Abstract: A slide-in structural interface between a Sea Water Intake Riser (SWIR) and a floating unit hull or sump tank bottom plate permits a pull-in, diver-less installation of the SWIR. Certain embodiments include an integrated, easily maintainable strainer.

Abstract: The present disclosure provides an exhaust assembly for an aerostat, including a valve base (2) provided with a valve port (1), and a valve cover (3) that selectively covers the valve port (1), and further including: a motor driving mechanism and a transmission mechanism that are arranged on the valve base (2). The motor driving mechanism propels the transmission mechanism to drive the valve cover (3) to selectively cover the valve port (1). When the valve cover (3) is in a position where the valve port (1) is open, the valve cover (3) is arranged at an angle with respect to a plane at which the valve port (1) is located. A purpose of the present disclosure is to provide the exhaust assembly that is for an aerostat and whose exhausting pressure can be flexibly adjusted, and an aerostat provided with the exhaust assembly.

Abstract: A method of controlling an elevator of an aircraft includes selecting a factor for increasing or decreasing a predetermined horizontal tail load alleviation (HTLA) authority limit for an elevator based on at least one aircraft parameter. The HTLA authority limit decreases with an increase in Mach number and/or airspeed. The method also includes computing an elevator position limit as a product of the HTLA authority limit and the factor, and moving the elevator to a commanded elevator position that is no greater than the elevator position limit.

Abstract: An aircraft hand controller is disclosed. The hand controller includes a set of finger controls on a single hand grip structure, the set of finger controls including a first finger control configured to control throttle of the aircraft and a second finger control, separate from the first, configured to control rotation about a first rotational axis of the aircraft.

Abstract: A combined active stick and control boost actuator system for a control surface has a control stick engaged to a mechanical flight control structure with a linkage configured to move a control surface. A mechanical interconnect engages the linkage and has a control stick connection. An integrated actuator is separably connected to the mechanical interconnect intermediate the control stick connection and the linkage. A stick force sensor is configured to provide a stick force signal. A flight control system receives the stick force signal and provides an actuator position control signal to the integrated actuator. The integrated actuator moves to a prescribed position in accordance with a force feel profile providing pilot variable tactile cueing and power boost to reduce both fatigue and workload.

Abstract: One object is to reduce a volume occupied by a device disposed in a first space spatially limited to a large degree. An electric actuator diving and controlling device is provided with a drive unit positioned in a first space in a piece of equipment and configured to apply power to an electric actuator and a control unit positioned in a second space in the piece of equipment and configured to transmit, to the drive unit, a power command signal including information related to power to be applied to the electric actuator. The first space having the drive unit positioned therein is limited compared with the second space having the control unit positioned therein.

Abstract: A vertical tail unit (7) including an outer skin (13) in contact with an ambient air flow (21), wherein the outer skin (13) extends between a leading edge (23) and a trailing edge (25) with opposite lateral sides (27a, 27b), and surrounds an interior space (29), and wherein the outer skin (13) has a porous section at the leading edge (23), a pressure chamber (15) arranged in the interior space (29), wherein the pressure chamber (15) is fluidly connected to the porous section (31), an air inlet (17) provided in the outer skin (13) and fluidly connected to the pressure chamber (15), and an air outlet (19) provided in the outer skin (13) and fluidly connected to the pressure chamber (15).

Abstract: A fluid interaction apparatus includes a wing having a first configuration with a first profile drag coefficient and a second configuration with a second profile drag coefficient that is less than the first profile drag coefficient. The fluid interaction apparatus further includes a body having a longitudinal axis, wherein the body is coupled to the wing. The fluid interaction apparatus further includes an actuator configured to change the wing from the first configuration when moving in a first direction relative to the body to the second configuration when moving in a second direction relative to the body, the second direction having a substantial component parallel to the longitudinal axis of the body.

Abstract: Methods, apparatus, and articles of manufacture to extend a leading-edge vortex of a highly-swept wing aircraft wing are disclosed. An example apparatus includes a shoulder wing coupled to a fuselage of an aircraft above a highly-swept wing of the aircraft, the shoulder wing operative in a first position to extend a leading-edge vortex spanwise along the highly-swept wing of the aircraft.

Abstract: A vortex generator arrangement comprising a section that defines an opening to a corresponding cavity, an aircraft airflow modification device disposed within the cavity, and at least one fluidic muscle actuator arrangement coupled to the airflow modification device.

Abstract: A folding trailing arm landing gear assembly having a main fitting configured to couple to a hinge positioned at a proximal end; a swing arm rotatably coupled at a proximal end to a distal end of the main fitting; a shock coupled at a distal end to a distal end of the swing arm; a bellcrank coupled at a distal end to a proximal end of the shock, and coupled at a proximal end to the main fitting; and a wheel coupled to the swing arm.

Abstract: A ground movement plug-in (GMP) apparatus for providing ground propulsion to an unmanned aircraft vehicle (UAV). The GMP apparatus includes a frame configured to mechanically couple with the UAV, a plurality of wheels, at least one of which is actuatable by a motor, and a controller operably coupled to the motor to control propulsion of the GMP apparatus.

Abstract: A laminated dimpled foil metallic heat shield may have a cylindrical structure with an outer diameter and an inner diameter comprising a first metallic layer defining the outer diameter, an inboard edge and an outboard edge of the laminated dimpled foil metallic heat shield assembly, a second metallic layer defining the inner diameter of the laminated dimpled foil metallic heat shield assembly, and a first dimpled foil layer extending about a first circumference between the inner diameter and the outer diameter.

Abstract: A strut assembly for a vibration isolation device is disclosed, comprising a piston spindle; a first elastomeric member and a second elastomeric member bonded to the piston spindle and in contact with an upper housing and a lower housing, respectively; a first strut support and a second strut support attached to or integral with the upper housing and the lower housing, respectively; a first strut spindle and the second strut support configured to be placed in the first strut support and the second strut support, respectively; and one or more removable struts configured to be engaged to the first strut spindle and to the second strut spindle, wherein at least one of the first or second strut spindles is removable such that the one or more struts can be replaced without breaking a bonding of the first elastomeric member, the second elastomeric member, or both.

Abstract: A tandem rigid rotor system has a first rigid rotor system and a second rigid rotor system connected by a fuselage. The fuselage has at least one framing member connected between the first rigid rotor system and the second rigid rotor system, such that the framing member is torsionally flexible for controlling yaw of the tandem rigid rotor system. In certain embodiments, multiple framing members are connected between the first rigid rotor system and the second rigid rotor system in parallel. In certain embodiments, the torsional flexibility allows up to 20 degrees of movement away from the lateral axis. In certain embodiments, framing members are vertically and laterally rigid.

Abstract: The ‘Air Wheel’ rotor is a variable pitch rotor with variable twist blades. The ‘Air Wheel’ rotor comprises a closed wing coupled to one or more coaxial hubs via torsional elastic blades, the blades are coupled to the closed wing in one of the following ways: rigid, elastic, or visco-elastic. There is provided a wide range of combinations of the wing relative width and coning angle typical for a lifting rotor with a thin planar wing attached to the tips of long blades, for a shrouded fan in a wide annular wing, or for an impeller in a rotating cylindrical wing. The ‘Air Wheel’ rotor combines and enhances the advantages of a rotor and a wing, it has excellent aerodynamic characteristics, and eliminates limitations of the rotor size and flight speed. The ‘Air Wheel’ rotor can be used for designing vertical take-off and landing aircraft. The “Air Wheel” rotor is universal and can function as a lifting rotor, or a wind turbine, or an aircraft propeller, or a marine propeller.

Abstract: An elastic flapping hinge for connecting a rotor blade to a rotor hub of a rotary wing aircraft, comprising an elastic flapping hinge member arrangement that includes a hub attachment area for attachment to the rotor hub, a connection area for attachment to the rotor blade, and an elastic flapping hinge area that is arranged between the hub attachment area and the connection area and adapted to allow flapping movements, the elastic flapping hinge member arrangement comprising at least two elastic flapping hinge members having a first bending stiffness for flapping movements and a second bending stiffness for lead-lag movements, the first bending stiffness being smaller than the second bending stiffness, wherein the at least two elastic flapping hinge members diverge from each other in the elastic flapping hinge area by a predetermined divergence angle.

Abstract: A method of fabricating a filler body for a blade of a rotor. In addition, such a method comprises a succession of steps of adding material layer by layer, each step consisting in making a new layer of material on a preceding layer of material made in the preceding step, at least one of the steps consisting in making an openwork layer of material presenting a plurality of openings, the succession of steps of adding material layer by layer generating openwork layers of material, each having a closed outline, the respective closed outlines of the openwork layers of material touching mutually in pairs and forming a closed envelope of the filler body for the blade.

Abstract: Various techniques are provided for a winged drone platform. In one example, a drone can be provided. The drone can include a drone body, a plurality of wings, a plurality of tiling propeller assemblies, and a drone controller. The wings can be coupled to the drone body and configured to generate lift when the drone travels in a first travel direction. The tilting propeller assemblies can each be supported by one of the wings, can include a propeller and a propeller powerplant connected to the propeller, and can be configured to move between at least a first position and a second position. The drone controller can provide instructions to the tilting propeller assemblies to move between at least the first position and the second position. Additional systems and related methods are also provided.

Abstract: A method for an aircraft may include determining a transition from an airplane mode to a helicopter mode for a propulsion system of the aircraft, wherein the propulsion system comprises a plurality of rotor blades; determining whether a descent rate condition is satisfied, wherein the descent rate condition is associated with a maximum allowable descent rate for the aircraft; and controlling a collective pitch angle for the plurality of rotor blades based on the descent rate condition.

Abstract: Airframes configured for stable in-flight transition between forward flight and vertical takeoff and landing are described herein. In one embodiment, an aircraft can include a fuselage, opposed wings extending from opposed sides of the fuselage, and a plurality of engines. At least one engine can be mounted to each of the opposed wings and at least a portion of each opposed wing including at least one of the plurality of engines can rotate relative to the fuselage around a rotation axis that is non-perpendicular and transverse to a longitudinal axis of the fuselage. Rotating portions of the wings including at least one of the plurality of engines in the described manner can provide a stable and smooth transition between vertical and forward flight.

Abstract: An unmanned aerial vehicle (UAV) includes a fuselage that supports breakaway components that are attached using magnets. One component is a battery pack which powers the vehicle. Another component is a rotor set including two identical pod pairs that each support a motor and a propeller. Each motor is attached to a hub assembly that includes a plurality of spokes captured in a motor hub and sandwiched by a rigid motor printed circuit board on top and a rigid hub plate. The hub assembly construction is rigid in plane and functions to keep the motor firmly stable during operation. The hub assembly is compliant and resilient when impacted parallel to the plane. Other features of the pod pairs encage the otherwise dangerous spinning propeller. This allows the vehicle to operate with a higher level of safety than conventional UAVs.

Abstract: A vision system for a vehicle includes a forward viewing camera disposed at a vehicle and viewing forward of the vehicle through the windshield. A control is disposed at the vehicle and includes an image processor operable to process image data captured by the forward viewing camera. An aerial platform is detachably disposed at the vehicle and is operable to detach from and fly at least above the vehicle. The aerial platform includes a drone camera that captures image data and the image data captured by the drone camera is wirelessly communicated to the control. A video display is disposed in the vehicle and is viewable by a driver of the vehicle. The video display, with the aerial platform detached from the vehicle and flying at least above the vehicle, displays video images derived from image data captured by the drone camera for viewing by the driver of the vehicle.

Abstract: A vehicular alert system includes an autonomous aerial vehicle and a central computer. The autonomous aerial vehicle includes a processor, a display, and a detector. The processor controls a data transceiver. The detector detects one or more vehicular condition. The central computer communicates with the autonomous aerial vehicle via the data transceiver. The central computer includes a memory device. The memory device stores vehicular condition data and road condition data. The central computer communicates one of a vehicular condition or a road condition to the autonomous aerial vehicle. The processor of the autonomous aerial vehicle displays the received condition on the display.

Abstract: A cargo transport system comprising a spine assembly and a container assembly. The spine assembly comprises a rigid spine and a plurality of mounts arranged on the rigid spine in a plurality of mount rows. The container assembly comprises a plurality of containers and is secured to the spine assembly using at least a subset of the plurality of mounts. Each container of the plurality of containers comprises a plurality of fittings for securing the container to the spine assembly and/or another container of the container assembly. Each mount row extends along a width of the spine assembly, and the plurality of mount rows are spaced apart at regular distance intervals along a length of the spine.

Abstract: A lavatory may include a vanity including a wash basin, and a handle assembly connected to a portion of the wash basin. The handle assembly provides an ergonomic shape that is configured to be grasped by an individual.

Abstract: A seat system for a passenger aircraft. The seat system includes a passenger seat frame having a backrest support assembly and a seat bottom support assembly. A quadrant assembly is connected between the backrest support assembly and the seat bottom support assembly. The quadrant assembly includes a quadrant member including a pivot point adapted to pivot the backrest with respect to the seat bottom support assembly and the quadrant member. The quadrant member is attached to the backrest and adapted to break away in the event of an impact with the backrest. The quadrant assembly may further include a pivot point brake assembly attached to the pivot point and adapted to provide a controlled stop of the backrest in the event of an impact with the backrest. In addition, a seat back tray table may be attached to the back of the passenger seat frame.

Abstract: The invention relates to a vehicle seat (1) comprising a seat surface (2) and at last one backrest element (3, 13) which are pivotable about an axis (6) relative to the seat surface (2). The at least one backrest element (3, 13) is movable from a sitting position, in which the backrest element (3, 13) is positioned substantially at an angle (a) relative to the seat surface (2), into a reclined position, in which the seat surface (2) and the at least one backrest element (3, 13) form a substantially planar surface, and back again. The vehicle seat (1) has at least one pneumatic cushion (10; 10.1, 10.2) and a pneumatic unit (9), which is configured in such a way that the pneumatic unit substantially completely inflates the at least one pneumatic cushion (10; 10.1, 10.2) if the at least one backrest element (3, 13) is moved into the reclined position, and the at least one pneumatic cushion (10; 10.1, 10.2) is substantially completely emptied when the backrest element (3, 13) is moved into the sitting position.

Abstract: An aircraft pressurized air system and method is disclosed. The system includes a compressor that receives and compresses outside air, and an air cycle machine that receives compressed air from the compressor and directs conditioned air to an aircraft pressurized zone. The system also includes a contaminant sensor disposed along an air flow path between the compressor and the aircraft pressurized zone, comprising an optical guide, a metal organic framework on an exterior surface of the optical guide in operative fluid communication with air from the air flow path, a light source in communication with the optical guide at a first end of the optical guide, and a light detector in communication with the optical guide at a second end of the optical guide.

Abstract: An aircraft air conditioning system including an ambient air supply line having a first end connected to an ambient air inlet and a second end connected to a mixer of the aircraft air conditioning system so as to supply ambient air to the mixer. A first compressor is arranged in the ambient air supply line and is configured to compress the ambient air flowing through the ambient air supply line. A bleed air supply line allows a flow of bleed air bled off from an engine or an auxiliary power unit therethrough. A bleed air turbine is driven by the bleed air flowing through the bleed air supply line and is coupled to the first compressor so as to drive the first compressor.

Abstract: An aircraft with rear mounted engines, comprising a vertical tail plane and a horizontal tail plane, in which the engines are mounted on top of the horizontal tail plane, such that the horizontal tail plane comprises an inner fixed part attached to the fuselage of the aircraft, the inner fixed part comprising an elevator, and two outer movable parts, each one of the outer movable parts being located at each side end of the horizontal tail plane which is furthest away from the fuselage of the aircraft, such that both the inner fixed part and the outer movable parts are at least partially subjected to a flow coming from the engines when the engines are in use.

Abstract: An airplane propelled by a turbine engine having at least one fan, the turbine engine being integrated in the rear of a fuselage of the airplane, extending it rearwards, the airplane further including at least one acoustic baffle forming panel connected to the fuselage of the airplane and arranged below the turbine engine.

Abstract: A propulsion system for an aircraft includes an engine (e.g., piston engine, or turbine) having an axis made to be nonparallel with the longitudinal axis of the aircraft. This is enabled using an electrical, hydraulic, or other system to transfer energy generated by the engine (e.g., via electrical wiring, fluid conduits, etc.) to remotely power a motor used to drive a thrust-creating device (e.g., propeller or ducted fan). That the engine is able to be freely oriented allows for it being positioned without regard to any mechanical restraints existing in conventional arrangements.

Abstract: Systems and methods for mounting motors include a housing configured to secure motor supported by a motor support framework coupled to and housed within the housing. The motor support framework is suspended from the housing by one or more pluralities of vibration isolation devices. The housing is provided with a mounting surface configured couple the housing a quick-connect bracket disposed on a bulkhead or other structural element.

Abstract: There is disclosed a cooling system for a liquid cooled internal combustion power plant housed in an engine compartment in a tail cone of an aircraft. The cooling system has: a tail cone inlet defined through a wall of the tail cone and fluidly communicating with an environment; a wall inlet defined through a firewall of the engine compartment; a blower within the engine compartment and having a blower inlet and a blower outlet, the blower inlet fluidly communicating with the environment via the tail cone inlet, via the wall inlet, and via an interior of the engine compartment; a blower outlet defined through a wall of the aircraft and fluidly communicating with the environment; and a cooling flow path extending from the tail cone inlet to the air outlet and across the wall inlet, the cooling flow path in heat exchange relationship with the power plant.

Abstract: An aircraft where an engine creates mechanical energy. That energy is then converted into another transmittable form, e.g., electrical using a generator, or hydraulic using a pump, and is delivered to remotely-located motors and thrusters, e.g., propellers at one or more locations on the aircraft. The general concept makes the engine as well as the motors used scalable to accomplish overall efficiency objectives.

Abstract: A method for startup of a catalytic oxidation unit includes flowing air from an air source into the catalytic oxidation unit, recycling air from an outlet of the catalytic oxidation unit to an inlet of the catalytic oxidation unit through a recycle duct, and flowing a fuel from a fuel source into the catalytic oxidation to cause a catalytic reaction.

Abstract: Systems, aircraft, and non-transitory media are provided. An avionics system for an aircraft includes a storage device and one or more data processors. The storage device stores instructions for monitoring an actual performance of the aircraft. The one or more data processors are configured to execute the instructions to: generate a lateral component and a longitudinal component of a measured moving air mass relative to the aircraft; generate a plurality of wind independent positions of the aircraft along a potential aircraft trajectory based on a prediction model; and generate a plurality of wind corrected positions of the aircraft based on the plurality of wind independent positions, on the lateral component, and on the longitudinal component.

Abstract: Locking line capture devices for unmanned aircraft are disclosed. An example line capture device is configured to be attached to a wing of an unmanned aerial vehicle (UAV). The example line capture device includes a body having a line capture slot. The line capture slot has an open end and a closed end. The example line capture device further includes a retainer having a first lobe, a second lobe, and a third lobe. The retainer is movable relative to the body between a first position in which the first and third lobes are positioned on opposite sides of the line capture slot and the second lobe is positioned over the line capture slot, and a second position in which the first and second lobes are positioned over the line capture slot and the third lobe is positioned clear of the line capture slot.

Abstract: The machinery system comprises an arm having an upper fixing device arranged to fix to the arm at least one upper module to be manipulated in an upper plane and a lower fixing device arranged to fix to the arm at least one lower module to be manipulated in a lower plane; a first securing device of the arm configured to control the positioning of the arm; the arm being mounted cantilever-fashion on the first securing device. The machinery system makes it possible to at least halve the manipulation time for two modules by virtue of the arm mounted cantilever-fashion, to which two modules can be fixed.

Abstract: A tail-cone reinforcement angle of a Cessna 180-185 series aircraft is repaired by the removal of an aft most section of that tail-cone reinforcement angle and its replacement with an elongated splice body. The elongated splice body is attached to the remainder of the tail-cone reinforcement angle and to the tail-cone portion of the fuselage of the aircraft. The aft section of the original tail-cone reinforcement angle is subject to the development and propagation of cracks in the area of the rear pivot shaft receiving bore, which cracks render the aircraft unfit for use. The invention includes the provision of a suitable elongated splice body, a method for its installation, and a tool kit which is usable in accomplishing the removal and replacement of the aft section of the tail-cone reinforcement angle.

Abstract: A device to verify main rotor swashplate positioning includes an inner surface of a first section and a gradient surface of a second section. The gradient surface of the second section may have a plurality of graduation indications. In one implementation, the inner surface of the first section at least partially defines a travel arc that is parallel to and concentric with the inner surface. In such an implementation, the device may be configured to move along the travel arc as it rotates about a collective sleeve to contact a swashplate lug.

Abstract: A spacecraft including a set of thrusters for changing a pose of the spacecraft. At least two thrusters mounted on a gimbaled boom assembly and are coupled together sharing the same gimbal angle. A model predictive controller (MPC) to produce a solution for controlling thrusters of the spacecraft by optimizing a cost function over a 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. A modulator to modulate magnitudes of the thrust of the coupled thrusters determined by the MPC as pulse signals specifying ON and OFF states of each of the coupled thruster, wherein the ON states of the coupled thrusters sharing the same gimbal angle do not intersect in time. A thruster controller to operate the thrusters according to their corresponding pulse signals.

Abstract: A temperature control system may include a heat exchanger configured to cool air within a pressurized enclosed crew cabin when the air is circulated across the heat exchanger and coolant is circulated through the heat exchanger. The system may further include a sublimator configured to cool the coolant. The system may also include a primary coolant line configured to transport the coolant from the sublimator through the heat exchanger.

Abstract: A lightweight spacecraft dispenser, which consists of a material made from composite materials, and of a ring structure with several payload ports. The ring structure has a surface that extends between opposite ends of the ring structure and that is at least partially spherical. The surface can be completely spherical or partially spherical between the opposite ends.

Abstract: Systems and methods for aseptically filling pharmaceutical containers with pharmaceutical fluid are disclosed. In one general aspect, these are based on an aseptically sealable chamber that includes a transfer wall to which pre-sealed pharmaceutical source and receiving containers are mounted aseptically. A robotic arm and a syringe store are disposed within the chamber along with a sterilizing facility for establishing in the chamber an aseptic condition. The robotic arm can grip and operate syringes to inject and/or extract pharmaceutical products from the containers by piercing their closures with the needles of the syringes.

Abstract: A package preparation system includes a material conveyable along a longitudinal direction and including two folded layers of polymeric film joined at a fold. The fold extends longitudinally and defines a first side of the material opposite an open second side. A first welding device forms partition welds located between the two folded layers and extending from the fold to a terminus inward of the open side. A second welding device forms first and second seal welds that extend from the fold to the open side and are spaced from each other by a length extending longitudinally and traversing a plurality of the partition welds. The system includes a device comprising a nozzle insertable in the open side, and clamps that traverse the length and temporarily seal the open side around the nozzle while the nozzle inflates interior channels defined between the plurality of partition welds.

Abstract: A method of applying a lid (1) onto a neck (9) of a container (10), the lid (1) having a side wall (3) extending around an axis and an end wall (2) extending transversely to said axis, comprises the following steps: —positioning the lid (1) onto the neck (9); —exerting on the end wall (2) a force directed towards the container (10), so as to level the lid (1) on the neck (9); —screwing the lid (1) onto the neck (9) by rotating the lid (1) in a screwing direction.

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 work station (40) for a packaging line having an apparatus (4) for executing a simultaneous action on packages (10) of an alignment of packages with a tool (46); and a transfer mechanism (31) for the simultaneous transport of an alignment of packages to be processed (10b) to the apparatus (4) and of an alignment of processed packages (10c) from the apparatus (4). The alignments are arranged parallel to each other and the transport direction of the packages are perpendicular to the alignments, the transfer mechanism (31) thus having a first and a second transport group (31a, 31b), one of which hangs from two movable parts (60) of the transfer mechanism (31) which are movable on respective parallel planes of movement and which do not interfere with the vertical projection of the tool (46). A packaging line (101, 102, 103) with modular construction having such work stations.