Abstract: A combined Kort nozzle and rudder steering system for vessels requiring a high degree of maneuverability. A Kort nozzle is mounted around the propeller to direct the wash to generate a first turning source, and a rudder is mounted behind the Kort nozzle to react with the wash exiting the nozzle to produce a second turning force. The nozzle and rudder are pivoted in the same directions simultaneously, but with the rudder being pivoted at a faster rate than the nozzle. The nozzle is pivoted to an optimal maximum angle relative to the wash generated by the propeller and the rudder is pivoted to an optimal maximum angle to the wash exiting the nozzle.

Abstract: There is provided a toe angle control system for outboard motors. A memory stores therein a toe angle data table in which a running state of a ship and a lifting force generated along with propulsion of a plurality of outboard motors which are mounted on a body of the ship are associated with each other for each toe angle of the outboard motors. A controller is configured to adjust a toe angle of the outboard motors based on the running state of the ship and the toe angle data table. The toe angle data table is adapted to be associated with a plurality of running states of the ship mounted with the outboard motors. The controller selects a toe angle of the outboard motors so as to minimize the lifting force depending on a speed of the ship and trim angles of the outboard motors.

Abstract: A system for controlling one or more propulsion devices of a marine vessel. The system includes circuitry configured to: receive a steering angle command for a propulsion device of the marine vessel; receive a trim position of the propulsion device; and generate a steering actuator position command for the propulsion device based on the steering angle command and the trim position of the propulsion device.

Abstract: A single monotlithic moving window may follow the free aperture of an optical sensor contained in a housing over a reasonable field of regard by translating the window with respect to the sensor and/or a pod cover. Because the window angle of attack is unvarying, near field turbulence is minimized over the envelope of operation.

Abstract: A method and apparatus for boarding an aircraft. Passengers may be lined up in a first line and a second line relative to a doorway for the aircraft. A flow of the passengers in the first line and the second line may be controlled through a corridor connecting the doorway to a first aisle and a second aisle in an interior of the aircraft. The flow of the passengers may pass through a number of spaces in the corridor. The number of spaces may be reserved for a number of crew members during an emergency operation in which the passengers exit the aircraft.

Abstract: An airfoil portion includes an outer skin member and an inner stiffening member. Either the outer skin member or the inner stiffening member or both are arranged to delimit a chamber. The chamber is configured to contain an inner pressure, wherein the inner pressure differs from a pressure external to the chamber. In an embodiment, an aircraft includes such an airfoil portion. A method for providing such an airfoil portion with a chamber is also described.

Abstract: The present invention provides novel inflatable and rigidizable support elements, and methods of manufacture and use thereof. In particular, the present invention provides inflatable and rigidizable support elements which find use in rapidly deploying and supporting the wing of an aerial vehicle.

Abstract: A span-loaded, highly flexible flying wing, having horizontal control surfaces mounted aft of the wing on extended beams to form local pitch-control devices. Each of five spanwise wing segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other wing segments, to minimize inter-segment loads. Wing dihedral is controlled by separately controlling the local pitch-control devices consisting of a control surface on a boom, such that inboard and outboard wing segment pitch changes relative to each other, and thus relative inboard and outboard lift is varied.

Abstract: An aerocar includes a body and a multiple of wings. The multiple of wings can be selectively extendable away from a top portion of the body for a flight mode. The multiple of wings can be selectively retractable toward the top portion of the body for a roadable mode.

Abstract: An aircraft comprising a fuselage; a main wing provided on a fuselage lower side and including a center wing and an outer wing; and a fairing covering at least a lower surface of the center wing, and a seal interposed between an end edge in a right-left direction of the fairing and an outer wing lower surface. In the aircraft, a most outboard fitting located on a most outboard side out of fittings respectively provided at a plurality of positions in the right-left direction of the fairing, and an outer wing fitting provided on the outer wing are pin-coupled via a pin or pins extending along a front-rear direction. The outer wing fitting is coupled to the outer wing at a position on an inboard side with respect to the end edge and other than a position of a joining structure for joining the center wing and the outer wing.

Abstract: A flap support structure for an aircraft wing having a trailing edge flap, the flap support structure comprising: a flap support beam including an aerodynamic fairing; and a drive unit including a universal support structure which rotatably receives a drive shaft connected to a drive arm for moving the trailing edge flap, wherein the universal support structure also forms part of the flap support beam and supports the aerodynamic fairing.

Abstract: An electronic control architecture for an aircraft actuation system may include a first channel and a second channel. The first channel may be configured to receive one or more inputs comprising a movement command, to produce an output to control a component of the system, and to receive feedback from the component respective of movement of the component. The first channel may comprise a fault detection module configured to compare the feedback to the command to determine if the first channel is functioning properly. The second channel may be configured to receive the one or more inputs and, if the first channel is not functioning properly, to produce an output to control the component.

Abstract: An aerodynamic structure and a method of boundary layer control for thickness and camber morphing of aerodynamic surfaces in the aerodynamic structure are disclosed. In one embodiment, smart material controlled slots are provided along chord length and span length of the aerodynamic surfaces and leading edges of moveable control surfaces. Further, fluid is distributed on the aerodynamic surfaces and the leading edges of moveable control surfaces through the provided smart material controlled slots to vary fluid thickness of a boundary layer such that free stream fluid paths are modified around the aerodynamic surfaces to achieve an apparent change in a camber and thickness.

Abstract: An aircraft with C-shaped carrier surfaces wherein an axis of rotation of top surfaces is arranged in the respective aerodynamic center of the top surfaces, furthermore that each top surface can be adjusted by an adjustment device that can be controlled by a control device, wherein an angle of attack of the top surfaces can be adjusted that is optimal for a minimal induced resistance based on flight state parameters. This arrangement minimizes the adjusting moment during the adjusting of the top surfaces and is independent of the angle of attack of the top surface.

Abstract: A winglet system for an aircraft wing may include an upper winglet and a lower winglet mounted to a wing tip. The upper winglet root chord and the lower winglet root chord may each have a length of no greater than 100 percent of the wing tip chord. The lower winglet may have a static position when the wing is subject to an on-ground static loading. The lower winglet may be configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading.

Abstract: A stretchable mesh material extends across the opening of a cavity of the landing gear of an aircraft when the landing gear is in the deployed position. The mesh material alters the flow of air across the opening of the landing gear cavity and significantly reduces the amount of noise produced by the wheel well at low-to-mid frequencies.

Abstract: The object of the invention is to therefore create an automated and versatile autonomously climbing undercarriage with flight capability that automatically reaches a suitable area for cleaning purposes, repair purposes, and monitoring purposes without being constantly connected to a supply station or base station in the process, and that independently goes to the surface of the facade and independently moves along the surface and away from the surface. The automated and versatile autonomously climbing undercarriage (1) with vacuum suction units (2) as per the invention involves a multicopter (3) with two, three or more rotors (11) or propellers (11) attached to the autonomously climbing undercarriage (1).

Abstract: An aircraft with a landing gear, a compartment to stow the landing gear and doors for the compartment movable between an open position and a closed position. The movement of the doors is controlled by a maneuvering system having two transmission chains or linkages each connecting one of the doors to an actuation member that includes a rotatable arm and an actuating cylinder. Each transmission chain or linkage has a relay element mounted pivotably on a structural element of the aircraft, a first connection element between the arm and the relay element, and a second connection element between the door and the relay element.

Abstract: A flapping wing device may include a main body and several wings hingedly coupled to the main body. The wings may be configured to reciprocate or “flap” relative to the main body to provide lift for the flapping wing device. A motor and trans mission, such as a crankshaft, are used to drive the reciprocating motion of the wings. The wings reciprocate from a first position that is substantially vertically parallel to the main body of the device to a second position in which a second end, opposite the hinged end, extends away from the main body. The motion of the reciprocating wings may be reminiscent of the motion of a jellyfish. In some instances, a first set of opposing or alternating wings may be reciprocated at an offset period relative to a second set of opposing or alternating wings, such as a quarter period offset.

Abstract: Methods, systems and devices are provided for securing a drone delivering a package of goods to a delivery destination. A notification may be provided to a device of the purchaser that the drone has arrived near the delivery destination. The drone may hover at a secure altitude from a landing zone at the delivery destination. The drone may receive a purchase code associated with a purchase of the package of goods. The drone may authenticate the purchase code as a condition for landing. The drone may land in the landing zone at the delivery destination when the purchase code is authenticated. The drone may abort the landing when the purchase code is not authenticated. The drone may receive a delivery code associated with completing delivery the package of goods. The drone may require the delivery code as a condition for releasing the package of goods.

Abstract: According to an aspect, an unmanned aerial vehicle (UAV) is provided that is capable of flying between a pick up point and a delivery point with respect to a package transfer operation. The delivery point is identifiable by the UAV through global positioning system (GPS) coordinates of the delivery point and verification of a device identifier of a package docking device (PDD) associated with a package transfer request. A control processor coupled to the UAV receives a transaction packet for the operation that includes the GPS coordinates and the device identifier of the PDD associated with the request. Upon arrival of the UAV at the delivery point, the control processor verifies that a device identifier of a PDD located at the delivery point matches the device identifier in the transaction packet, implements the package transfer operation, and transmits confirmation of completion of the operation to an originator of the request.

Abstract: An electrically powered unmanned aircraft system (UAS or drone) including a propeller including a core formed by battery material layers as a power source and integrated as a structural component of the drone. The battery material layers can be a graphene super capacitor or a nanopore battery structure. Power available from the integrated battery material layers can be used to power an electric motor included with the drone and operating to rotate the propeller.

Abstract: Systems and methods for controlling an unmanned aerial vehicle within an environment are provided. In one aspect, a system comprises one or more sensors carried by the unmanned aerial vehicle and configured to provide sensor data and one or more processors. The one or more processors can be individually or collectively configured to: determine, based on the sensor data, an environment type for the environment; select a flight mode from a plurality of different flight modes based on the environment type, wherein each of the plurality of different flight mode is associated with a different set of operating rules for the unmanned aerial vehicle; and cause the unmanned aerial vehicle to operate within the environment while conforming to the set of operating rules of the selected flight mode.

Abstract: A method and apparatus for determining actions for entities (4, 6) such that a goal is accomplished constraints are satisfied. The method comprises: determining an initial plan comprising actions that, if performed by the entities (4, 6), the goal would be accomplished; determining that a constraint would not be satisfied if the initial plan was implemented; and iteratively performing steps (i) to (v) until a final plan that accomplishes the goal and satisfies the is determined. Step (i) comprises identifying a constraint that is not satisfied in part of the current plan. Step (ii) comprises determining a remedy that, if implemented, satisfies the identified constraint. Step (iii) comprises updating the goal specification to include the remedy. Step (iv) comprises, using the updated goal specification, determining a further plan that accomplishes the goal and the remedy. Step (v) comprises determining whether or not the further plan satisfies each constraint.

Abstract: The ventilation apparatus (20) according to the invention comprises a fan (30) including a rotary machine (32) and a fan wheel (34), an observation module, a module for connecting the device (20) to a power source (12), the fan wheel (34) being set in rotation by the rotary machine (32) when the apparatus (20) is connected to the power source (12), and rotating freely when the apparatus (20) is disconnected from the power source (12). The device (20) further includes an internal power module electrically connected between the rotary machine (32) and the observation module, the internal power module being able to recover an electric current generated by the rotary machine (32) driven by the fan wheel (34), to power the observation module (62), when the apparatus (20) is disconnected from the power source (12).

Abstract: An air generation unit for an aircraft, an air generation arrangement, an aircraft and a method for operating an air generation unit in an aircraft are described. The air generation unit for an aircraft includes an air supply means and a control unit. The air supply means is configured to supply air to an air conditioning system of an aircraft's cabin. The air supply means is further or alternatively configured to supply air to a flow control system of an aircraft. The control unit is configured to provide, during cruise conditions of the aircraft, a larger amount of the air to the air conditioning system than to the flow control system. The control unit is further configured to provide, during take-off and/or landing conditions of the aircraft, a larger amount of the air to the flow control system than to the air conditioning system.

Abstract: An environmental control system (ECS) for an aircraft may include a mixing diffuser configured to admit a stream of cold air and a stream of hot air and a reheater-condenser fluidly coupled with an output end of the mixing diffuser. The mixing diffuser may include a diffuser cone with a plurality of holes configured to allow passage of hot air into the stream of cold air so that the cold air and the hot air are combined to produce a mixed airstream. The reheater-condenser may include mixing tabs configured to produce further mixing of the mixed airstream.

Abstract: A method of treating ice for a windshield of an aircraft, in which method at least two distinct de-icing zones of the windshield are defined. During a de-icing step, at least one de-icing means is activated temporarily in order to de-ice the de-icing zones in succession and in a given cycle.

Abstract: A system for locating a downed aircraft is provided. The system includes a canister. The canister has an internal housing and a door. The door covers an opening leading into the internal housing. The present invention includes a plurality of inflatable pods having a light and a battery powering the light. The pods include a deployed position and a stowed position. The stowed position includes the deflated pods within the canister and the deployed position includes the inflated pods released from the canister and inflated. When an aircraft is crashing, the canister may be released from the aircraft, the pods may be released from the canister and inflated, and the light may be powered.

Abstract: The present disclosure provides methods and articles useful in sealing fasteners, including seal caps and in particular translucent or transparent seals or seal caps. In some embodiments, a seal cap which is optically translucent and optionally visibly transparent contains an uncured sealant, which is optionally optically translucent or visibly transparent, and is applied to a fastener. In some embodiments, the sealant is cured by application of actinic radiation to the sealant through the seal cap. In another aspect, a protected fastener construction is provided comprising: q) a fastener; r) a seal cap; and s) a cured sealant; wherein the sealant is optically translucent and optionally visibly transparent.

Abstract: A locking member includes a body having a first end, a second end opposite the first end, a bore extending through the body from the first end to the second end, a bearing surface at the first end, fastening means for securing the locking member to a pin member, and a channel formed within the bearing surface and surrounding the bore. The locking member also includes a first insert located within the channel. The first insert is adapted such that, when the locking member is secured against a surface of a workpiece, the first insert prevents passage of a sparking material from within the bore of the locking member.

Abstract: This optical device for lighting and/or signaling system comprises a set of at least one collimator (10) each comprising a light ray input surface (13) refracting the light, a collimated light beam output surface (17) and a reflecting surface (16) intended to reflect light beams refracted by the input surface and suitable for reflecting the rays in parallel directions. The input surface (13) comprises a set of surfaces (S1, S2, S3) refracting the light that are juxtaposed and suitable for directing the rays from the source towards the reflecting surface.

Abstract: The Unmanned Aircraft Systems ground support platform is a portable, multifunctional apparatus to accommodate UAS (Drone, UAV) landings, takeoffs, idle time, maintenance, retail merchandise product display and package delivery support within the UAS recreational and business industry. The Unmanned Aircraft Systems ground support platform will provide stability and cleanliness of a Unmanned Aerial Vehicle. Ownership identification is intergraded into the base platform.

Abstract: A method for joining two aircraft structural parts by a bolted or riveted joint and for preventing cracks at said joint includes a step of providing a first metallic aircraft structural part and a second aircraft structural part, wherein the first aircraft structural part includes a first joint region and a second aircraft structural part includes a second joint region. Furthermore, the method includes a step of inducing compressive residual stresses in a first area of the first joint region for preventing cracks. Finally, the method includes a step of fastening together the first and second aircraft structural parts at the first and second joint regions by a bolted or riveted joint. An aircraft including first and second aircraft structural parts is also described.

Abstract: A maintenance system for use with an aircraft and a method for management of a maintenance routine for an aircraft with a maintenance system comprising multiple communication terminals located physically about the aircraft and in data communication with each other, the method includes executing a maintenance software program for a maintenance routine comprising maintenance tests corresponding to components of the aircraft.

Abstract: A maintenance system for use with an aircraft and a method of implementing a maintenance schedule for an aircraft with a maintenance system comprising multiple communication terminals located physically about the aircraft and in data communication with each other, the method includes executing a maintenance software program for a maintenance routine comprising maintenance tests corresponding to components of the aircraft and displaying the maintenance routine on at least one of the communication terminals to define a control terminal.

Abstract: A deployable mast with spontaneous autonomous deployment comprises at least one elementary structural block with a longitudinal axis of deployment X, the elementary structural block comprising two, respectively lower and upper platforms parallel to a plane YZ orthogonal to axis X, and N stages stacked on one another parallel to axis X, where N is more than 1, and where i is between 1 and N?1. Each stage comprises at least six flexible longitudinal connection arms which are articulated by tape springs, which arms are, in the deployed position, on planes parallel to axis X and are inclined relative to axis X, the N stages being secured to one another in pairs by means of connection platforms parallel to the plane YZ; two adjacent lower and upper stages are offset angularly relative to one another by rotation around the axis of deployment X.

Abstract: A powder filling method includes introducing a tube into a can so that the lower end of the tube is near the bottom of the can. The powder in the can is introduced through the tube. The proximity of the lower end of the tube to the powder is controlled by retracting the tube as the powder fills the can.

Abstract: A stopper and container body are molded in the same molding machine. An assembly device, such as a pick and place robot, transfers the stopper from one mold cavity into the opening in the container body located within another mold cavity, or vice versa, to assemble the stopper and container body. Then, the assembled container body and stopper are removed from the molding machine and transported to a needle filling and laser resealing station for filling and laser resealing. A laminar flow source directs a substantially laminar flow of air or sterile gas over the mold surfaces, stoppers and container bodies, and assembly device, to prevent contamination during assembly.

Abstract: A dispensing device that dispenses a predetermined volume of fluid into a receptacle has a valve that controls the flow of the fluid through the device. The valve is pre-heated to a calculated operating temperature before dispensing operations begin. Once the temperature of the valve reaches the calculated operating temperature, the device begins dispensing the fluid. The valve is maintained at that calculated temperature during dispensing operations.

Abstract: A method and apparatus for producing multi-compartment water-soluble pouches 38 from a base web 27 and a lidding web 35 is disclosed. The apparatus includes a rotatable former 21 having compartment forming cavities 23 into which the base web 27 can be formed. The former 21 is configured so that compartments 26,29,32 of a pouch 38 can be formed and filled sequentially and thereafter all compartments 26,29,32 closed and sealed by affixing the lidding web 35 to the base web 27.

Abstract: Described are tensioning devices comprising: a base housing comprising a drive gear, a spindle gear proximate the drive gear, and a pawl proximate the spindle gear; a lever pivotally coupled to the base housing and comprising a lug pivotally coupled to the lever, wherein the lug is configured to interact with the drive gear; a spindle fixedly coupled to the spindle gear; and a brake assembly coupled to the base housing, wherein, the lug is configured to avoid engagement with the drive gear when the lever is rotated in a first direction, but configured to engage the drive gear when the lever is rotated in a second direction, so as to effect rotation of the drive gear in the second direction, and thereby effect a counter rotation of the spindle gear and spindle. Methods of tensioning straps via such tensioning devices are also described.

Abstract: A strapping assembly for fastening a strap to a support surface includes a handle may be gripped. A housing coupled to the housing. The housing is structured to dispense a strap. A disk is coupled to the housing. The disk contains the strap. A stapler is coupled to the housing. The stapler selectively dispenses a staple from the housing. The strap is fastened to a support surface. A cutter is coupled to the housing. The cutter selectively cuts the strap after the strap is fastened to the support surface. A pair of actuators is coupled to the handle. The actuators are each electrically coupled to an associated one of the stapler and the cutter. The actuators each actuates the associated stapler and cutter.

Abstract: A process for packaging a product (P) arranged in a support (4) comprising unrolling a film (10a), transversely cutting the unrolled portion of film (10a) and preparing cut film sheets (18), moving the cut film sheets (18) to a packaging assembly (8) defining at its inside a packaging chamber (24), progressively moving a number of supports (4) inside the packaging chamber (24) of a packaging assembly (8), keeping the packaging chamber (24) open for a time sufficient for a number of supports (4) and for a corresponding number of film sheets (18) to properly position inside said packaging chamber (24), hermetically closing the packaging chamber (24) with the film sheets held above the respective support (4) and at a distance sufficient to allow gas circulation inside the support (4), optionally causing one or both of: a gas withdrawal from the hermetically closed packaging chamber (24) and gas injection of a gas mixture of controlled composition, heat sealing the film sheet (18) to said support (4), wherein the

Abstract: A method and apparatus for packaging a bag (1) in which a gas channel (5) where the laminated films constituting the front and back faces of the bag are not fused is formed inside a sealed part (2) of the side edge, with the lower end of the gas channel opening (through a communicating portion (5b)) into the bag, and a gas inlet (5a) that allows the gas channel to communicate with the outside of the bag being formed at the upper end of the gas channel. After the bag has been filled with its filling material, a pressurized inert gas is blown from the gas inlet into the gas channel and then through the gas channel into the bag, thus replacing the air inside the bag with the inert gas. After this gas replacement, the gas inlet is sealed, and the bag mouth is also sealed.

Abstract: A packaging machine for packaging one or more articles in a package; the packaging machine comprising a first article path and a second article path; wherein the packaging machine comprises a first apparatus for packaging articles in a paperboard carton; and a second apparatus for packaging articles in a plastics material; the packaging machine comprising at least one transfer device for transferring articles between a pair of conveyors to select either the first article path or the second article path; the packaging machine being configurable such that the articles may follow either the first or second article path such that the articles may be packaged in either or both of the paperboard carton and the plastics material.

Abstract: The present invention relates to a packing machine having:—a heating device, which heats up a film web—a forming station by means of which packing blisters are formed in the film web and/or the top film web, preferably by deep drawing;—a filling station in which the packing blisters are filled with a material to be packed;—a sealing station which seals a top film web to the packing blister; and—a longitudinal and/or transverse cutter, which separates the finished packages. The present invention also relates to a method for heating up a film web using a heating device which comprises a heated porous agent.

Abstract: The present invention relates to a packaging machine (1) having:—a filling station (7), in which packaging depressions (6) are filled with a material to be packaged (16),—a sealing station (15) at least having an upper tool (12) and a lower tool (11) which seal an upper film web (14) to the packaging depression (6), wherein the sealing station (15) has at least one valve which connects the lower tool (11) and/or upper tool (12) reversibly to a rough and/or fine vacuum source. Furthermore, the present invention relates to a sealing tool.

Abstract: A facility (1) for producing a container loaded with a biopharmaceutical fluid, includes: a container (2) wherein a biopharmaceutical fluid is placed (B); a control module (9) for controlling the filling of gas into the container (2); and an analysis module (10) for estimating a parameter for controlling the gas filling; and a pumping device (40) for generating a depression in the inner filling space (Vg).

Abstract: Metal-walled vacuum flasks including tin phosphorus oxide sealing glass, and methods of sealing an exhaust aperture for a metal-walled vacuum flask, including disposing a tin phosphorus oxide sealing glass frit adjacent the exhaust aperture, applying a vacuum to the metal-walled vacuum flask; and raising a temperature of the sealing glass frit under the vacuum sufficiently that the sealing glass flows and seals the exhaust aperture.