Abstract: A teatcup liner, for use in a method of providing enhanced teat massage during a milking operation, includes a cross-sectional shape defining plural corner portions and plural side portions with a first side portion being a weak side and each remaining side portion being a strong side; with the weak side having a greater flexibility than each strong side such that during a collapse phase, the collapse of the weak side occurring first and being greater than the collapse of each strong side creates an asymmetric pressure distribution with a greater pressurized area resulting in a prolonged contact surface against the teat end across a first surface region of the cross-sectional shape opposite the weak side as compared to a remainder of the cross-sectional shape, the increased pressurized area across the first surface region providing an enhanced teat massage during the collapse phase.

Abstract: A flow body having a surface, a leading edge has an active flow control system. The active flow control system includes a plurality of openings, at least one control pressure varying device and at least one fluidic actuator with an interaction chamber having an inlet connectable to an air source, at least two outlets and at least two control pressure ports. The openings are distributed along or parallel to the leading edge in a side-by-side relationship and extend through the surface. The control pressure varying device is connected to the at least two control pressure ports in a fluidic manner, wherein the control pressure varying device is adapted to bring about the flow of the fluid at least majoritarily into a respective one of the outlets. Each of the outlets is connected to one individual opening of the plurality of openings.

Abstract: A personal service unit pod assembly configured to be positioned in the interior of an aircraft. The personal service unit pod assembly includes a personal service unit pod and a panel positioned directly above and affixed to the personal service unit pod. The pod includes a housing with a lens assembly and a pod interior, a first reading light positioned within the pod interior and configured to shine light below the bottom of the housing, and cabin lighting positioned in the housing and configured to shine light through the lens assembly and above the housing. The panel includes connectors that are configured to secure the personal service unit pod assembly to a component within the aircraft.

Abstract: A detangling lead assembly comprising an elongated flexible lead having a first lead end and a second lead end, a body subassembly comprising a pulley, the lead retained in a lead path from a distal end of the body assembly, around the pulley and extending from the distal end of the body subassembly whereby the first lead end and the second lead end extend generally in a distal direction from the handle subassembly and the lead is generally movable back and forth around the pulley. In some embodiments, the lead assembly further comprises a handle subassembly rotatably coupled to a proximal end of the body subassembly. In some embodiments, the housing further comprises exit points for the lead ends defining a moment arm for a moment to force the body subassembly to rotate and uncross a crossing of the lead ends.

Abstract: Methods and systems are provided to wrap a faired tether around a drum. The tether may be connected to an aerial vehicle. The method may involve guiding a faired tether around an exterior surface of a drum, wherein the drum comprises a helical shaped step around the exterior surface that is configured to mate with at least part of the faired tether, and to stack subsequent layers of wrapped tether in a staggered manner along the longitudinal axis of the drum. The faired tether may be guided onto the step using one or more level winds.

Abstract: A teatcup and a cartridge to be attached to a teat of an animal to be milked. The cartridge includes a sleeve having an upper end and a lower end, and a teatcup liner mounted in the sleeve and having an inner space for receiving the teat. A pulsation chamber is provided between an inner side of the sleeve and an outer side of the teatcup liner. The teatcup liner includes an upper end portion located at the upper end of the sleeve, a barrel portion and a lower end portion extending beyond the lower end of the sleeve. The lower end portion forms an end nozzle beyond the lower end of the sleeve. The end nozzle has a tapering external shape configured to be received in a milk conduit for transporting the milk from the cartridge to the milk conduit.

Abstract: A crashworthy bench (1) for an aircraft having a cabin that includes a floor (51), a ceiling (52), and substantially vertical partitions. Said bench (1) comprises a frame (2), at least one seat for a passenger, with each seat comprising a seat, a back, a retaining system (7) for retaining said passenger, and at least one energy absorber device (20). Said frame (2) is fastened to the inside of said cabin via one low connection point (8) for each seat and via at least one high connection point (9) for said bench (1). Two low connecting rods (11) and one leg (12) connect the frame (2) to each low connection point (8) on said floor (51). Two high connecting rods (15) connect the frame (2) to the high connection points (9) on said ceiling (52) or on a vertical partition of the cabin of the aircraft.

Abstract: The invention relates to a steering method of a projectile and to the associated projectile with incidence steerable fins, comprising at least three fins, each being pivotable with respect to the projectile around a pivot axis perpendicular to the longitudinal axis X of the projectile, wherein the projectile comprises a fin orientation ring, the ring comprising as many arms as there are fins, wherein the ring can translate in a plan P perpendicular to the longitudinal axis X of the projectile and following at least two directions of this plan P, wherein the orientation ring can rotate on itself around its center parallel to the longitudinal axis X of the projectile, each arm comprising means cooperating with an orientation lever fixed to a fin to be able to pivot the fin around its pivot axis during translation of the ring by positioning means.

Abstract: The invention provides in-flight refueling systems with a communication sub-system available in radio silence operations including at least a first digital wireless data link comprising a first RF transceiver and a second RF transceiver coupled, respectively, to first and second antennas located in two points inside the boom or the hose of the refueling system or in RF communication with them and connected, respectively, to refueling control units in the tanker aircraft and in the free end of the refueling device by data buses allowing a digital communication between them.

Abstract: A balloon having a balloon envelope formed with a plurality of adjacent envelope gores sealed together at their respective edges to form an edge seam between each of the adjacent envelope gores, a tape comprised of fibers applied to a centerline of each of the envelope gores, wherein the envelope gores are constructed such that the edge seam between each of the adjacent envelope gores is longer than the centerline of each of the envelope gores, and wherein a load caused by pressurized lifting gas within the balloon envelope is carried primarily by the fiber tapes on the centerlines of the envelope gores, rather than the edge seams between the adjacent envelope gores.

Abstract: A symmetrical rib structure and methods are presented. A structural web comprises a web center plane and a plurality of web stiffeners, and is symmetrical about the web center plane. A flange is configured on a periphery of the symmetrical rib structure, and a fastener hole is configured in the flange and comprises a fastener hole centerline aligned with the web center plane. A cutout is configured in the structural web around the fastener hole, and two support columns are coupled to the flange on opposite sides of the cutout.

Abstract: A hybrid aircraft (1) having a fuselage (2) extending longitudinally along an anteroposterior plane of symmetry (PSYM) from the rear (4) of the aircraft (1) towards the front (3) of the aircraft (1). The aircraft (1) has a rotary wing (6) carried by the fuselage (2) of a lift surface (10) fastened to the fuselage (2) and constituted by a first half-wing (11) and a second half-wing (12). The aircraft (1) has a first propulsion unit (30) carried by the first half-wing (11) and a second propulsion unit (40) carried by the second half-wing (12). Each propulsion unit (30, 40) includes at least one tractor propeller (31, 32, 41, 42), and at least one propulsion unit has two propellers (31-32, 41-42) on the same axis, each of said propellers rotating about an axis of rotation (AX) that is offset transversely from said anteroposterior plane of symmetry (PSYM).

Abstract: A gearbox system for a dual coaxial counter rotating rotor assembly includes an input shaft to input a first torque into the gearbox system and a transfer shaft operably connected to the input shaft to transfer the first torque therethrough. Two gear sets are operably connected to the transfer shaft. Each gear set includes a first output gear to transfer a second torque acting in a first direction to a first rotor of a rotor assembly and a second output gear to transfer the second torque acting in a second direction opposite the first direction to a second rotor of the rotor assembly. The second torque transferred by each gear set of the two gear sets is substantially equal.

Abstract: A hybrid aircraft (1) having a fuselage (2) extending longitudinally along an anteroposterior plane of symmetry (PSYM) from the rear (4) of the aircraft (1) towards the front (3) of the aircraft (1). The aircraft (1) has a rotary wing (6) carried by the fuselage (2) of a lift surface (10) fastened to the fuselage (2) and constituted by a first half-wing (11) and a second half-wing (12). The aircraft (1) has a first propulsion unit (30) carried by the first half-wing (11) and a second propulsion unit (40) carried by the second half-wing (12). Each propulsion unit (30, 40) includes at least one tractor propeller (31, 32, 41, 42), and at least one propulsion unit has two propellers (31-32, 41-42) on the same axis, each of said propellers rotating about an axis of rotation (AX) that is offset transversely from said anteroposterior plane of symmetry (PSYM).

Abstract: A tray lock mechanism for a pet enclosure is disclosed. The tray lock mechanism includes a sliding component that has a camming surface that interacts with a leading-edge of the tray to generate an upward force to move the sliding component out of the way so that the tray can be inserted into an opening and into the pet enclosure. Additionally, in a further embodiment, the tray lock mechanism contemplates a door extension that extends downward and blocks the opening when the door is in the closed position and unblocks the opening when the door is in an opened position.

Abstract: A launch vehicle payload that includes at least two spacecraft is disclosed. The launch vehicle includes a single payload adapter. Each spacecraft has a launch vehicle adapter structure providing a respectively coplanar structural interface directly with the single launch vehicle payload adapter. The spacecraft share a launch vehicle payload fairing volume substantially side-by-side and are detachably coupled together such that a positive clearance is provided between adjacent, non-abutting structural body surfaces of each spacecraft.

Abstract: An orbit attitude control device includes a divert thruster including a plurality of nozzles. First group nozzles inject combustion gas in opposite directions along a first axis. Second group nozzles inject combustion gas in opposite directions along a second axis. A control section calculates correction values for opening degree commands based on a detection value of a pressure of the combustion chamber and a command value of the pressure, and corrects the opening degree command values by the correction values. The device further includes a first axis acceleration sensor for detecting acceleration along the first axis and a second axis acceleration sensor for detecting acceleration along the second axis. The correction values for the opening degrees of the first group nozzles are determined by a first axis acceleration, and the correction values for the opening degrees of the second group nozzles are determined by a second axis acceleration.

Abstract: A fixed compliant wing system is provided that is coupled to a rigid spar and a rigid stopper. The fixed compliant wing system includes an actuator and at least two compliant rib structures coupled to the rigid spar. The compliant rib structures include an outer compliant contoured structure, a drive member coupled to the outer compliant contoured structure where the drive member is in a sliding arrangement with the rigid stopper. The drive member is further connected to the actuator. The outer compliant contoured structure of the compliant rib structures is configured to deform when force is applied from the actuator to the drive member. The fixed complaint wing system further includes a skin encompassing the compliant rib structures.

Abstract: An aircraft lifting surface with a torsion box of a composite material including an upper skin, a lower skin, a front spar, a rear spar, one or more intermediate spars and transverse ribs arranged between the rear spar and an adjacent intermediate spar and/or between the front spar and the adjacent intermediate spar.

Abstract: A nectar feeder for hummingbirds comprises a container, base tray, a base tray cover, a float, and a stopper thereon. The container, or bottle, is used for storing nectar feed. An exit port is defined on the bottom end of the container. The base tray is connected in fluid communication with the container and has at least one vertical member depending upwardly from a top surface of the base tray. A circumferential flange or ring is provided about the float for stabilization. The float engages the at least one vertical member to prevent substantial independent lateral movement of the float. In operation, the nectar feed flows through the container and into the base tray until the float rises to a level where the stopper mechanism engages the exit port to prevent fluid from flowing into the base tray.