first and second brace members with the strongback having a curved shape that matches the plurality of arches. The strongback includes clamps configured to engage with the frame. First and second tension devices apply tension to the skin at the strongback.

Abstract: A launch system and method for orbital or suborbital air-launch of a payload involving releasably coupling a launch vehicle with a towed aircraft via an articulatable carriage to form an air-launch assembly, towing the air-launch assembly via a tow aircraft and interconnected tow cable to a first altitude, releasing the air-launch assembly from tow at or above the first altitude, activating the towed aircraft propulsion system and initiating a pull-up and climb maneuver of the towed aircraft to a second altitude, articulating the articulatable carriage to shift the air-launch assembly from a stowed position to a deployed position with the launch vehicle spaced from the towed aircraft, releasing the launch vehicle from the articulatable carriage and thus from the towed aircraft, and activating the launch vehicle propulsion system for further altitude gain or to meet specific mission requirements.

Abstract: Systems and methods to remove dust from an extravehicular mobility unit (EMU) worn by an astronaut in a deep space environment involve one or more ionic shower units installed external to an interior volume of a facility. Each ionic shower unit releases positively charged ions and negatively charged ions in a specified direction to neutralize the dust and generate neutralized dust. The interior volume of the facility is defined by an interior hatch that is separated from an exterior hatch by an airlock. One or more collection units is installed external to the interior volume. Each collection unit traps the neutralized dust to prevent the dust from entering the interior volume.

Abstract: A thermal control system may transfer energy (directly or after a delay) to a thrusting device that can be used to slow a reentry vehicle entering a gaseous atmosphere from orbit. The thermal control system may mitigate the heating of the vehicle by transferring heat generated by the viscous interaction between the vehicle and high-altitude portions of a planetary atmosphere to a working fluid. This working fluid may then be routed through and/or ejected through one or more nozzles aligned to produce thrust in a direction that opposes the forward motion of this vehicle. This counter thrust may help to slow the reentry vehicle and reduce the amount of kinetic energy that can be converted into thermal energy. The working fluid may also be stored to use for propulsion after the reentry vehicle slows below hypersonic velocities.

Abstract: An unmanned aircraft system operable for wing-borne lift in a flying wing orientation. The unmanned aircraft system includes an airframe having a leading edge, a trailing edge, first and second wingtips and a root chord. The airframe has an airfoil cross-section along chord stations thereof. A thrust array is coupled to the airframe including first and second motor mounts coupled to the leading edge respectively between the root chord and the first and second wingtips. The motor mounts each have first and second propulsion assemblies coupled to respective first and second distal ends thereof. The motor mounts each have a flight configuration substantially perpendicular with the leading edge forming a two-dimensional distributed thrust array such that the airframe extends outboard of the first and second motor mounts. The unmanned aircraft system includes an electric power system and a flight control system that are operably associated with the thrust array.

Abstract: An unmanned aerial vehicle (UAV) module includes a UAV having foldable wings coupled to a body of the UAV, a UAV case having length and width dimensions that is constructed and arranged to operate in (i) a closed configuration that stores and protects the UAV while the UAV module is transported within the UAV case between locations with the foldable wings in a folded configuration, and (ii) an opened configuration that provides a base from which the UAV launches vertically from within the UAV case while the foldable wings of the UAV remain in the folded configuration. The UAV is constructed and arranged to automatically unfold the foldable wings outwards from the body of the UAV to form a fixed wing that extends beyond the length and width dimensions of the UAV case for fixed wing horizontal flight after the UAV is airborne.

Abstract: A flush mount table-top assembly designed to mount an automatic cable tie tool to a work surface. The flush mount assembly includes an overlay plate, a tool cage, and a paddle assembly. The tool cage holds the automatic cable tie tool. The tool cage is suspended from the overlap plate by an integrated insert plate to enable the top of the automatic cable tie tool to protrude above the work surface. The paddle assembly is rotatably mounted to the insert plate. The paddle assembly activates the automatic cable tie tool. When not in use, the flush mount assembly can be configured to restore work surfaces lost due to fixture implementation.

Abstract: Described is an apparatus for filling food containers, including: a filling device for filling a food container including a neck through which the food product can be filled and a cap to cover the neck, wherein the filling device is configured to remove the cap and to fill the food container through the neck, a food container label printing device configured to print at least one label for the at least one food container; a user interface, configured at least to start the filling device; and a support for supporting at least the food container.

Abstract: In a method embodiment, an example method for simultaneously filling balloons with water, using an apparatus sufficiently compact to be operated while being held by hand, is disclosed. The method includes attaching the apparatus to a water supply. The apparatus includes a fitting comprising an inlet configured to connect to the water supply and a bulkhead joining the at least three branch assemblies. Each branch assembly includes a tube and an automatically-sealing balloon with a neck disposed around and removably attached to the tube. The method further includes simultaneously providing water from the attached water supply to each balloon of the balloon-filling apparatus. The method further includes detaching one or more of the balloons from the balloon-filling apparatus using a force comprising gravity each detached balloon and the water contained therein. Each detached balloon automatically seals upon detachment.

Abstract: A sealing station for sealing packaging units comprises a lower tool with at least one receptacle for a packaging unit and an upper tool. The lower tool and the upper tool are arranged to be movable relative to one another. The sealing station further comprises an edge extractor with at least one extraction opening for subjecting an interior of the packaging unit to a vacuum and/or a gas, and the lower tool comprises a lifting element for lifting a film cover of the packaging unit.

Abstract: A handling device having a holder for gripping web-shaped packaging material, which holder has a curvature in the longitudinal direction of the holder. When the packaging material is gripped by the handling device, a free end section of the packaging material is arched in the transverse direction of the packaging material and projects out from the handling device to be inserted into a processing station of a packaging machine.

Abstract: A product bagging assembly and method of manipulating a web material bag that is operable to create a bag opening that is greater than six inches and which is operable without substantially detracting from product throughput associated with use and operation of the product bagging assembly. In a preferred embodiment, the bag opening/dosing assembly includes a first actuator and a second actuator that are connected to one another such that a position of one of the actuators can be manipulated by operation of the other actuator. The product bagging assembly can be provided as a kit configured for plug and play operation with previously provided bag and product delivery systems.

Abstract: A method for quality assessment of a sealing section of a package, wherein the package includes at least a robustness layer and a plastic layer. The sealing section is formed by holding a first section and a second section of the package against each other while providing heat such that the plastic layer of the first and second section melt and thereby provide for that the first and second section adhere to each other. The method includes capturing image data depicting the sealing section using a camera, identifying a reference line in the image data, identifying a sealing section boundary line in the image data, determining a sealing section assessment feature set based on the reference line and the sealing section boundary line, and comparing the sealing section assessment feature set with a reference feature set.

Abstract: Time required for initial operation and operation immediately after wound body replacement is shortened. A packaging device packages an object to be packaged using a wound body. An elongated sheet-shaped packaging material is wound into the wound body. The wound body includes a recording medium that stores information. The information recorded in the recording medium includes remaining amount information indicating a remaining amount of the packaging material in the wound body. The packaging device includes a drive unit that generates driving force in order to rotate the wound body, an information reader that reads the remaining amount information stored in the recording medium, and a controller that controls the packaging device. The controller sets a rotation speed of the wound body based on the remaining amount information read by the information reader.

Abstract: An opening assembly for a package, particularly for containers including vials, bottles, syringes, and carpules which can be installed in a container handling and filling system. The package includes a tub covered by a covering film, the tub containing a nest bearing the containers in an orderly manner. The opening assembly includes at least one clamp located upstream of an opening placed on a separation wall between a first and second sterile environment. While the package passes through the opening, the clamp clamps a portion of an edge of the covering film, consequently removing the covering film from the tub.

Abstract: An apparatus for dispensing lids has at least one magazine lane including an entrance end, an exit end, and a longitudinal length defined therebetween. The at least one magazine lane further includes a plurality of side guides along the longitudinal length for guiding the lids therebetween and a pair of rollers for carrying the lids thereon. The apparatus further has a throat plate at or near the exit end, the throat plate including an opening. At least one of the throat plate, the side guides, or the rollers is adaptable so as to accommodate different sizes and/or shapes of lids.

Abstract: The invention relates to a packaging machine (100) for arranging elements, preferably cartons (K), on pallets (Z), wherein the packaging machine (100) has the following: a palletizing station (180) that has a platform (181) and a Scara robot (182), which is positioned on the platform (181) and which is embodied to move elements, preferably cartons (K), to be stowed on pallets (Z); a pallet feed (190), which is embodied to feed empty pallets (Z) along a path, wherein the platform (181) is embodied in a bridge-like manner and the path extends through under the platform (181) of the palletizing station (180) to a pallet loading station (191).

Abstract: A safety lifting device for positioning a labelling unit in a vertical direction (Z) in relation to a flow of objects where the labelling unit is arranged for printing labels and/or applying labels to the objects. The lifting device includes a linear actuator, a balancing unit, a drive unit connected to the linear actuator, and a movable section. The labelling unit is connected to the movable section. The linear actuator is connected to the movable section and arranged to control the position of the labelling unit. The balancing unit is arranged to counterbalance the gravitational force exerted on the linear actuator. The movable section of the lifting device includes an upper stand unit, and the lifting device further includes a lower stand unit. The upper stand unit is movably arranged in relation to the lower stand unit in the vertical direction.

Abstract: A labeling device (1) for applying a label to a product (2) located on a conveyor (3), includes an application cell (4), at least two label dispensers (5a,b) arranged outside the application cell (4) and an applicator (6), mounted inside the application cell (4), the applicator (6) being adapted to label the product (2) at variable positions on the conveyor (3) individually detected by a measuring system (9) at variable conveyor speeds, such that the labels are applied by a method for applying a label by the labeling device (1).

Abstract: An object can be heat-shrinkable packaged by placing an object inside of heat-shrinkable film, sealing the heat-shrinkable film around the object to form a heat-shrinkable package, coupling a first portion of a label to the heat-shrinkable package, and causing the heat-shrinkable film to shrink into heat-shrunk film and the heat-shrinkable package to form into a heat-shrunk package. The label includes an identifier on a second portion of the label. The label remains coupled to the heat-shrunk film after the heat-shrinkable film is caused to shrink into heat-shrunk film. The second portion of the label remains substantially undeformed after the heat-shrinkable film is caused to shrink into heat-shrunk film.

Abstract: A label printing device includes: a conveying unit configured to convey a mountless label; a shaft portion configured to change a conveying direction of the mountless label; a cutting unit configured to cut the mountless label of which the conveying direction is changed by the shaft portion and issue a label; and a controller configured to control the conveying unit and the cutting unit. The controller executes a preparatory operation mode in which the mountless label is conveyed a predetermined distance longer than a length of a portion extending from the shaft portion to the cutting unit in the mountless label by the conveying unit and is cut by the cutting unit when a label is not issued for more than a predetermined time.