Abstract: The subject matter of this specification can be embodied in, among other things, a control apparatus includes a first mounting member, an elongate member having a first elongate portion, a second elongate portion, a first axis member between the first elongate portion and the second elongate portion, pivotally mounting the elongate member to the first mounting member and defining a first axis, a track configured as an arc defined about the first axis, and a first feedback assembly supported upon the second elongate portion and providing a first interface device configured to travel along the track in response to movement of the second elongate portion partly about the first axis, wherein the mass of the second elongate portion and the first feedback assembly substantially offsets the mass of the first elongate portion about the first axis member.

Abstract: Yoke alignment assemblies, aircraft, and rigid covers are provided. An aircraft includes a yoke alignment assembly. A yoke alignment assembly is provided for aligning an aircraft yoke with a column. The yoke alignment assembly includes a rigid cover and a flexible cover. The rigid cover defines a protective portion configured to protect the yoke. The inclinometer portion is configured to hold an inclinometer. The flexible cover is secured to an upper part of the protective portion and is configured to protect the yoke.

Abstract: The present disclosure provides methods and system for managing gust loading in an aircraft. A deflection angle of one or more spoilers of the aircraft is monitored. When the spoiler deflection angle is above a first threshold value, one or more aileron control signals are sent to the ailerons. The aileron control signals cause the ailerons to deflect based on the spoiler deflection angle.

Abstract: A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a reoriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value.

Abstract: An ice protection assembly on an airfoil includes a heater positioned on the leading edge, and one or more ice phobic layers positioned to inhibit runback ice formation on the surface of the airfoil downstream of the heater.

Abstract: An aspect provides a skid landing gear assembly including a cross member disposed between a first skid tube and a second skid tube, and a tension cable member configured to be disposed in the cross member; wherein the tension cable member resists outward deflection of at least a portion of the skid landing gear assembly when a downward load is applied to the skid landing gear assembly. In other aspects, there are methods of avoiding ground resonance in a skid landing gear assembly, methods of assembling a skid landing gear assembly, methods of operating a helicopter with a skid landing gear assembly, and methods of improving the service life of a skid landing gear assembly.

Abstract: A drive train for a helicopter, which includes an engine, a reduction gear and a main gearbox, the reduction gear including an output shaft, which are received in assembled front and rear housings, the output shaft being supported and guided rotatably by a plurality of rolling bearings, mounted in the housings. The drive train includes a redundant mount arranged around the output shaft and between a wall of the main gearbox and the front end of the front housing, and the redundant mount is configured, sized and attached to the wall of the main gearbox and to the front end of the front housing so as to create, if the front housing breaks, a secondary path for absorbing loads passing via the redundant mount, via the output shaft of the reduction gear and via the bearings.

Abstract: There is provided a multicopter having a frame, four rotors attached to the frame and each having an input shaft, four motor-generators installed one on each of the rotors and each having an input-output shaft, a single gas-turbine engine connected to the motor-generators and having an output shaft. The input shaft of each rotor, the input-output shaft of each motor-generator and the output shaft of the engine are respectively connected with each other by a speed reducer mechanism having a sun gear, ring gear and planetary carrier.

Abstract: A rotor system for a rotorcraft has a hub rotatable about an axis and a plurality of blades coupled to the hub for rotation therewith about the axis. Each blade is capable of rotation about a pitch axis relative to the hub, and a ring couples adjacent blades to each other.

Abstract: Rotor assembly apparatus are disclosed. An example rotor assembly includes a twist actuator to drive a first rotation of a first shaft about a first axis, the twist actuator positioned at a center of rotation of the rotor assembly. A first gear assembly to convert the first rotation into a plurality of second rotations of a plurality of second shafts. Each of the second shafts to provide torque to a respective blade coupled to the rotor assembly.

Abstract: A bond fixture includes a first frame defining a chamber configured to receive a leading edge of a rotor blade and a second frame pivotally coupled to the first frame. The second frame is movable between a first position and a second position. In the second position, the second frame restricts movement of the bond fixture relative to the rotor blade. At least one supporting assembly extends from the first frame towards the chamber. The at least one supporting assembly is adjustable to apply a pressure to an adjacent surface of the rotor blade.

Abstract: A biplaner rotor blade has an upper airfoil section connected to a lower airfoil section such that the upper airfoil and lower airfoil are rotated in separate planes—an upper plane and a lower plane. The upper airfoil has a root end attached to a hub at an upper location of the hub and the lower airfoil has a root end attached to the hub at a lower location of the hub. The upper airfoil converges with the lower airfoil to form a blade tip end at the outermost portion of the blade, thus generating lift along two geometric planes.

Abstract: A mast lockout system for a tiltrotor aircraft having a proprotor assembly. The system includes a mast coupled to and rotatable with the proprotor assembly. A proprotor gearbox having a proprotor gearbox housing is operable to transmit torque and rotation energy to the mast. A lock assembly has first and second lock members. The first lock member is coupled to and rotatable with the mast. The second lock member is coupled to the proprotor gearbox housing. The lock assembly has a first position in which the first and second lock members are disengaged, thereby allowing rotation of the proprotor assembly. The lock assembly has a second position in which the first and second lock members are engaged, thereby preventing rotation of the proprotor assembly. The lock assembly is actuatable between the first and second positions.

Abstract: An aerial device (100) capable of controlled flight has a body (110), a rotor (120) arranged to rotate relative to the body; and a deployable sheet (130), the sheet having an undeployed configuration in which the sheet is folded against the body and a deployed configuration in which the sheet is at least partially unfolded away from the body.

Abstract: There is provided a vertical takeoff and landing aircraft (VTOL), having a main propulsion unit (GT engine) with high-pressure and low-pressure turbine shafts installed along a longitudinal axis of a frame to be rotated by pressurized gas jetted on combustion of an air-fuel mixture to produce propulsion force in a longitudinal direction of the frame, high-pressure side and low-pressure side motor generators coaxially attached to the high-pressure and low-pressure turbine shaft, four fans installed on the frame to be rotatable around axes parallel to a vertical axis of the frame, four propulsion units individually connected to the fans to rotate them and generate lift force in a vertical direction of the frame, and a controller. The controller control operation of the main propulsion unit, motor generators and sub propulsion units to obtain propulsion forces in the longitudinal direction and in the vertical direction of the frame.

Abstract: An aerial vehicle adapted for vertical takeoff and landing using pivoting thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to takeoff with thrust units providing vertical thrust and then transitioning to a horizontal flight path. An aerial vehicle with pivoting thrust units with propellers, wherein some or all of the propellers are able to be stowed and fully nested during forward flight.

Abstract: Disclosed herein are aircraft and landing gear systems configured to fix an aircraft to the ground. For example, the aircraft and aircraft systems configured for ground manipulation. In one aspect, an aircraft with an arm and end-effector may be fixed a ground surface to facilitate ground-based robotic manipulation tasks.

Abstract: A telepresence drone that is configured to navigate through an environment includes a frame, a propulsion system comprising propellers and motors coupled to the frame, an electronic control unit in communication with the propulsion system, and a hull positioned outside of the frame and the propulsion system. The hull includes a plurality of openings through which the propulsion system acts on air to navigate through the environment.

Abstract: The present invention relates to a hybrid-powered unmanned vehicle, comprising: a fuel engine (10), a permanent magnet brushless DC motor (20), a rechargeable battery component (30), an startup control circuit (40), an electronic speed regulator, a flight controller, and a propeller. The startup control circuit (40) supplies power from the chargeable battery assembly to the permanent magnet brushless DC motor such that the permanent magnet brushless DC motor drives an operation of the fuel engine. The power generated by the permanent magnet brushless DC motor can charge the rechargeable battery component. When compared to using a battery as sole power supply device, the use of hybrid-power provides greater energy density of up to 1,000-1,500 Wh/kg.

Abstract: A multi-modular aerial firefighting control method and apparatus for use by firefighters to control fire. The multi-modular aerial firefighting control method and apparatus generally includes multi-modular units that are held together to form an aerial firefighting system. The modular units may work together or independently. The multi-modular system comprises more than one modular unit, fluid, fluid conduit, reservoir, air flow generator, multi-modular unit support structure, aerial suspension system and aerial lift system.

Abstract: A payload loading system is disclosed. The payload loading system includes a UAV and a loading structure. A retractable tether is coupled to a payload coupling apparatus at a distal end and the UAV at a proximate end. A payload is loaded to the UAV by coupling the payload to the payload coupling apparatus. The loading structure of the payload loading system includes a landing platform and a tether guide. The tether guide is coupled to the landing platform and directs the tether as the UAV approaches and travels across at least a portion of the landing platform such that the payload coupling apparatus arrives at a target location. The payload is loaded to the payload coupling apparatus while the payload coupling apparatus is within the target location.

Abstract: In a preferred embodiment, a modular galley monument for an aircraft cabin includes a first side panel, a second side panel, and an upper surface connecting the first side panel and the second side panel. The modular galley monument may include dividers partitioning the monument into a number of compartments. The monument may include an upper monument portion and a lower monument portion connected at a periphery via a seal allowing for vertical deflection between the first monument portion and the second monument portion of at least one inch while maintaining contact with both. The monument may include an integrated heating appliance for a compartment, including an insulation shell, a heated compartment positioned within the insulation shell, an electrical heating unit disposed within the insulation shell and configured to provide heat energy to the heated compartment. And a door assembly rotatably connected about an opening of the heated compartment.

Abstract: A room partition assembly is configured to selectively convert an area within an internal cabin of a vehicle between a standard use and a non-standard use. The room partition assembly includes a mounting frame that is configured to be secured to a monument within the internal cabin, and a panel that is moveably coupled to the mounting frame. The panel is selectively moved between a retracted position and an extended position with respect to the mounting frame. The area is configured for the standard use when the panel is in the retracted position. The area is configured for the non-standard use when the panel is in the extended position.

Abstract: A modular panel system for attachment to an overhead stowage bin including an elongate bracket, a plurality of spacers, and at least one panel removably attached to the plurality of spacers without requiring tools to facilitate panel interchangeability independent of stowage bin structure. The at least one panel can be marked with, for example, branding, cabin class designation, advertising or wayfinding.

Abstract: A passenger tray table includes at least two hingedly connected table sections, and is operable to move between at least three positions: 1) a stowed mounting position against a fore positioned monument, where the tray table stows at an angle relative to vertical, and a top portion of the tray table is closer to the passenger than a lower portion of the passenger tray table in the stowed position, 2) a first operative position, where a front table section of the tray table lowers into a horizontal position, while the rear table section remains in the angled stowed position, and 3) a second operative position, where the front table section is disposed closer to the passenger while the rear table section of the passenger tray table is lowered to a horizontal position, in line with the front table section to provide a contiguous table surface.

Abstract: An aircraft cabin arrangement includes at least one cabin attendant seat, called a high-comfort seat, which can assume a stowed position, a sitting position and at least one rest position, and at least one furniture unit. The high-comfort seat is installed in a space provided in the furniture unit, or can extend at least partially into a space arranged in the furniture unit when said high-comfort seat is in the rest position.

Abstract: According to the invention, a drive device for an aircraft is provided, which has a shaft turbine coupled to an impeller via a shaft. The impeller has an intake side and a thrust side. The shaft turbine is mounted in the area of the intake side of the impeller. The drive device is also designed for mounting externally on an aircraft fuselage and/or inside an aircraft fuselage and/or in a casing on a wing.

Abstract: A vibration isolation device comprises a frame for mounting on an engine casing, an axis to be mounted to an external component to isolate, a resilient member located between the frame and the axis, and a fuse mechanism ensuring that the vibration isolation device presents a first stiffness when loads applied to said vibration isolation device are below a predetermined threshold load, and a second stiffness, lower than the first stiffness, when loads applied to the vibration isolation device are at least equal to the predetermined threshold load. The fuse mechanism constrains the resilient member within a predetermined space when loads applied to the vibration isolation device are below the predetermined threshold load and to release the resilient member so that this latter is capable of deforming beyond said predetermined space when loads applied to the vibration isolation device are at least equal to the predetermined threshold load.

Abstract: In one embodiment of the present disclosure, there is provided an aircraft having a bi-folding cowl for providing full access to equipment without completely removing the cowl. The bi-folding cowl has an upper portion and a lower portion mechanically connected along the adjacent edges, where the upper and lower portions fold so that the inner surfaces face each other when opened. In another embodiment, the bi-folding cowl has at least three maintenance positions, including partially-opened, fully-opened, and fully-opened, lying flat on the surface of the aircraft.

Abstract: In one embodiment of the present disclosure, there is provided an aircraft that includes a cowling having a j-track mounted on the inwardly facing surface and a rod pivotally connected to a stationary part of the aircraft at a first end and moveable within the j-track at a second end, so that, when the cowling is opened, the second end moves to lock into the j-shaped portion and hold the cowling open. In various embodiments, the first end may be pivotally connected to the aircraft by a quick release pin, and the second end may be connected to the j-track by a torsion spring. In another embodiment of the present disclosure, the cowling is a bi-folding cowl having an upper portion and a lower portion, where the rod and the lower portion may include structures for retaining the lower portion in an opened position.

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: The present disclosure particularly relates to an acoustic attenuation structure for a propulsion assembly of an aircraft. The acoustic attenuation structure includes an acoustically reflective wall and a sandwich panel. The sandwich panel includes a honeycomb structure surrounded by two acoustically porous skins, a rear skin and a skin. The acoustically reflective wall and the sandwich panel are arranged in such a way as to be separated by a layer of air.

Abstract: There is disclosed a cooling system for a liquid cooled internal combustion aircraft power plant for an aircraft having a tail cone. The cooling system has: an air inlet defined through a wall of the tail cone and fluidly connected to an environment outside the aircraft; a heat exchanger having at least one first conduit fluidly connected to the environment via the air inlet and at least one second conduit in heat exchange relationship with the at least one first conduit and fluidly connectable to a coolant circuitry of the liquid cooled internal combustion aircraft power plant; a blower fluidly connected to the environment via the air inlet; and an air outlet fluidly connected to the blower and defined through a wall of the aircraft upstream of the air inlet relative to a direction of an airflow along the aircraft.

Abstract: A fiber composite component includes an integrated structural health sensor arrangement, wherein the component includes a plurality of layers of fibers embedded in a matrix material, wherein the layers include at least two strain sensing fibers arranged parallel and at a distance to each other, wherein the strain sensing fibers are lithiated carbon fibers having piezoelectric characteristics.

Abstract: A method of operating a manipulation system of the type having a movable arm with a proximal end connected to a base and a distal end that is movable relative to the base and is coupled to an end-effector. The method comprises moving the distal end of the movable arm towards a target object and into contact with a stabilization object proximate to the target object, maintaining contact between the distal end of the movable arm and the stabilization object while operating the end-effector to perform a desired operation at the target object, and upon completing the desired operation at the target object, disengaging the distal end of the movable arm from contact with the stabilization object.

Abstract: The embodiments described herein provide for lightning protection in aircrafts constructed with Carbon Fiber Reinforced Plastic (CFRP). In one embodiment, the apparatus includes a first Carbon Fiber Reinforced Plastic (CFRP) panel, a second CFRP panel that overlaps with the first CFRP panel in a vertical direction, and a fastener to join the first CFRP panel with the second CFRP panel, the fastener extending in the vertical direction in an area where the first CFRP panel and the second CFRP panel overlap. The apparatus further includes a plurality of electrically conductive pins in each of the first CFRP panel and the second CFRP panel, wherein the pins extend in the vertical direction proximate to the fastener to electrically connect the first CFRP panel and the second CFRP panel in the area where the first CFRP panel and the second CFRP panel overlap.

Abstract: An aerodynamic blade is provided and includes a blade body and a light module. The blade body includes an inboard end and a tip outboard of the inboard end. The blade body is connectable with a hub at the inboard end such that rotations of the hub drive rotations of the tip about a rotational axis. The light module is disposed in the tip and configured to activate in response to the rotations of the tip about the rotational axis to emit light visible at an exterior of the blade body.

Abstract: A method for charging an aerial vehicle is implementable by an aerial vehicle and may comprise: obtaining a relative location of the aerial vehicle to a landing deck, and landing to the landing deck according to the relative location; sending an instruction signal to a charging apparatus located on the landing deck, to cause the charging apparatus to detect a movement route from the charging apparatus to the aerial vehicle; and docking to the charging apparatus via a charging end of the aerial vehicle.

Abstract: A passenger boarding bridge for docking a cab with an aircraft. The passenger boarding bridge includes: a tunnel unit; a cab; a drive wheel provided on the tunnel unit or the cab; a rotational mechanism configured to rotate the cab; a controller configured to control the drive wheel and the rotational mechanism; a camera configured to capture an image of an entrance of an aircraft; and an entrance position calculator configured to detect the entrance of the aircraft based on the image and calculate horizontal positional information of the entrance. The controller is, when the cab is at a predetermined standby position from which the cab starts moving at a time of performing docking of the cab with the entrance, configured to: calculate a target position based on the horizontal positional information; and move the cab from the standby position to the target position.

Abstract: A secure terminal for the aerial transport of passengers whose technical and operational infrastructure makes it possible to ensure the physical security of the building, of the aircraft, of the goods, of the passengers and of the flight, technical and administrative personnel and the confidentiality of the passengers and of their goods, noteworthy in that it comprises at least one building having a globally V-shaped horizontal section and comprising two branches extending from a mid-zone, constituting parking hangars for aircraft and determining between them an uncovered central zone.

Abstract: A non-geostationary satellite system and method for weather and climate monitoring, communications applications, scientific research, and similar tasks. The satellite system provides global coverage using a constellation of six satellites in two orthogonal, 24 sidereal hour orbits (geosynchronous) with inclinations of 70° to 90°, and eccentricities of 0.275-0.45. By placing three of the satellites in a first orbit with an apogee over the north pole, and three of the satellites in a second, orthogonal orbit with an apogee over the south pole, global coverage may be obtained. As well, the satellites in these orbits avoid most of the Van Allen Belts.

Abstract: A control system for controlling an operation of a spacecraft. A model predictive controller (MPC) produces a solution for controlling thrusters of the spacecraft. The MPC optimizes a cost function over a finite receding horizon using a model of dynamics of the spacecraft effecting a pose of the spacecraft and a model of dynamics of momentum exchange devices of the spacecraft effecting an orientation of the spacecraft. The optimization is subject to hard and soft constraints on angles of thrusts generated by thrusters. Further, the hard constraints require the angles of thrusts in the solution to fall within a predetermined range defined by the hard constraints. The soft constraints penalize the solution for deviation of the angles of thrusts from nominal angles corresponding to a torque-free thrust passing through the center of the mass of the spacecraft. A thruster controller operates the thrusters according to the solution of the MPC.

Abstract: A web packaging machine for enclosing a food product within a food product package has a first sealing station that seals an upper web of packaging material to a lower web of packaging material to thereby partially enclose the food product in the food product package and a second sealing station configured to further seal the upper web of packaging material to the lower web of packaging material to thereby fully enclose the food product in the food product package. A lower web transport conveyor conveys the lower web of packaging material from upstream to downstream first through the first sealing station and then through the second sealing station.

Abstract: A blister packaging machine that manufactures a blister pack, wherein the blister pack comprises: a lidded container that includes a container main body and an outer lid portion; and an inner cover film attached to close the opening of the container main body, the blister packaging machine comprising: a conveyor; a molding device that executes a molding process to a strip-shaped container film and form a lidded container-corresponding part corresponding to the lidded container; a placing device that is disposed downstream of the molding device and places the article in a container part; a sealing device that is disposed downstream of the placing device and attaches the inner cover film to close an opening of the container part; and a punching device that is disposed downstream of the sealing device and punches out the lidded container-corresponding part along with the inner cover film to produce the blister pack.

Abstract: The operation handle includes a link portion engaged with the main handle on one side as viewed from the rotation fulcrum and a lever operation portion on the other side as viewed from the rotation fulcrum. The clincher arm is configured to rotate in a closing direction with respect to the main handle when the lever operation portion and the main handle are gripped. The binding machine for gardening further comprises a cover member configured to cover the link portion.

Abstract: A calibrated coupling station for components of capsules includes an external body and a bag. A through seat for stably housing the external body supports the bag and is arranged on an articulated sector of a respective advancement component movable along a frame. At least one grip element is aligned with a predefined stop area of the at least one through seat and is movable from a raised configuration in which its terminal end rests on a bottom of the bag, in turn juxtaposed against an inner face of the base of the external body/The grip element is adapted to define an intermediate configuration for a calibrated positioning in which the terminal end, stably coupled to the bottom of the bag, is arranged at a predefined distance from the inner face of the base of the external body.

Abstract: A push-in mechanism pushes articles into a box that is opened sideways. The push-in mechanism is provided with a box standby part, an article placement part, a push-in plate, a horizontal movement mechanism, and a lifting/lowering mechanism. The box standby part causes the boxes to wait. The article placement part has a placement surface on which the articles are temporarily placed. The push-in plate is installed in a standing state so as to have a pressing surface for pressing the articles toward the box. The horizontal movement mechanism causes the push-in plate to reciprocate horizontally above the placement surface so that the push-in plate moves toward the box or moves away from the box. The lifting/lowering mechanism moves the push-in plate so as to change a separation distance in the height direction between a lower edge of the pressing surface and the placement surface.

Abstract: There is described a packaging apparatus for forming a plurality of sealed packages from a tube of a web of packaging material which is continuously filled with a pourable product. The packaging apparatus comprises a delimiting element arranged, in use, within the tube and being designed to divide the tube, in use, in a first space and a second space. The packaging apparatus also comprises a pressurizing device for pressurizing the second space by a sterile gas withdrawn from the inner environment of an isolation chamber within which the tube is formed. Furthermore, the delimiting element is also designed to allow, in use, a leakage flow of sterile gas from the second space into the first space.

Abstract: A laminated bottle formed in a cylindrical shape with a bottom includes: an outer layer; and a flexible inner layer laminated onto an inner surface of the outer layer and being separable from the inner surface. A bottom section of the outer layer positioned at a bottle bottom portion is provided with a holding rib pinching and holding the inner layer. A part of the outer layer is provided with an intake hole allowing outside air to be imported into a space between the outer layer and the inner layer, and the holding rib is provided in each of a pair of areas which are disposed within the bottom section at an interval such that a bottle axis is interposed between the areas in a bottle radial direction.

Abstract: A tamper evident container (2) made from cardboard, paperboard or other lightweight foldable sheet material comprises a container body (6) comprising a first pair of opposed side wall panels (8, 10) and a second pair of side wall panels (12, 14), the side wall panels (8, 10, 12, 14) being hingedly attached to each other about respective side wall fold lines (16). A lid (22) is hingedly attached to one side wall panel (8) of the first pair of opposed side wall panels (8, 10) about a lid fold line (26). First and second closure flaps (28, 30), are hingedly attached to a respective one of the second pair of opposed wall panels (12, 14) about respective closure flap fold lines (32, 34) so as to define respective locking slots (36, 38) between a side edge of the respective closure flaps (28, 30) and the other side wall panel (10) of the first pair of side wall panels (8, 10).