Abstract: An integrated pylon structure for a propulsion system is suitable for one end to be connected to an aircraft wing and the other end to be connected to an aircraft engine. The pylon structure includes a pylon box section (110) formed from an upper and a lower bean, a frame (100) and a side wall panel. The pylon structure has a thrust reverser hood connection structure, provided on the side wall and connected with a nacelle thrust reverser hood having a front fixed hood (301) and a rear movable hood (302). A guide rail allows the rear movable hood to slide and open relative to the pylon box section. The engine thrust reverser hood is directly connected to the side wall of the pylon box section and a guide rail on the side wall guides the opening of the thrust reverser hood.

Abstract: A controller includes a first body portion, adapted to be grasped by a person's middle finger, ring finger, and pinky finger, a second body portion adapted to be grasped by a person's index finger, and a third body portion that defines a first surface adapted to receive a person's thumb. A finger switch is positioned on a front surface of the second body portion. The finger switch is positioned such that it may be actuated by the person's index finger. The second body portion is disposed between the first body portion and the third body portion. The second body portion defines an offset with respect to the first body portion. The third body portion defines a second surface above the finger switch, which may receive the person's index finger.

Abstract: A milk conduit, that connects to a teatcup to be attached to a teat of an animal to be milked, includes a first end portion defining a first end and configured to be connected to the teatcup, a second end portion defining a second end, and a conduit portion located between the first end portion and the second end portion. The milk conduit defines a milk channel extending through the first end portion, the conduit portion and the second end portion. The first end portion is received in an opening extending through a bottom wall of the teatcup. The first end portion includes a first circumferential groove configured that engages in the bottom wall of the teatcup.

Abstract: A front installation node is suitable for integral forming with a front end frame of an aircraft pylon and includes a first lug and a second lug, each respectively protruding outwardly from one of the two sides of the frond end frame; a first connecting rod and a second connecting rod, one end thereof being respectively connected to the first lug and the second lug, and the other end thereof being respectively suitable for connecting to an aircraft engine. The first connecting rod can pivotally connect to the first lug at a first connection point. The second connecting rod and the second lug are respectively connected at a second connecting point and a third connecting point. Using the front installation node to transmit torque is beneficial in reducing the external width of a rear installation node, reducing engine fuel consumption.

Abstract: A fluidic system is disclosed. The system comprises a plurality of fluidic oscillatory actuators, and at least one synchronization conduit connecting two or more of the actuators such as to effect synchronization between oscillations in the two or more connected actuators.

Abstract: The invention proposes to protect a rear part of a floor of an aft fairing of a pylon of an aircraft bypass turbojet engine using a film of cool air formed of part of a bypass flow of the jet engine which is guided under the floor by two lateral wall portions of this fairing which have been profiled for this purpose. To do that, these two lateral wall portions delimit respective air passage spaces formed between a forward part of the floor and a jetpipe of the turbojet engine and which open laterally and towards the rear.

Abstract: Herein is disclosed a tool, system and method for refueling on-orbit spacecraft. The tool and system are configured to allow for resupply of spacecraft configured to be propelled by either a bipropellant (oxidizer and fuel) or a monopropellant (typically hydrazine). The refueling tool is particularly suited for resupply of satellites not originally prepared for refueling but the system may also be used for satellites specifically designed for refueling.

Abstract: An aircraft monument comprising a first compartment and a cabin attendant seat having a backrest and a seat element. The seat element is movable relative to the backrest between a folded position, wherein a seat surface of the seat element extends substantially parallel to a backrest surface of the backrest, and an unfolded position, wherein the seat surface of the seat element extends substantially perpendicular to the backrest surface of the backrest. The cabin attendant seat is movable relative to the aircraft monument between a stowed position, wherein the cabin attendant seat, with the seat element being in its folded position, is received in the first compartment of the aircraft monument, and an operating position, wherein the cabin attendant seat is disposed outside of the first compartment of the aircraft monument in a position which allows the seat element to be moved into its unfolded position.

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 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: Acoustic liners for aircraft noise reduction include one or more chambers that are configured to provide a pressure-release surface such that the engine noise generation process is inhibited and/or absorb sound by converting the sound into heat energy. The size and shape of the chambers can be selected to inhibit the noise generation process and/or absorb sound at selected frequencies.

Abstract: A bird feeder comprising a seed container, a center tube formed within the seed container, a seed tray, an independently calibrated cartridge spring assembly having a center rod, a spring extending about the center rod with the center rod extending downwardly of said center tube, a cover, and a hanger engaged with an upper portion of the center tube to thereby retain the cover in position, a shroud having a perch member and a central opening therein to permit the lower end of the center rod to pass therethrough, and a retainer secured to the lower end of the spring assembly.

Abstract: An improved spacecraft actuator wheel is provided which can be operated as a momentum wheel, a reaction wheel or a gimbal. The actuator wheel has a central cavity. One or more battery modules are located within the actuator wheel's central cavity. The battery modules supply power to one or more electronic components affixed to the actuator wheel or mounted on the spacecraft frame via an electrical harness. In addition, the actuator wheel's central cavity is pressurizeable for storing spacecraft propellant which can be controllably diverted to the spacecraft's thrusters through conduits and flow valves.

Abstract: Herein is disclosed a tool, system and method for refueling on-orbit spacecraft. The tool and system are configured to allow for resupply of spacecraft configured to be propelled by either a bipropellant (oxidizer and fuel) or a monopropellant (typically hydrazine). The refueling tool is particularly suited for resupply of satellites not originally prepared for refueling but the system may also be used for satellites specifically designed for refueling.

Abstract: Gossamer apparatus and systems for use with spacecraft may include a deployable gossamer apparatus. The deployable gossamer apparatus may include a plurality rib members and gossamer material extending therebetween and may be configured in a stowed configuration and a deployed configuration. The rib members of the deployable gossamer apparatus store potential energy used for deployment of the deployable gossamer apparatus.

Abstract: A system for arresting an unmanned aerial vehicle (UAV). In an illustrative embodiment, a crane has an arrestment receiver that can pivot around the crane. A UAV has a hook on one of its wings that can latch onto the arrestment receiver during flight. After latching onto the arrestment receiver, the UAV pivots around the end of the crane until the UAV comes to rest. The UAV and the arrestment receiver each include optical alignment systems that facilitate the connection between the hook and the arrestment receiver.

Abstract: A milking method and system for preventing detachment of a teat cup from a teat of an animal during a milking process where the milking system includes a milk line connected to the teat cup, a vacuum system that applies at least two different vacuum levels to the teat cup, a measuring device configured to measure the air flow in the milk line during the milking process, and a control unit (5) that receives information about measured air flow values and to determine if the teat cup is about to be detached from the teat by comparing the measured air flow values (qa) with an acceptable value (qa, ?qal/?t), and when the measured air flow values are not acceptable, to control the vacuum system to apply a higher vacuum level to the teat cup than the present vacuum level.

Abstract: An automatic emergency radar and proximity sensor activated protection system that could assist to prevent commercial, private, or military aircraft jet engines from being damaged or destroyed by the installment of a Shielding Blade Assembly which will immediately close when detection of objects such as; birds, debris, or other destructive elements try to enter through the engine intake while the aircraft is in FLIGHT causing the Internal Air Injection Unit (A.I.U.) to supply high volumes of air in order for the engine to stay operational and prevent it from stalling while in FLIGHT.

Abstract: Described is a pet feeding device having an elongated post that can be secured in or on the ground in a vertical orientation. A water bowl has a central aperture through which the elongated post can be positioned such that the water bowl is positioned on the ground. A feeding bowl support is secured to the elongated post in an elevated position and holds one or more food bowls thereon. A hose can be secured to a tube that extends through the water bowl, through the elongated post, and is attached to a faucet disposed on the elongated post in order to provide water for a pet. A nipple is positioned on the outlet of the faucet, and excess water from the nipple drips into the water bowl. A cover is disposed on the top portion of the elongated post and provides shelter for the pet's food and water.

Abstract: A jump cup for equestrian activities which includes two curved plates for supporting the ends of two jump poles and two hinges that allows the two curved plates to rotate independently from each other and to a single pinned attachment point to a conventional jump standard.