Abstract: Methods and apparatus for controlling aircraft flight control surfaces are disclosed. An example apparatus includes a flight control surface controller to move a control surface of an aircraft to a target position via at least one of a first actuator or a second actuator associated with the control surface based on a command input received by the flight control surface controller. The flight control surface controller to: obtain a flight characteristic of the aircraft; compare the flight characteristic to a flight characteristic threshold; in response to a first comparison result, cause the first actuator to move the control surface to the target position based on the command input without moving the second actuator; and in response to a second comparison result, cause the first actuator and the second actuator to move the control surface to the target position based on the command input.

Abstract: A landing gear is disclosed having a main strut connected at one end to an aircraft via a main joint is disclosed. The landing gear further includes an inboard sidestay assembly connected to the main strut. The inboard sidestay assembly includes a forward stay connected at one end to the aircraft, a rear stay connected at one end to the fuselage, and a shear web extending between the forward stay and the rear stay and configured to resist movement of the forward stay relative to the rear stay. The landing gear is arranged such that when the landing gear is extended substantially all the landing gear loads are transferred from the landing gear to the aircraft via one or more of the main joint, the forward stay and the rear stay.

Abstract: A landing gear controller (120) to control extension and retraction of a landing gear for an aircraft, the landing gear controller (120) configured to cause, during an aircraft take-off or landing procedure, a landing gear extension and retraction system (110) to perform only a first portion of a landing gear extension or retraction process, on the basis of a status of the aircraft and prior to receiving a command for the landing gear to be extended or retracted.

Abstract: Embodiments refer generally to systems and methods for providing autorotative enhancement for helicopters using an autorotative assist unit coupled to the transmission of the helicopter. Methods of utilizing an autorotative assist unit as well as retrofitting an autorotative assist unit to an existing helicopter are also disclosed. By employing an autorotative assist unit, improved autorotation can be achieved without the need to increase the weight of the rotor.

Abstract: The present invention includes a balancing system that includes a weight box, mounted substantially within the rotor-blade spar, flush with a rotor-blade spar outer surface, operably accessible from a rotor-blade tip, and retained within the rotor-blade spar by a weight-box retention pin, one or more weight-box contact surfaces bonded to a rotor-blade-spar inner surface, or a weight-box lip providing a bearing contact with an edge of a spar rotor-blade spar cutout; and a weight package attached to the weight box, the weight package including a weight-box cover, two or more weight guide-rods attached to the weight-box cover, wherein one of the two or more weight guide-rods is positioned forward of a pitch change axis or center of twist and wherein one of the two weight guide-rods is positioned aft of the pitch change axis or center of twist, and one or more balance weights mounted on the weight guide-rods.

Abstract: In one embodiment, an apparatus comprises a shaft, a rotor, and a cam surface. The shaft comprises a spiral spline along a length of the shaft. The rotor comprises a blade extending from the rotor and a tubular hole extending into the rotor. The tubular hole comprises a spiral groove configured to mate with the spiral spline on the shaft. Relative rotation between the spiral spline and the spiral groove causes the rotor to linearly move along the shaft. The cam surface comprising a recession. The blade nesting in the recession to constrains rotation of the rotor about the shaft and allows linear movement of the rotor along the shaft.

Abstract: A variable-solidity propeller apparatus, comprising a propeller having at least one rotatable hub carrying at least one row of propeller blades, wherein the propeller has a first configuration in which the propeller has a first average solidity, and a second configuration in which the propeller has a second average solidity which is greater than the first average solidity.

Abstract: An apparatus for connecting a number of rotary blade unmanned aerial vehicles (UAVs) is described. The apparatus includes a first physical connector, a first electrical connector, a second physical connector, a second electrical connector, a storage area, and a UAV control unit. The first physical connector attaches the apparatus to a first UAV. The first electrical connector connects electricity between the apparatus and the first UAV. The second physical connector attaches the apparatus to a second UAV. The second electrical connector connects electricity between the apparatus and the second UAV. The storage area stores an energy source for the apparatus. The UAV control unit includes a processor and storage medium. The processor and storage medium are in communication with a cloud based network and receive instructions for the operation of the UAV, including steering instructions, through the cloud based network from a remote control device.

Abstract: A modular unmanned aerial system includes a chassis for attaching components of the modular unmanned aerial system and one or more rotary wings. Each of the one or more rotary wings is drivable by a respective motor. A central controller is provided for controlling operation of the modular unmanned aerial system. A modular interface portion attached to the chassis and adapted for removably mounting one or more modular devices.

Abstract: A system for controlling an unmanned aerial vehicle (UAV) includes a first user interface configured to receive a first user input and a second user interface configured to receive a second user input. The first user input provides one or more instructions to effect an autonomous flight of the UAV. The second user input provides one or more instructions to modify the autonomous flight of the UAV, The autonomous flight includes a flight towards a target.

Abstract: An unmanned aerial vehicle includes a fuselage and a power supply assembly arranged at the fuselage. The power supply assembly includes a polyhedron mounting bracket arranged at the fuselage, a power supply device arranged at the fuselage, and at least two functional circuits arranged separately on different outer surfaces of the mounting bracket and electrically coupled to each other and to the power supply device.

Abstract: In a first aspect, there is a personal air vehicle including a body having a forward portion, a central portion and an aft portion; a first ducted fan supported by the forward portion of the body; a second ducted fan supported by the aft portion of the body; and third and fourth ducted fans supported by the left and right sides of the body and pivotable relative to the body. An aspect provides a method of flying the personal air vehicle.

Abstract: A blended wing body aircraft having an interior cabin with a usable volume of at most 4500 ft3 and a cabin aspect ratio of at most 4, wherein a combination of the wings and center body has a wetted aspect ratio of at least 1.7 and at most 2.8. Also, a blended wing body aircraft having an interior cabin with a usable volume of at least 1500 ft3 and at most 4500 ft3 and a cabin aspect ratio of at least 2 and at most 4, wherein a combination of the wings and center body has a wetted aspect ratio of at least 1.9 and at most 2.7. Also, a blended wing body aircraft wherein at least each profile section having normalized half-span values from 0 to 0.3 has a leading edge having a normalized height having a nominal value within the range set forth in Table 4.

Abstract: A blended wing body aircraft wherein at least each profile section corresponding to the normalized half-span values from 0 to 0.2 has a thickness ratio having a nominal value within the range set forth in Table 1. Also, a blended wing body aircraft wherein at least each profile section corresponding to the normalized half-span values from 0.15 to 0.3 has a normalized chord having a nominal value within the range set forth in Table 1, and wherein a ratio between a maximum thickness of the center body and the chord length along the centerline has a nominal value of at least 16%. Also, a blended wing body aircraft wherein a region of the aircraft defined by normalized half-span values from 0.1 to 0.2 has a normalized chord having a dimensionless rate of change from ?3.5 to ?5.1, and a thickness ratio having a rate of change from ?0.27 to ?0.72.

Abstract: An aircraft (2) comprising a launch tube (14) extending along at least part of a length of a wing of the aircraft (2),and through which an item (24) may be launched from the aircraft (2). The launch tube (14) comprises an opening (22) at a distal end of the wing (6).

Abstract: An aircraft region comprising an aisle section extending in a longitudinal direction of the aircraft region, a bench seat oriented transversely with respect to the longitudinal direction and having a first seat adjacent to the aisle section and a second seat arranged remote from the aisle section, and an aircraft stowage bin system having a first stowage bin arranged at least in part above the first seat and a second stowage bin arranged at least in part above the second seat. The first stowage bin has a first rear side facing away from the aisle section, and the second stowage bin has a second rear side facing away from the aisle section. The second stowage bin is arranged above the second seat such that it is accessible for a person sitting on the second seat or standing in the longitudinal direction in front of the second seat.

Abstract: A seat, including a seat bottom for which a seat frame is supported by a base, and a seat back, the seat including a “seated” position, a “lying” position and an intermediate “resting” position. A seat plate can be moved in rotation around a rear axis located at the side of a rear edge of the seat, the seat plate being movable in rotation around a tilting axis in front of the rear axis, the seat frame is moved forward during conversion from the “seated” position to the “lying” position. An essentially horizontal rear segment. An intermediate rear segment with a downward slope greater than the slope followed by the tilting axis. An intermediate front segment with an essentially horizontal upward slope.

Abstract: An environmental control system includes a pair of parallel operating environmental air compressors (EACs) that receive a first outside air, wherein each EAC includes a respective EAC compressor and EAC turbine. A first regenerative heat exchanger is downstream of the EAC compressors and upstream of the EAC turbines, wherein the first regenerative heat exchanger receives environmental air from an enclosure for occupants. A primary heat exchanger is downstream of the first regenerative heat exchanger, wherein the primary heat exchanger receives a second outside air. An air cycle machine (ACM) is downstream of the primary heat exchanger. A condenser is downstream of the ACM, wherein a conditioned air exits the condenser and into the enclosure. A water extractor is downstream of the condenser. A reheater is downstream of the water extractor and upstream of the ACM. A secondary heat exchanger is downstream of the ACM, wherein the secondary heat exchanger receives the second outside air.

Abstract: A pneumatic deicer assembly includes a first stretch fabric with a first edge opposite a second edge. The first edge is positioned proximate the second edge such that the first stretch fabric forms a tube. A non-stretch fabric covers a seam formed between the first edge and the second edge of the first stretch fabric. A second stretch fabric covers the non-stretch fabric and a portion of the first stretch fabric.

Abstract: An unmanned aerial vehicle is provided, including a primary operation system in communication with a primary state estimator. The primary operation system is configured to operate the unmanned aerial vehicle based in part on the primary state estimator. The vehicle includes a flight failure recovery system in communication with a recovery state estimator and the primary operation system. The flight failure recovery system is configured to determine, at a first time, that flight failure has occurred. The flight failure recovery system is configured to determine a suitable second time to generate a deploy signal for a parachute based at least in part on one or more signals from the recovery state estimator. There is a delay between the first time and the suitable second time. An intelligent emergency parachute deployment system for, and a method for flight failure recovery of an unmanned aerial vehicle are also provided.

Abstract: An aircraft, such as an unmanned aerial vehicle or a small-sized manned aircraft, can be hybrid-powered by fuel engines and electric motors. In various embodiments, such an aircraft can include both of rotors and fixed wings, and can perform vertical take-off and landing like a helicopter and level flight like a fixed-wing aircraft.

Abstract: A system for mounting an engine to an aircraft includes an engine forward mount angled toward the forward end of the engine at a first angle. At least two thrust links extend between an engine aft mount to a link support connection at a second angle. The engine aft mount is angled toward the forward end of the engine at a third angle. A projection of a load vector of the engine forward mount onto a vertical plane extending through the axis of rotation of the engine and a projection of a load vector of each of the at least two thrust links onto the vertical plane intersect the axis of rotation of the engine within a first vertical plane segment extending between a forward end of a nose of a fan assembly and forward of a forward mount interface.

Abstract: An aircraft is described that has: at least one primary engine configured to operate when the aircraft takes-off, lands, and cruises in a cruise mode; and at least one secondary engine configured to operate when the aircraft takes-off and lands. The drag of the aircraft can be reduced or minimized by: turning off the at least one secondary engine when the aircraft cruises in the cruise mode; opening cowlings covering the at least one secondary engine when the aircraft takes-off and lands, and closing them when the aircraft cruises in the cruise mode; and/or move the at least one secondary engine into the airstream when the aircraft takes-off and lands, and move the at least one secondary engine out of the airstream when the aircraft cruises in the cruise mode. Related apparatuses, systems, methods, techniques, and articles are also described.

Abstract: A hinge assembly may include a support structure and a panel hingedly coupled to the support structure via at least one hinge of a plurality of hinges. The plurality of hinges may include a first hinge having a first rotational axis, a second hinge having a second rotational, and a third hinge having a third rotational axis. The second rotational axis may be collinear and aligned with the third rotational axis such that the second hinge and the third hinge have a shared concentric axis. The first rotational axis may be eccentric to the shared concentric axis. The hinge assembly may be implemented in a nacelle to improve the aerodynamics of the interfaces between the fan cowl and adjacent structure.

Abstract: A nacelle may include fan cowl panels which may be opened to provide access to the fan case. A self-locking latch may automatically lock when the fan cowl panels are closed. A manual release button may disengage the self-locking latch in order to open the fan cowl panels.

Abstract: A nacelle may include a pylon, an adjustable length beam, a first fan cowl, and a second fan cowl. The adjustable length beam may have a first end and a second end and the adjustable length beam may extend in a direction substantially normal to a centerline axis of the nacelle. The first fan cowl may be pivotally coupled to the first end of the adjustable length beam and additionally may be pivotally coupled to the pylon. The second fan cowl may be pivotally coupled to the second end of the adjustable length beam and additionally may be pivotally coupled to the pylon.

Abstract: One example of a cowling assembly for a rotorcraft includes a stationary fairing affixed to an airframe of the rotorcraft, an articulated fairing hinged on the stationary fairing for articulation relative to the stationary fairing between a closed position, a first partially open maintenance position and a second fully open maintenance position. The articulated fairing is supported in the first maintenance position by a for example gas-charged strut and is releasably locked in the second maintenance position against the stationary fairing by a locking mechanism. The locking mechanism includes a latch blade disposed on the stationary fairing and a latch arranged on the articulated fairing, wherein a latch pin engages with a hole or recess in the latch blade when the latch blade extends through a slot in the articulated fairing.

Abstract: According to one or more aspects, a control system for managing operational limits associated with two or more actuators includes a controller. The controller may continually monitor a first operational limit associated with a first actuator and a first operational limit associated with a second actuator. The controller may determine a first overall distributed control system operating limit based on the first operational limit associated with the first actuator, the first operational limit associated with the second actuator, and a type of operational limit associated with both operational limits.

Abstract: In one embodiment, there is described an inlet plenum assembly for a rotary aircraft, including: an inlet plenum defined on a first side by an inlet plenum wall and on a second side by a forward firewall assembly; the inlet plenum wall having a mechanical interface for receiving a reduction gearbox (RGB) to provide reduction gearing to the drive shaft; and the forward firewall assembly having an inlet aperture configured to receive a drive shaft to rotatably couple to an engine; wherein the forward firewall assembly includes a forward firewall upper and a forward firewall lower, the forward firewall upper configured to removably seat to the forward firewall lower.

Abstract: An air inlet (3) for a nacelle (2) for an aircraft (1) includes at least one acoustic panel (5), adapted to lower noise generated by the engine (21) to which the air inlet (3) is connected. At least one lip (6) defines the profile upon which an airflow flowing into the air inlet (3) acts. If necessary, at least one engine ring (4) is adapted to allow the air inlet (3) to be connected to an engine (21) of the nacelle (2). If necessary, at least one outer barrel (7) is adapted to define the outer shape of the air inlet (3) upon which an airflow acts. The air inlet (3) is manufactured as one single piece, made of a composite material.

Abstract: Techniques are disclosed for cooling an unmanned aerial vehicle (UAV). In some examples, a heat sink is coupled to a portion of the UAV that is to be cooled. One or more heat pipes are coupled to the shim, and extend to one or more propulsion engines of the UAV. Liquid in a heat pipe is heated to gaseous form at the heat sink, and the vapor travels to a portion of the heat pipe near the propulsion engine, where the vapor is cooled by air moved by the propulsion engine, upon which the vapor returns to liquid form and travels back to the heat sink.

Abstract: The present invention includes a rotorcraft drive system, method, and aircraft comprising a fixed engine; a rotating spindle that rotates a proprotor gearbox and rotor pylon between a hover and forward flight position, wherein the rotating spindle rotates about a rotation bearings on two inboard ribs of a wing member; and an interconnect drive shaft connected to the fixed engine, wherein the interconnect drive shaft passes through an aft cove of the wing member and connects to the engine via a forward-aft drive shaft, wherein the forward-aft drive shaft is connected to the proprotor gearbox to provide power to a proprotor.

Abstract: A first DC power supply section of a DC stabilization power supply system includes at least a generator and a PWM converter. A second DC power supply section of the DC stabilization power supply system includes at least a battery and a boost converter. Each of these DC power supply sections performs a power supply stabilization operation for supplying DC power to an electric system and absorbing regenerative power generated from an actuator or the like. A PWM converter controls adjustment of the amount of the power supply stabilization operation to be performed by the DC power supply section and the amount of the power stabilization operation to be performed by the DC power supply section, by changing a target voltage value of a DC bus.

Abstract: A lightning protection system of an aircraft includes a wall defining an inner surface and an outer surface. The outer surface is configured to come into contact with a mass of air located around the aircraft. The lighting protection system also includes at least two electrically conductive lighting traps received in holes traversing the wall and at least one strip with pellets having an electrically insulating substrate and electrically conductive pellets spaced apart from one another on the electrically insulating substrate. The strip with pellets is fastened on the wall by the two lightning traps. The strip with pellets is attached on the inner surface of the wall.

Abstract: An imaging device can be mounted on a vehicle and used to capture images. The imaging device can include a camera assembly rotatable relative to a platform of the vehicle and about two or three camera axes. The camera assembly can include a camera and a mirror attached to the camera. The mirror can be rotatable relative to the camera and about one or two mirror axes, different from the camera axes. Users can provide input to controllers that operate the vehicle, the camera, and the mirror to control both flight and the line-of-sight of the camera. The controllers combine separate inputs as well as measured conditions, such as inertial angles, to coordinate control of vehicle, camera, and mirror parameters, such as yaw adjustments to both the camera and the mirror to achieve a desired line-of-sight.

Abstract: A modular sensor platform is provided for installation on an unmanned aerial vehicle (UAV) for sensor operation. The platform includes an external shell that defines an internal volume, an interface module, and a mission module. The shell inserts between sections of the UAV. The interface module attaches to the shell within the volume. The mission module attaches to the shell within the volume. The interface module includes a communications package, a battery package and an air intake.

Abstract: A method for controlling a movable object includes receiving a user input indicative of a command to adjust a perception of a target while tracking the target, determining a subsequent perception of the target based on the user input, and generating one or more control signals to move the movable object based on the subsequent perception of the target.

Abstract: An airport lighting system includes one or more lighting elements, a transient protection apparatus, and one or more electrical control cabinets. The transient protection apparatus is coupled to the one or more lighting elements. One or more electrical control cabinets are coupled to the transient protection apparatus. Each of the control cabinets produces one or more of control and power signals that are effective to operate the one or more lighting elements. The transient protection apparatus is configured to provide protection for one or more of the electrical control cabinets and the one or more lighting elements from electrical surges.

Abstract: The invention relates to a method by means of which an unmanned transport device (3) docked on a receiving container (1) is loaded with a payload container (7) for a consignment (4), having a loading device (8) for loading the transport device (3) with the payload container (7), wherein the payload container (7) has a bearing means (9) at its first end (8a), the transport device (3) has a loading opening (6) on its underside (5) for receiving the payload container (7), and the loading opening (6), at its front end (19), has a mating contour (20) corresponding to the bearing means (9), and the method has the following steps: the payload container (7), arranged on the loading device (8), is pivoted in relation to the horizontal by the loading device (8) such that the first end (8a) is elevated in relation to a second, opposite end (14) of the payload container (7), the loading device (8) is raised until the payload container (7) ends up at least with its first end (8a) located within and/or beneath the loading

Abstract: A ground station device for a plurality of unmanned aircraft, comprising an upper face, which comprises a plurality of receptacles for positioning a plurality of unmanned aircraft, a data interface for connecting the ground station device to a control unit, and a power supply device for charging the unmanned aircraft. The ground station device is designed to be stackable so as to form a stack with at least one other ground station device.

Abstract: A method for lifting a wing of an aircraft. A plurality of lifting assemblies is attached to a mounting ring supporting the wing. A first plurality of base assemblies is attached to a plurality of fittings connected to the fuselage of the aircraft. The plurality of lifting assemblies is moved away from the first plurality of base assemblies using a plurality of biasing systems correspondingly attached to the plurality of lifting assemblies, the moving causing the mounting ring to move away from the fuselage. The first plurality of base assemblies is removed. A second plurality of base assemblies is attached to the plurality of fittings. Thereafter, moving the plurality of lifting assemblies away from the second plurality of base assemblies using the plurality of biasing systems is repeated, the repeating moving causing the mounting ring to move away from the fuselage to the first height.

Abstract: The present disclosure relates to aircraft and aircraft flight control systems, methods, and apparatuses. A condition-aware aircraft configured to make in-flight decisions autonomously, based on the most up-to-date information, to perform missions under dynamic conditions, while also providing in situ feedback to maintenance units and depots in order to coordinate required and upcoming maintenance.

Abstract: This disclosure describes various techniques and systems for rapid low-cost access to suborbital and orbital space and accommodation of acceleration of sensitive payloads to space. For example, a distributed gas injection system may be used in a ram accelerator to launch multiple payloads through the atmosphere. Additionally or alternatively, multiple projectiles may assemble during flight through the atmosphere to transfer and/or resources to another projectile.

Abstract: A system for vibration control of a cryocooler that cools an imager. The system includes a vibration sensor that is physically affixed to the cryocooler. The vibration sensor senses a physical vibration of the cryocooler and to generates a vibration signal therefrom. The system also includes cryocooler drive electronics operatively coupled to the vibration sensor and the cryocooler. The cryocooler drive electronics output a drive waveform that drives the cryocooler so as to reduce the vibration impact of the cryocooler. The harmonic content of the cryocooler drive waveform is controlled by the cryocooler drive electronics based on the vibration signal.

Abstract: An apparatus including: a plurality of forming molds, each mold including: a leading edge; a trailing edge; a mold face; a plurality of first recesses in the mold face positioned across the mold face, each first recess in fluid communication with a first vacuum duct; a leading face extending from the leading edge in a direction away from the mold face; a trailing face extending from the trailing edge in a direction away from the mold face; wherein at least a portion of the leading face is recessed relative to the mold face proximal the leading edge or at least a portion of the trailing face is recessed relative to the mold face proximal the trailing edge; wherein the plurality of forming molds is arranged leading edge to trailing edge as a first mold belt.

Abstract: Embodiments disclosed herein include needle-free syringe and cap assemblies and filling tub systems. One embodiment of filling tub system includes a filling tub having exterior walls and a floor. The floor is formed into a plurality of sockets configured to receive and support a plurality of cap and syringe body assemblies, with each cap and syringe assembly received in a separate socket. Furthermore, each socket is configured to receive and support a syringe and cap assembly with contact only between one or more surfaces of the socket and selected outer surfaces of the cap. Methods of pre-filling a quantity of needle-free syringes are also disclosed.

Abstract: In order to accomplish the objects of the present invention, there is provided a method for filling containers with fluids. A method provides a container made of an elastic material, the container having an internal chamber and a neck with an opening. A plug is provided inside the chamber, the plug having a buoyancy that allows it to float when fluid is introduced into the chamber. A fluid is introduced into the chamber, causing the plug to float until the plug enters the neck and seals the neck.

Abstract: A method for reverse-filling cosmetic material having an irreversible property and a cosmetic container filled therewith, including the steps of: sealing the top part of the cosmetic inner container, the top and bottom of which are open, with a filling mold, and turning the cosmetic inner container upside down to reverse-position the cosmetic inner container so that the sealed top part of the cosmetic inner container is directed downward and the open bottom part thereof is directed upward; and filling the cosmetic inner container through the bottom part thereof with the cosmetic material. In so doing, the top surface of the cosmetic material filled in the cosmetic container is smooth without any bumps, moisture seepage phenomenon is prevented, and cosmetic material having excellent applicability can be provided as the hardness thereof is relatively low by reverse-filling the cosmetic container with cosmetic material having an irreversible property, such as agar.

Abstract: A sealing system is for containers, in particular of the type that envisages sealing with an aluminum cap. Forming equipment (12) of a cap or seal (0) of weldable sealing material (S) is for the application on the mouth of a container (B), the equipment (12) including a service portion (12a) outside a controlled atmosphere chamber (2) and an operating portion (12b) inside the controlled atmosphere chamber (2). The operating portion (12b) includes a positioning roll (29) which is tangential, in the direction of rotation of the positioning roll (29), with a cutting roll (30) adapted to cut a sheet of sealing material (S) from a web of the sealing material (S) and with a forming roll (31) adapted to shape the sheet of sealing material (S) in the cap or seal (O).

Abstract: A non-woven fabric comprising bicomponent fibers. The non-woven fabric has a core containing polylactic acid (PLA-1), coated with an envelope containing polylactic acid (PLA-2). The fibers are characterised in that PLA-1 is a copolymer of lactic acid monomers L1 and lactic acid monomers D1, and PLA-2 is a copolymer of lactic acid monomers L2 and lactic acid D2, whose D2 monomers rate is greater than the monomers rate D1 of PLA-1. The core further contains a polymeric plasticizer. The non-woven fabric may be used for making coffee filters and/or capsules via a thermoforming process for use in a percolating apparatus.