Abstract: A fairing for an aircraft is disclosed in which the fairing comprises a first fairing portion configured to be fixedly attached to a first structural component and having a first edge; a second fairing portion configured to be fixedly attached to a second structural component and having a second edge, wherein the first edge and the second edge define an interface configured to enable relative movement between the first fairing portion and the second fairing portion.

Abstract: Mini-spoilers for enhancing the effectiveness of lateral-control surfaces of aircraft wings are described. An example aircraft includes a wing, a lateral-control surface, and a mini-spoiler. The lateral-control surface is movably coupled to the wing. The lateral-control surface is movable between a neutral position, a first upward deflected position, and a second upward deflected position extending beyond the first upward deflected position. The mini-spoiler is located on or forward of the lateral-control surface. The mini-spoiler is movable between a retracted position and a deployed position. The mini-spoiler is configured to be moved from the retracted position to the deployed position based on the lateral-control surface being moved from the neutral position to or toward the first upward deflected position.

Abstract: An exemplary spring-loaded link for an aircraft including a spring interposed between a first and a second rod, the spring, when compressed, urging the first rod and the second rod away from each other.

Abstract: A turbine engine module including an upstream propulsive unit including a propellers doublet that are upstream and downstream, respectively mounted around an axis, a power turbine shaft with axis of rotation intended for rotating the propellers doublet, a speed reducer connected to the propellers doublet and driven by the shaft, and, a pitch-changing system including a cylinder that controls the pitch of the blades of the upstream propeller the rotational axis of the propellers doublet is shifted in relation to that of the shaft. The cylinder is placed downstream of the reducer, and the pitch-changing system includes a shaft for controlling the pitch of the blades that connect the cylinder to the blades of the upstream propeller.

Abstract: An airplane comprises a fuselage, two wings, engines, a rear tail unit comprising a horizontal tail provided with two tail ends, a first and a second set of fuel tanks, and a fuel transfer system configured to be able to transfer, at least in flight, fuel from one to the other of the first and second sets of fuel tanks, the tail ends being, in addition, mounted so as to be able to be pivoted, at least in flight, relative to the horizontal tail, the airplane thus having a configuration changeable in flight.

Abstract: A lifting device including: a movable discontinuity (1) located in a surface of the lifting device, the movable discontinuity (1) being movable between: an active position in which the movable discontinuity (1) acts as vortex generator, and a passive position in which the movable discontinuity (1) is integrated into the surface of the lifting surface, a conduit (2) located in the spanwise direction of the lifting surface and in communication with the movable discontinuity (1), the lifting surface including openings (3) in its surface spanwise distant from each other in communication with the conduit (2), the movable discontinuity (1) and the conduit (2) being configured such that when an airflow goes through the conduit (2), this airflow activates the movable discontinuity (1) to act as a vortex generator of the lifting surface.

Abstract: A dual-rotor wing motor includes a sleeve separating an inner shaft from an outer shaft. An external bearing is independently coupled to a shaft cover while an internal bearing is independently coupled to the inner shaft, and thus the external bearing and the internal bearing independently bear a friction force due to the rotation of the respective single shaft, the heat generated by the friction force can be reduced and the lubricant cannot be easily evaporated. Accordingly, the service life of the dual-rotor wing motor of the present invention can be prolonged.

Abstract: A multirotor aircraft with at least two thrust producing units, the multirotor aircraft being adapted for transportation of passengers and comprising an aircraft operating structure that is adapted for operation of the multirotor aircraft in failure-free operating mode, and a redundant security architecture that is at least adapted for operation of the multirotor aircraft in case of a failure of the aircraft operating structure in operation, the redundant security architecture being provided to comply with applicable authority regulations and certification requirements regarding passenger transportation.

Abstract: A fully compounding rotorcraft includes a fuselage having first and second wings extending therefrom and configured to provide lift compounding responsive to forward airspeed. A twin boom includes first and second tail boom members that extend aftward from the first and second wings. An empennage is coupled between the aft ends of the tail boom members. An anti-torque system includes a tail rotor that is rotatably coupled to the empennage. An engine is disposed within the fuselage and is configured to provide torque to a main rotor assembly via an output shaft and a main rotor gearbox. An auxiliary propulsive system is coupled to the fuselage and is configured to generate a propulsive thrust to offload at least a portion of a thrust requirement from the main rotor during forward flight, thereby providing propulsion compounding to increase the forward airspeed of the rotorcraft.

Abstract: The invention relates to an aerodyne with vertical take-off and landing ability and the ability to generate lift by means of both rotors and fixed wings, which includes: a fuselage (1); two fixed wings (2); two front rotors (11) and two rear rotors (12) arranged symmetrically and actuated by means of motors (13), each rotor (10) being attached to a central portion of a fixed wing (2) by means of a support (14) and connected pivotably about a connection shaft (E2), which allows changing the inclination of each rotor (10) from a longitudinal forward movement position, in which they propel the aerodyne horizontally, to a lift position in which it provides vertical lift; said rear rotors being in a lift position partially overlapping a portion of the wing including a flap (20) freely connected to the rest of the wing, the position thereof being determined between a lift position and a longitudinal forward movement position by the effect of the aerodynamic thrust.

Abstract: A rotorcraft includes a main rotor system coupled to a mast and a rotor assembly. The rotor assembly includes a yoke comprising a rotor coupling, a first damper mount attached to the rotor coupling, a rotor extension configured to couple to the rotor coupling and comprising a second damper mount, a damper coupled to the first and second damper mounts, and a fairing enclosing the damper and the yoke.

Abstract: This invention employs a generic axial modulating mechanism to manipulate the pitch of the blades of a fan or propeller; conceptually, this is a threaded bolt and nut where the threaded bolt would be analogous to a rotating shaft, with an acme thread (i.e. the “rotor thread”) on its exterior, and the nut would be analogous to the axial modulator of this teaching. The “nut,” or axial modulator, is further spun above and beyond the rotation in the rotating bolt or rotating shaft. The axial motion of the axial modulator is then deployed to do useful work i.e. manipulate the pitch of the blades of a fan or propeller. This invention is a continuation in part of a previous variant disclosed where the means of modulating the axial modulator was magnetic. The variation introduced in this teaching instead achieves the modulation using a gear-driven arrangement.

Abstract: A device for controlling the orientation and magnitude of cyclorotor thrust and for providing mechanical power to that cyclorotor including a system of linear actuators to position a cam or eccentric around a geared shaft. The invention includes a frame which supports the main cyclorotor shaft, provides mounting for the linear actuators, and contains the mechanical gearing system.

Abstract: This invention is directed toward an aerodynamically designed drone with a unique angle of propulsion. The drone uses airfoil design to move more efficiently through the air, and the aerodynamic design is optimized when the drone is tilted forward at various degrees of “tilt” to provide the most aerodynamic profile to the oncoming air. The invention contemplates single hull, double hull and triple hull designs, and is applicable to heaving lifting drones, drones use for photography and remote sensing, and racing drones.

Abstract: An apparatus includes a light source configured to emit light, a beam shaper configured to project the light to substantially surround the apparatus in a plane and onto an object in the plane, and a receiver configured to project the light reflected from the object in the plane to an image sensor. A distortion parameter of the receiver in conjunction with a difference between the emitted light and the reflected light detected at the image sensor is indicative of at least one of a direction or a distance of the apparatus relative to the object.

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

Abstract: The present invention is directed to a device for dispensing pyrophoric decoy particulates where the device is comprised of at least one payload vessel having a structural wall that forms a cavity for housing a plurality of pyrophoric particles. The structural wall has at least one opening to facilitate dispersal of the pyrophoric particles. The payload vessels are inserted inside a tubular sleeve and hermetically sealed inside the sleeve. Within the sleeve the at least one payload vessel is also in direct contact with an expulsion assembly that upon activation pushes the payload vessels and its pyrophoric contents out of the sleeve to react with the air.

Abstract: A parasite aircraft for airborne deployment and retrieve includes a wing; a fuselage rotatably mounted to the wing; a dock disposed on top of the fuselage and configured to receive a maneuverable capture device of a carrier aircraft; a pair of tail members extending from the fuselage; and a plurality of landing gear mounted to the wing. A method of preparing a parasite aircraft for flight includes unfolding an end portion of a wing; unfolding an end portion of a tail member of the parasite aircraft; and rotating a fuselage of the parasite aircraft so that the fuselage is perpendicular to the wing. A method of preparing a parasite aircraft for storage includes rotating a fuselage of the parasite aircraft to be parallel with a wing of the parasite aircraft; folding an end portion of the wing; and folding an end portion of a tail member of the parasite aircraft.

Abstract: A conformal seat insert for an adjustable vehicle seat, the conformal seat insert comprising an insert frame, the insert frame having one or more insert reference features for locating the insert frame on a seat frame of the vehicle seat in a predetermined position relative to the seat frame, and a contoured support surface formed in the insert frame, the contoured support surface having a crew reference point corresponding to an acromial point of a shoulder of a seat occupant of the adjustable vehicle seat, the crew reference point being a datum from which an eye position of the seat occupant is established relative to instrumentation of an aerospace vehicle in which the adjustable vehicle seat is located.

Abstract: An environmental control system of an aircraft includes a ram air circuit including a ram air shell having at least one heat exchanger positioned therein, a dehumidification system arranged in fluid communication with the ram air circuit, and a compressing device arranged in fluid communication with the ram air circuit and the dehumidification system. The compression device includes a compressor and a first turbine coupled to one another via a shaft. During operation of the first turbine, work is extracted from a first medium within the first turbine to power the compressor. At an outlet of the first turbine, a temperature of the first medium is above freezing and at least a portion of the moisture within the first medium is condensed.

Abstract: Ice detection systems for aircraft and related methods are disclosed. A disclosed example ice detection system includes a thermochromic device to sense a temperature of freestream air relative to a temperature threshold, and a hydrochromic device to sense an amount of moisture in the freestream air relative to a moisture threshold. A controller to detect an icing condition in response to the thermochromic device sensing a temperature that is less than or equal to the temperature threshold and the hydrochromic device sensing an amount moisture that exceeds the moisture threshold.

Abstract: An ejector system for propelling a vehicle. The system includes a diffusing structure and a duct coupled to the diffusing structure. The duct includes a wall having openings formed therethrough and configured to introduce to the diffusing structure a primary fluid produced by the vehicle. An airfoil is positioned within the flow of the primary fluid through the openings to the diffusing structure.

Abstract: A unit (1?, 10?, 100?) for generating non-propulsive electrical power for use on board an aircraft, the unit (1?, 10?, 100?) comprising an electricity production device (3, 30) comprising a gas turbine (31) and an electricity generator (32) mechanically connected to an outlet shaft (33) of the gas turbine (31), said electricity generator (32) including output electrical connections (320) for being electrically connected to an electrical power supply network (2, 20, 200) on board an aircraft. The unit (1?, 10?, 100?) includes energy storage means (5) and regulator means (6) configured to control the speed of rotation of the gas turbine (31) as a function of the electrical power required by the on-board electrical power supply network (2, 20, 200).

Abstract: A method for operating a vertical takeoff and landing aircraft includes modifying a first variable component of a wing associated with a first portion of the plurality of vertical thrust electric fans relative to a second variable component of the wing associated with a second portion of the plurality of vertical thrust electric fans to adjust an exposure ratio of the first portion of the plurality of vertical thrust electric fans relative to the second portion of the plurality of vertical thrust electric fans.

Abstract: An engine pylon that is used for supporting an engine, the engine pylon including a pylon body having an upper pylon and a lower pylon. The pylon further includes a fairing that covers the pylon body such that the upper pylon and fairing define a predetermined region. Moreover, the pylon includes a first drain that is configured to discharge a flammable liquid leaking from a pipe provided within the predetermined region into outside air; and a ventilation path configured to bring the inside of the predetermined region into communication with the outside air. The first drain includes a drain port and a drain pipe, wherein the drain pipe extends in a rear direction from the drain port and has an outlet at a rear end of the drain pipe, the outlet being located past a rear end of the upper pylon and a rear end of the lower pylon.

Abstract: Controlling a movement of an aircraft. A computer system detects a position of a group of integrated control levers for the aircraft. The computer system controls a forward thrust, a drag, and a reverse thrust generated by the aircraft based on the position of the group of integrated control levers.

Abstract: A vehicle which includes a flight controller that is configured to receive one or more desired forces or moments associated with a plurality of rotors in the vehicle and determine a plurality of motor control signals for the plurality of rotors based at least in part on the desired forces or moments and an expected rotor noise produced by at least one of the plurality of rotors. The vehicle further includes the plurality of rotors, where the plurality of motor control signals is used to control the plurality of rotors.

Abstract: An inlet for a flight vehicle engine, such as for a supersonic or hypersonic engine, includes an internal flow diverter to divert boundary layer flow. The flow diverter is configured to minimize disruption to flow outside the diverted boundary by being configured through use of a flow field that is also used to configure the walls of the inlet. The flow field that is used to configure an inlet-creating shape and a diverter-creating shape has the same flow generator, contraction ratio, compression ratio, mass capture ratio, pressure ratio between entrance and exit, and/or Mach number, for example. The internal diverter may be configured so as to allow arbitrary selection of a leading edge shape for the internal diverter, for example to use a shape that helps avoid radar detection.

Abstract: Hybrid propulsion engines for aircraft are described herein. An example hybrid propulsion engine includes a propulsor and a gas turbine engine having a first drive shaft. The hybrid propulsion engine also includes an electric motor having a second drive shaft, and the propulsor is coupled to the second drive shaft. The hybrid propulsion engine further includes a clutch coupled between the first drive shaft and the second drive shaft to enable the gas turbine engine to drive the propulsor, via the clutch, during a first mode of operation and to enable the electric motor to drive the propulsor during a second mode of operation.

Abstract: An electrically conductive patch for a sheet that is part of a skin of an aircraft is disclosed. The sheet includes an outermost surface constructed of an electrically conductive material and one or more electrical discharge points that are conductively coupled to the outermost surface of the sheet. The electrically conductive patch is disposed along the outermost surface of the sheet and is conductively coupled to the outermost surface of the sheet. The electrically conductive patch is constructed of a voltage responsive film configured to change from a first coloration and into a second coloration in response to experiencing a threshold voltage difference, where the first coloration substantially matches a coloration of the skin of the aircraft.

Abstract: An unmanned aerial vehicle (UAV) has: a body for carrying an article; at least one rotor; and a light source for generating a light beam to indicate the landing zone for the UAV. The UAV, in use, is flown to a desired location, that might be a site of an emergency with no defined landing zone. The UAV descends, and, while descending the light source is operated to illuminate and to define a landing zone. The UAV can be provided with lights and an audio source to warn and advise bystanders that the UAV is landing and to stand clear of the landing zone.

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

Abstract: The disclosure relates to a method for guiding a pilot of an approaching aircraft to a stop position at a stand, said method being characterized by: monitoring a position of the approaching aircraft within a volume at the stand, comparing said monitored position with a first area, said first area enclosing the stop position, comparing said monitored position with a subsection of the first area enclosing the stop position, if said monitored position is inside said subsection: transmitting information to a display to show an indication to the pilot to proceed approaching the stand, and if said monitored position is inside the first area but not inside said subsection: transmitting information to the display to show an indication to the pilot to stop the aircraft. The disclosure further relates to an aircraft docking system.

Abstract: Capture devices for unmanned aerial vehicles, including track borne capture lines, and associated systems and methods are disclosed. An example system includes a support having an upright portion and a boom portion. The example system further includes a capture line carried by and extending downwardly relative to the boom portion. The capture line has an engagement portion positioned to engage an unmanned aircraft. The example system further includes a flexible landing device positioned to receive the unmanned aircraft in response to the unmanned aircraft engaging the engagement portion.

Abstract: A method and system for alleviating a load is provided. A support system is positioned at a nominal location with respect to an object. The support system comprises jacks and supports. Each of the supports is associated with one of the jacks. The object is positioned on the support system. The support system with the object is moved across a path. The height of each of the jacks is adjusted as the support system moves along the path to maintain a desired minimum load on each jack. Maintaining the desired minimum load prevents damage to the object.

Abstract: A device and an inspection method for inspecting screw and nut assemblies in an aircraft, comprising a mechanical tool and a digital human-machine interface. The mechanical tool comprises a housing comprising a bearing surface defining a reference plane, a support beam mounted to be translationally mobile inside the housing, a linear encoder configured to measure, in use, a distance between the reference plane and a bottom face of the mobile support beam. The digital human-machine interface comprises a central unit, a display screen, an application and a database in which are stored validity ranges or standardized distances relating to types of assembly, the application and the database being loaded and operational in the central unit.

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 satellite system operates at altitudes between 100 and 350 km relying on vehicles including a self-sustaining ion engine to counteract atmospheric drag to maintain near-constant orbit dynamics. The system operates at altitudes that are substantially lower than traditional satellites, reducing size, weight and cost of the vehicles and their constituent subsystems such as optical imagers, radars, and radio links. The system can include a large number of lower cost, mass, and altitude vehicles, enabling revisit times substantially shorter than previous satellite systems. The vehicles spend their orbit at low altitude, high atmospheric density conditions that have heretofore been virtually impossible to consider for stable orbits. Short revisit times at low altitudes enable near-real time imaging at high resolution and low cost. At such altitudes, the system has no impact on space junk issues of traditional LEO orbits, and is self-cleaning in that space junk or disabled craft will de-orbit.

Abstract: A modular spacecraft is provided. The modular spacecraft includes a bus module and a payload module. The bus module provides additional thermal radiative capacity for the payload module by including a bus-panel payload thermal zone that couples operational components of the payload module to a radiator panel in the bus module. The bus module also includes its own operational components that are thermally coupled to the radiator panel but that are thermally isolated from the payload module and the bus-panel payload thermal zone.

Abstract: A load-decoupling attachment system is configured to secure a component to a primary structure. The load-decoupling system includes a fore end coupling bracket that is configured to attach to a fore end of the component. A first tie rod is coupled to the fore end coupling bracket. The first tie rod is configured to couple to a first portion of the primary structure. A second tie rod is coupled to the fore end coupling bracket. The second tie rod configured to couple to a second portion of the primary structure. A universal joint mount assembly is configured to couple to an aft end of the component and a third portion of the primary structure.

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: A lidding station for containers, including a conveyor structured and arranged for moving unrestrained containers in a conveyance direction; a lid infeed chute above said conveyor; and first, second and third compression rollers positioned above said conveyor and downstream of said lid infeed chute, and methods for affixing lids to containers.

Abstract: A method for constructing a packaging and displaying assembly utilizes a hand held punch or other punching device equipped with a specially designed template and a strip of card stock that is dimensioned to hold and display the item for sale. The template produces two cutouts in the top of the strip which is thereafter folded down to form a flap leaving upright a rounded tab with a centered opening. The item for sale may be affixed directly to the card stock under the flap or placed within a transparent envelope that is similarly affixed to the card stock. The resulting package with the item clearly visible is placed onto a display bar by threading the bar through the centered opening. The card stock may contain informative or decorative indicia to make the packages appealing for sale.

Abstract: Strapping tensioning tools are disclosed herein. The disclosed strapping tensioning tools reduce the forces that are required to be applied by an actuator (i.e., a motor) to release the tools from tensioned straps without damaging the straps. According to one aspect of the invention, the forces are reduced by the relative positioning, from front to back, of the cutter, the gripper and the windlass. According to a second aspect of the invention, the forces are reduced by reducing the angle formed between the gripper and the base of the tool. Namely, in one embodiment, the angle of the gripper relative to the strapping surface of the base is approximately 45-55 degrees.

Abstract: A method for handling and drying cardboard tubes is provided. The method involves using the skids for supporting cardboard tubes during the drying, wrapping and transport of the cardboard tubes, in order to reduce handling of the tubes while maintaining a low moisture level in the tubes.

Abstract: A process and apparatus can be used to vacuum skin package a product arranged on a support comprising providing a film portion above said support with the product being arranged between the support and the film portion; air tightly fixing the film portion to the support; removing at least a portion of air from a volume underneath said film portion through said at one nozzle inserted in an interspace between the film portion and the support.

Abstract: A medical vial filling system is adapted to fill a medical vial with a solution and cap the filled medical vial. A purging system includes a manifold disposed between a filling station and a capping station. The manifold includes a filling inlet port and a plurality of output ports. The output ports are positioned in a space proximate the filling station and in a space over the transport mechanism. A stoppering block includes a capping chamber for receiving a bushing positioned at the capping station. The stoppering block comprises a stoppering inlet port, a first nozzle opening into the capping chamber and a second nozzle extending into the capping chamber and directed into the medical vial when the medical vial is position in the capping station.

Abstract: A packaging apparatus comprising a base surface, in turn comprising a first end and a second end is disclosed. The packaging apparatus further comprises a feed tube between the first end and the second end of the base surface, a transporter between the first end of the base surface and the feed tube, a first sealer between the feed tube and the second end of the base surface, and a second sealer between the first sealer and the second end of the base surface.

Abstract: The invention relates to a processing device for foil pouches, comprising a plurality of pouch receiving elements arranged side by side, each of them being configured to receive and transport one foil pouch, a plurality of pairs of oppositely disposed ramps arranged successively in the direction of transport, the pouch receiving elements being transported in a guided manner along said ramps when in operation, the distance of oppositely disposed ramps defining the width of the pouch receiving elements, and an adjusting element configured to automatically adjust the distance transversely to the direction of transport between oppositely disposed ramps.

Abstract: A container and cap stores and measures material. A container has a cap removably attached to a double-walled container section. The cap has a housing between a base and a scale tray. The housing contains electronic components including a display, microcontroller, a sensor array and functional buttons. The scale tray includes a ring of LEDs that direct into the container section to sanitize and illuminate. The sensor array of the cap includes a scale transducer and humidity and temperature sensors. The container can be flipped over so the base on an underlying surface and so that the material the container falls down onto the scale tray, so the contents can be weighed. The cap can be removed and used as a stand-alone scale. The functions of the electronics can be controlled by an external devices, like a smartphone, through a software application.