Abstract: A rotor blade is provided. The rotor blade includes a blade portion, a tip cap formed to define a dimple, a fastener and a doubler. The fastener includes a flat-headed shaft and is disposable such that the flat-headed shaft extends through the blade portion and the tip cap at the dimple. The fastener is configured to urge the blade portion toward the tip cap. The doubler includes a dimpled portion disposable between the tip cap and a portion of the flat-headed shaft at the dimple and an exterior portion. The exterior portion is disposable flush with respective exterior surfaces of the blade portion and the flat-headed shaft.

Abstract: A ganged servo flight control system for an unmanned aerial vehicle is provided. The flight control system may include a swashplate having first, second, and third connection portions; a first control assembly connected to the first connection portion of the swashplate; a second control assembly connected to the second connection portion of the swashplate; and a third control assembly connected to the third connection portion of the swashplate. The first control assembly may include two or more servo-actuators connected to operate in cooperation with each other.

Abstract: A rotor actuation system includes a swashplate assembly comprised of a stationary swashplate and a rotating swashplate operatively connected together for relative rotation about a rotor axis. A cyclic actuator is operatively connected to the stationary swashplate to tilt the swashplate assembly off axis from the rotor axis for cyclic control. A collective actuator is operatively connected to the swashplate assembly to move the swashplate axially along the rotor axis for collective control. The cyclic actuator and the collective actuator are operatively connected to the swashplate assembly to respectively actuate cyclic and collective control independent of one another.

Abstract: The invention relates to an aircraft comprising a fuselage (1), a plurality of propeller units (3) that can pivot in relation to the fuselage (1), and wings (5) that can pivot at least partially in relation to the fuselage (1) and independently of the propeller units (3).

Abstract: Systems, methods, and devices are provided that combine an advance vehicle configuration, such as an advanced aircraft configuration, with the infusion of electric propulsion, thereby enabling a four times increase in range and endurance while maintaining a full vertical takeoff and landing (“VTOL”) and hover capability for the vehicle. Embodiments may provide vehicles with both VTOL and cruise efficient capabilities without the use of ground infrastructure. An embodiment vehicle may comprise a wing configured to tilt through a range of motion, a first series of electric motors coupled to the wing and each configured to drive an associated wing propeller, a tail configured to tilt through the range of motion, a second series of electric motors coupled to the tail and each configured to drive an associated tail propeller, and an electric propulsion system connected to the first series of electric motors and the second series of electric motors.

Abstract: An aircraft includes a fuselage, a wing, a ducted fan and a controller. The wing and the ducted fan are coupled to the fuselage. The controller is operable to control the aircraft in a vertical flight mode, a horizontal flight more, and transition the aircraft from the vertical flight mode to the horizontal flight mode.

Abstract: An aircraft includes a fuselage, a wing, a ducted fan and a controller. The wing and the ducted fan are coupled to the fuselage. The controller is operable to control the aircraft in a vertical flight mode, a horizontal flight more, and transition the aircraft from the vertical flight mode to the horizontal flight mode.

Abstract: Certain embodiments herein relate to location verification for autonomous unmanned aerial vehicles (also referred to as “drones”). In some embodiments, an unmanned aerial vehicle engaged in autonomous flight may determine its location using a satellite-based navigation system. The location may be evaluated against location data obtained from one or more secondary factors, such as public broadcast beacons, cellular towers, wireless network identifiers, visual markers, or any combination thereof. If the location is determined to be invalid, the unmanned aerial vehicle may be instructed to take a mitigation action. Additionally, certain embodiments also include the verification of a flight plan for the unmanned aerial vehicle using secure no-fly logic to verify a flight plan does not violate no-fly zones. If the flight plan is verified, the flight plan may be signed using a cryptographic signature and provided to a navigation module that verifies the signature and executes the flight plan.

Abstract: A drone launch system includes a canister defining an internal cavity, and a drone positioned within the internal cavity in a stowed state. The drone is configured to be ejected from the canister and transition from the stowed state into a deployed state outside of the canister. A method for launching a drone, the method includes positioning the drone in a stowed state in an internal cavity of a canister, ejecting the drone from the canister, and transitioning the drone into a deployed state after the ejecting operation.

Abstract: The invention relates to flying robots which can cover large distances between arrangements of smooth or curved surfaces without requiring manual redeployment. This reduces the need for personnel and allows fully-automated maintenance of large surfaces, for example, solar power stations. The flying robot consists of a drive unit having at least two rotors, and is attached to a cleaning module. This comprises a brush, as well as solar cells on one side, and electrodes for receiving current on the other. The flying robot is suitable for use on solar power station, both photovoltaic and photo-reflective. The design of the cleaning module allows the flying robot to charge itself using sunlight or undergo a quick charge using electrodes.

Abstract: Presently disclosed crew rest systems for an aircraft may provide an upper crew rest positioned in the crown portion of the aircraft and a lower crew rest positioned in the cargo area of the aircraft, with both the upper crew rest and the lower crew rest being accessible from a single entrance enclosure. Each of the upper crew rest and lower crew rest may include one or more bunks, or locations for a crew member to rest (e.g., lie down). Such crew rest systems may be customizable and/or modular, such that the number of bunks in the upper crew rest and/or lower crew rest may be selectively increased or decreased. In some examples, the lower crew rest may be selectively removable, and replaced with a cargo pallet or cargo container. Related methods of customizing such crew rest systems are also disclosed.

Abstract: An aircraft galley is provided, including a first galley unit that includes meal carts, cabinets and a countertop-height work area and a second galley unit that includes a countertop-height work area and a plurality of deployable crew seats and with the first galley unit defines a crew work/interaction area. A passenger interaction screen is positioned for viewing by passengers boarding the aircraft and passing through the galley into a passenger cabin. A plurality of lavatories are positioned in a like plurality of corners of the galley and having respective major walls positioned at an oblique angle to a longitudinal axis of the aircraft and with respective doors angled away from the crew work/interaction area.

Abstract: An aircraft table configuration includes a first table section and a second table section. The first and second table sections are hingedly connected along a first hinge line so that the second table section is configurable between a deployed, opened position and a folded, closed position. The first table section presents a first angled side and the second table section table presents a second angled side. The first angled side defines a first angle with respect to the first hinge line, and the second angled side defines a second angle with respect to the first hinge line. The first angled side and the second angled side are opposite to one another on either side of the first hinge line, wherein the first and second angled sides are adapted to define an aisle width in the aircraft. The aisle width does not change between the open position and the closed position.

Abstract: Disclosed herein is a hybrid mechanical/reactive pressure prevention system that includes a passive pressure control device operably coupled to a door that allows air within a pressurized vehicle to flow out of the pressurized vehicle. An event module detects a door event in the pressurized vehicle. The door event indicates that a door is not secure and air within the pressurized vehicle is being released through the passive pressure control device. An altitude module determines an altitude of the pressurized vehicle in response to detecting the door event. An electronic pressure control device one or more of reduces air inflow into the pressurized vehicle and increases air outflow out of an active pressure control device of the pressurized vehicle in response to the altitude of the pressurized vehicle being below a cutoff altitude.

Abstract: A cooling system in which an ACS (air cycle system) turbine may be driven by high pressure air from a turbo-fan engine and a VCS (vapor cycle system) having an evaporator and a VCS refrigerant compressor may be driven by the ACS turbine. Fluid of the chilled fluid reservoir, which may be chilled fuel, may be circulated through and cooled in the evaporator. In some embodiments, the ACS turbine may be coupled to the VCS refrigerant compressor by a magnetic coupling.

Abstract: An aircraft air conditioning system includes an air conditioning unit for the production of air conditioning air, which unit is connected to a pack air line, a recirculation air line adapted to be flown through with recirculation air and a mixing chamber, which is connected to the pack air line and the recirculation air line. An inlet line is connected to a connection on the aircraft for an aircraft-external air production unit and opens into the pack air line connecting the air conditioning unit to the mixing chamber. An air conditioning air line branches off from the pack air line between an opening point of the inlet line into the pack air line and the mixing chamber and is connectable to an aircraft area to be cooled.

Abstract: An anti-icing system for annular turbofan engine housings what include a substantially closed annular housing at a leading edge of the turbofan engine housing, the annular housing containing a quantity of air and a conduit extending from a source of high pressure hot gas to the annular housing. The system also includes an injector connected to the end of the conduit and extending into the annular housing; one or more nozzles extending outwardly from the injector in a direction that the quantity of air circulates in the annular housing while the turbofan engine is operating. The nozzles have an entrance in fluid contact with the injector and an exit, wherein a cross-sectional area of the entrance is less than a cross-sectional area of the exit such that gas leaving the nozzles is travelling slower than gas entering the nozzles.

Abstract: Systems and methods are provided for an inductive coil anti-icing and noise absorption system. In certain versions, the inductive coil anti-icing and noise absorption system may include an inductive coil and a skin. The inductive coil may generate electromagnetic fields and may electromagnetically couple with the skin. The skin, upon electromagnetically coupling with the inductive coil, may increase in temperature and the increase in temperature may melt or prevent the formation of ice on the skin. The skin or a portion of the skin may be porous and may allow incorporation of a sound absorbing liner. The sound absorbing liner may attenuate noise generated by the aircraft (e.g., noise generated by the aircraft engine). Certain versions may include a plurality of inductive coils and a plurality of skins.

Abstract: An impact protection apparatus is provided, comprising a gas container configured to hold a compressed gas and an inflatable member configured to be inflated by the gas and function as an airbag of a movable object, such as an aerial vehicle. A valve controls flow of gas from the container to the inflatable member in response to a signal from a valve controller. The valve and valve controller are powered by an independent power source than one or more other systems of the movable object. A safety mechanism may also be provided that, unless deactivated, prevents inflation of the inflatable member.

Abstract: An emergency evacuation assembly may comprise an inflatable slide, a soft cover containing the inflatable slide, a lace holding the soft cover closed, a pin retaining the lace, and a pneumatic actuator configured to release the lace by pulling the pin. In various embodiments, the pneumatic actuator may include a housing, a cylinder disposed within the housing, a plunger disposed within the cylinder, a seal disposed within the cylinder, and a spring disposed within the housing.

Abstract: A propulsion system coupled to a vehicle. The system includes a convex surface, a diffusing structure coupled to the convex surface, and at least one conduit coupled to the convex surface. The conduit is configured to introduce to the convex surface a primary fluid produced by the vehicle. The system further includes an intake structure coupled to the convex surface and configured to introduce to the diffusing structure a secondary fluid accessible to the vehicle. The diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid and secondary fluid.

Abstract: A propulsion system coupled to a vehicle. The system includes an ejector having an outlet structure out of which propulsive fluid flows at a predetermined adjustable velocity. A control surface having a leading edge is located directly downstream of the outlet structure such that propulsive fluid from the ejector flows over the control surface.

Abstract: An integrated propulsion system comprising at least two gas turbine engines, at least one fan, and a transmission assembly coupling the at least two gas turbine engines to the at least one fan wherein the at least two gas turbine engines are disposed within a main body of an airframe comprising the main body and a pair of wings, and wherein the number of gas turbine engines is greater than the number of fans.

Abstract: A system for providing regenerative power for an aircraft to sustain flight includes multiple energy cells disposed within the aircraft, the energy cells being configured to supply power to a propulsion motor and electronics of the aircraft, a fan generator harnessing propeller blast created by an aircraft propeller and converting kinetic energy of the propeller blast into electrical energy, a charger receiving the electrical energy generated by the fan generator and using the electrical energy to recharge one or more of the energy cells, and a power transfer switch selectively connecting one of the energy cells to the propulsion motor and electronics of the aircraft, such that the energy cells are rotated one at a time to power the propulsion motor and electronics. During recharging, the one or more of the energy cells are disconnected by the power transfer switch.

Abstract: A gas turbine engine mount for an aircraft wing including a link body having a first joint, a second joint and a linking structure connecting the first joint to the second joint. The linking structure includes at least a flexing portion and an elastic portion. The flexing portion is configured to flex during a load outside of an expected load window.

Abstract: An aircraft engine unit comprising an engine, a mast and an engine connection connecting the engine and the mast. The aircraft engine unit includes a front engine attachment of the engine connection which comprises at least one front rod connecting the primary structure of the mast and the core of the engine and which assures the take-up of vertical forces, and at least one connection connecting the primary structure of the mast and the fan casing of the engine and which assures the take-up of forces that are horizontal and perpendicular to the axis of rotation of the engine and/or a torque about the axis of rotation of the engine.

Abstract: A liquid storage system comprising: a tank for containing a liquid, the tank enclosing a liquid storage space; multiple layers of a fabric material; and attachment means attaching the multiple layers of the fabric material to an internal surface of the tank. The attachment means may comprise a non-permeable envelope attached to the internal surface of the tank. The multiple layers of the fabric material may be enclosed in the envelope such that the multiple layers of a fabric are isolated from a fluid in the tank. The envelope may contain a fluid (e.g. air) in addition to the multiple layers of the fabric material.

Abstract: An airframe having an integrated thermoelectric generator and a method thereof for providing electricity in an aircraft. A plurality of thermocouple wires is disposed about an aircraft frame to form a thermopile circuit in which electrical current is generated as a result of a temperature difference observed at a cruising altitude. The temperature difference is created by a hot side, interior to the aircraft frame, and a cold side, exterior to the aircraft frame. The thermopile circuit is formed by a first thermoelectric material and a second thermoelectric material that are selected to produce a desired voltage when exposed to the temperature difference. The electric current is harnessed by a transfer cable and directed to an aircraft electrical system to provide power to the desired devices.

Abstract: A ram air turbine system includes a rotatable shaft, a housing having a body defining an interior, a generator located within the interior and having a stator and a rotor, and a turbine having a first set of blades operably coupled with the rotatable shaft and configured such that airstream passing through the first set of blades rotates the shaft.

Abstract: An aeroplane attitude indicator device includes a mobile rod which includes a first end connected by a link to a support fastened to the aeroplane and a second end to which is connected a moving body, at least one actuator for controlling the motions of the rod, and a system for piloting the at least one actuator as a function of information originating from an attitude detection system of the aeroplane, so as to orient the rod in a vertical direction. The assembly of rod and moving body correspond to a pendulum-like artefact. Also described is an aeroplane cockpit equipped with an attitude indicator device.

Abstract: A helicopter stall warning method includes receiving an airspeed of the helicopter, determining a stall airspeed based on multiple factors associated with the helicopter, the multiple factors comprising ambient temperature near the helicopter, the helicopter's altitude, and the helicopter's gross weight, determining a stall warning threshold derived from the stall airspeed, and providing a tactile warning through a collective helicopter control when the helicopter's airspeed meets or exceeds the stall warning threshold.

Abstract: A method and system for alerting a pilot to a potential unanticipated LTE with simple intuitive symbology on the cockpit display is provided. The provided method and system evaluates rotorcraft airspeed, wind velocity, wind direction, and rotorcraft height above ground to predict several scenarios for LTE zones. The provided method and system overlays or superimposes simple intuitive symbology on the existing PFD and/or MFD to alert a pilot to a potential LTE.

Abstract: An apparatus for determining the position of an object having one or more magnetic elements. The apparatus includes magnetostrictive optical sensors, each arranged to produce a signal which is indicative of a proximity of the sensor to the one or more magnetic elements. The apparatus is arranged to determine the position of the object based on a plurality of such proximity signals.

Abstract: A porthole, a porthole plug in a vehicle, and an aircraft with portholes are provided. The porthole includes an opaque plug with an aperture therethrough. A camera is arranged with a lens aligned with the aperture.

Abstract: Systems, methods, and apparatus for space surveillance are disclosed herein. In one or more embodiments, the disclosed method involves scanning, by at least one sensor on at least one satellite in inclined super-geostationary earth orbit (super-GEO), a raster scan over a field of regard (FOR). In one or more embodiments, the scanning is at a variable rate, which is dependent upon a target dwell time for detecting a target of interest. In at least one embodiment, the target dwell time is a function of a range from at least one sensor to the target of interest and a function of a solar phase angle. In some embodiments, the axis of inclination of the inclined super-GEO is a function of the solar phase angle.

Abstract: Systems, methods, and apparatus for space surveillance are disclosed herein. In one or more embodiments, the disclosed method involves scanning, by at least one sensor on at least one satellite in super-geostationary earth orbit (super-GEO), a raster scan over a field of regard (FOR). In one or more embodiments, the scanning is at a variable rate, which is dependent upon a target dwell time for detecting a target of interest. In at least one embodiment, the target dwell time is a function of a characteristic brightness of the target.

Abstract: A device for maneuvering and immobilizing an aircraft on the ground. Included in the device is a moving apparatus and a remote control configured for remotely controlling the moving apparatus. The device allows a coupling of a single remote control with several moving apparatuses and/or of one moving apparatus with several remote controls. Also, the device allows an operator equipped with a remote control to remotely control several pushback maneuvers by successively using several moving apparatuses or several operators each equipped with a remote control to successively control the same moving apparatus.

Abstract: A secure automated baggage/parcel handling system with the aim of eliminating or minimize use of man power for baggage/parcel handling and easily adapt to airport or any baggage/parcel handling organization's process. The system is adapted of 4 main systems capable of functioning of manually and automatically up and downloading, transporting and stocking baggage/parcel from one location to the other location(s). This system is comprises of: 1. A Baggage Transport Vehicle comprises robot, conveyor, laser measurement and optical reader is capable to up and download baggage/parcel from one location to the other location(s) and to recognize the baggage/parcel's size and shape. 2. A baggage/parcel transfer cart to transfer large number of the baggage/parcel capable of navigating from one location(s) to the other location(s) manually or automatically or pulled by baggage transport vehicle. 3.

Abstract: A method includes receiving a reference design at a computing device. The reference design includes first geometrical information associated with a first set of composite materials to form a reference surface. The method includes receiving second geometrical information at the computing device. The second geometrical information is associated with a second set of composite materials associated with a second design. The method includes determining, based on a comparison of the first geometrical information and the second geometrical information, an offset surface relative to the reference surface. The method further includes generating a model of a surface of the second design based on the reference surface and the offset surface.

Abstract: A method and apparatus for ply blending. A desired thickness and a desired stiffness distribution for a composite structure are received. A model of the composite structure is split into a plurality of panels. Lamination parameters and a quantity of plies for each panel of the plurality of panels are determined using the desired thickness and the desired stiffness distribution for the composite structure. Ply shapes for each ply of the plurality of panels are determined using an objective function. A fiber angle is determined for each ply of the plurality of panels. Each ply of a first half of a panel of the plurality of panels has a different fiber angle value than each other ply of the first half of the panel.

Abstract: A pump health monitoring system for an aircraft fuel pump. The health monitoring system compares environmental data to a reference environment and captures pump data when the environmental data matches the reference environment. The pump data captured is therefore normalised to the reference environment. A pump remaining useful life is calculated from the normalised pump data.

Abstract: Methods and apparatuses are disclosed relating to multilayer 3D textile composite materials containing self-healing resins for use as protective structures on stationary objects, and moving objects including, without limitation, vehicles including spacecraft and aircraft.

Abstract: A side-by-side dual-launch spacecraft arrangement is provided. The arrangement may include a first and second spacecraft mounted within a fairing. The first and second spacecraft may be mounted side by side on the dual-launch adaptor. A ratio of a first lateral dimension of the GEO spacecraft to a second lateral dimension of the GEO spacecraft may be within a range from 0.55 to 0.8, with the first lateral dimension and the second lateral dimension being perpendicular to each other and smaller than a height of the GEO spacecraft.

Abstract: A device for dispensing an ingredient in the context of a process of preparation of a mixture for making a food product includes a structure for loading the ingredient and control means for controlling the flow of the ingredient from the loading structure to a structure for receiving the ingredient. An optical sensor in the range of visible light, is designed to detect an optical parameter of the aforesaid ingredient. A control unit is configured for governing the aforesaid control means on the basis of the signal received from the sensor.

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

Abstract: Clipper assemblies include a clipper body with a die support holding at least one clip die; and a knife cylinder with a downwardly extending rod, the knife cylinder attached to the clipper body above the clip die. The clipper assemblies also include a knife plate having a body with a perimeter with a first portion pivotably attached to the rod and a second portion pivotably attached to the clipper body below the clip die. The knife plate holds a knife which extends outward from a side of the knife plate a distance between about 1-2 inches, at an angle of between 80-110 degrees (measured from a line drawn parallel to the side from which the knife extends outward from). In operation, the knife is configured to either: (a) move upward to cut respective clipped packages or (b) move downward to cut respective clipped packages.

Abstract: A wrapping apparatus employing plastic stretching film for items to be wrapped has entry lines and exit lines, which define a horizontal feeding line, in the proximity of a wrapping station (W) provided with a drive ring apt to bring into rotation a reel of the stretching film around the feeding line, and a holding gripper apt to temporarily hold an initial edge of said film in a starting step of the rotation of said reel. A temporary retaining device of said film provided with an elongated hollow member arranged with the longitudinal axis thereof parallel to the feeding line and having an inner side.

Abstract: A hand-held cable tie tensioning and severing tool including a gripping mechanism having a pawl and a pawl hood, wherein the underside of the pawl hood is provided with a texture pattern.

Abstract: An article selection and packing system includes at least two article housing stations and a composite article housing station spaced from the at least two article housing stations. A boom extends over the at least two article housing stations and the composite article housing station. A selection and packing assembly extends between the at least two article housing stations and the composite article housing station. The selection and packing assembly includes at least two telescoping shuttles, the at least two telescoping shuttles are movably coupled along the boom. At least two grasping assemblies coupled with the at least two telescoping shuttles, respectively. The at least two grasping assemblies are each configured to withdraw one or more articles from the at least two article housing stations, respectively, and pack the withdrawn one or more articles together at the composite article housing station.

Abstract: The present invention relates to a vacuum packaging machine bag storing and cutting device. The device comprises a bag storing box body and a bag storing box cover; a cavity for putting storing bags is arranged in the bag storing box body; baffle plates for axially fixing the storing bags are arranged in the cavity; connecting grooves in detachable connection with a vacuum package machine are arranged in a front side surface of the bag storing box body; a turnover bag storing box cover is connected to a rear side surface of the bag storing box body; and a bag cutter is arranged on the bag storing box cover. A structure detachable from the vacuum package machine is adopted in the bag storing and cutting device of the present invention, so that the structure of the vacuum package machine is simplified and has a reduced volume.