Abstract: An aircraft pylon comprising a primary structure and a pipe segment having an internal duct positioned inside at least one structural tube primary structure. This solution makes it possible to reduce the crowding outside the structural tubes of the primary structure, makes it easier to integrate other equipment inside the pylon, and may help to improve the aerodynamic performance of the pylon by reducing its cross section.

Abstract: A feed hopper with two chute members is provided. The chutes are movable with respect to one another and one chute has an extending lip to engage the inner surface of the other chute to prevent feed from escaping the hopper.

Abstract: A system to arrest flap over-travel employs a track engaging a flap to a support structure. The track has a deployment profile determining flap motion relative to the support structure during travel between an extended position and a normal retracted position. The deployment profile has a transition portion extending beyond the normal retracted position and terminating in a detent. A resiliently mounted catcher is configured to be displaced by the transition portion during over-travel of the flap beyond the normal retracted position and captured in the detent in a maximum retracted position thereby restraining the flap.

Abstract: A crustacean trap adapted to permit blocking entry to a crustacean of a protected species, including a cage, enclosing a volume and a crustacean entrance that can be closed to prevent entry, responsive to a first signal and opened to permit crustacean entry, responsive to a second signal received at the trap. Also, an image forming assembly includes a digital camera and a flash mechanism, the assembly being directed at an area immediately outside of the entrance and being tuned to return a maximum signal from crustaceans of the protected crustacean species so that a protected species crustacean appears as brightly lit in images formed, and being communicatively connected to a remote station that is equipped to receive-images from the assembly. Finally, there is a connector for connecting the cage to a signal source for receiving the first and second signals and for sending the images formed.

Abstract: A pet bed including a cushioned-base defined by a body-section and a head-section; a blanket removably fastened to the cushioned-base; and fastener for removably fastening the blanket to the cushioned-base. The cushioned-base includes molded sections to provide support and comfort to the bed. In particular, the head-section includes a molded section which defines a pillow. The pet bed is useful for providing a pet, particularly a dog, with a comforting location to rest.

Abstract: An electrical energy processing unit of an apparatus to kill a plant or at least attenuate plant growth is disclosed. The electrical energy processing unit includes a converter and a control circuit. Also disclosed are an apparatus that includes the electrical energy processing unit and a method of utilizing the apparatus. Further disclosed are a computer program for a processor of the control circuit of the electrical energy processing unit and a non-transitory computer readable medium that includes the computer program.

Abstract: An aircraft engine attachment including a beam fixed to a pylon and including a yoke with two walls, and a connecting rod with an articulation housed in the yoke, in which the connecting rod has a front flank and a rear flank which are facing inner faces of the walls. For each wall, a wearing part is disposed against the inner face of the wall and between the wall and the corresponding flank of the connecting rod. A Fixing arrangement ensures the fixing of the wearing part to the wall. Thus, the wearing parts prevent an excessive tilting of the connecting rod and the wearing of the connecting rod or of the yoke.

Abstract: A front engine attachment system for an engine of an aircraft, the front engine attachment system having an engine pylon having, in its front part, a frontal part having an attachment wall that has a front face, and a front engine attachment having a beam that is fixed against the front face and to which is fixed, on either side of a median plane, a rod system, wherein each rod system is fixed to the beam in an articulated manner by at least one first connection point, and is configured to be fixed to a front part of the engine in an articulated manner by at least one second connection point. Such a front engine attachment system thus has rod systems having two rods, allowing the shape of the rods and the shape of the beam to be simplified.

Abstract: An assembly for an aircraft that has a wing and an engine pylon having a primary structure with right-side and left-side panels, an upper and a lower spar and a rear rib, two sets of upper or lower shackles, one set fastening the right-side panel to the wing, and a second set fastening the left-side panel to the wing, a fastening element secured to the rear rib or to the lower spar, a rear rod connecting the fastening element to the wing, a transverse shackle connecting the upper spar to the wing, a line connecting two centers of the transverse shackle being oriented transversely relative to a longitudinal axis of the engine pylon, and a reinforcing panel, at each joint between a right-side or left-side panel and an upper or lower shackle, which is fastened along a height against the panel and to which the shackle is also fastened.

Abstract: A junction of a pylon with an aircraft wing, the pylon including a primary structure extending from front to rear along a longitudinal axis and in the form of a box with a rear face and an upper spar forming an upper face of the box, a longitudinal median plane separating the primary structure into two parts, left and right, the junction comprising a rear attachment system for attaching the pylon to the wing, this system being arranged at the rear of the primary structure, the rear attachment system including a shoe attached beneath the wing, the shoe being connected, via at least one articulated connecting rod, to a fitting attached to the rear face of the pylon by an articulation whose articulation pin, termed the horizontal articulation pin, is perpendicular to the longitudinal median plane, and the shoe being connected to the upper spar via a force reacting system.

Abstract: A for providing control input adjustment for an aircraft, including one or more mode sensors disposed on an aircraft, a mode analysis system, the mode analysis system operable to receive mode sensor data from the one or more mode sensors, and operable to decompose the mode sensor data into decomposed mode data associated with fundamental modes of structural elements of the aircraft associated with the one or more mode sensors, and a flight control computer (FCC) disposed on the aircraft and connected to one or more actuators, the FCC operable to provide a control signal to the one or more actuators according to an association between the decomposed mode data and one or more rotorcraft parameters associated with the one or more actuators.

Abstract: An aircraft undercarriage including electrical equipment (2, 3) fastened to a portion (1) of the undercarriage and a lightning protection device (10) comprising at least one shield fastened to said portion (1) of the undercarriage by fastener means so as to extend in register with the electrical equipment (2, 3) in a position that is spaced apart therefrom, the shield comprising at least a first plate (11) made of electrically conductive material that is arranged to absorb a major portion of the heat energy that is generated by the passage of a lightning wave and to discharge the electric charge of the lightning wave. An aircraft fitted with such an undercarriage.

Abstract: The invention relates to an aircraft having a tailless fuselage. The fuselage has a body which includes a transverse trailing edge. The aircraft further includes a wing having two sides which protrude from opposite sides of the fuselage. The body typically has a fineness ratio of between 3 and 7. Each side of the wing has an inner section having a first dihedral angle and an outer section having a second dihedral angle, the second dihedral angle being less than the first dihedral angle. At least part of the outer section is typically swept back. The configuration of the aircraft provides it with improved flight efficiency.

Abstract: A moisture control system includes an anode coupled to an insulation blanket that is positioned between an inner wall and an outer wall of an aircraft fuselage, a cathode coupled to an interior surface of the outer wall, and a power control unit coupled to the anode and the cathode to apply voltage across the anode and the cathode. When the voltage is applied across the anode and the cathode, moisture is drawn away from the anode and toward the cathode on the interior surface of the outer wall and guided along a drainage path provided via structural members disposed between the inner wall and the outer wall toward a drainage port.

Abstract: A field incinerator has a carriage with a frame. A fuel tank such as a propane tank is mounted to the frame. An outlet passage extends from the tank. An outlet valve is mounted to the outlet passage. The outlet valve controls the outlet passage. The first gauge has a first gauge tap. The first gauge tap is connected to the fuel tank or the outlet passage. The first gauge has a first gauge control parameter. The first gauge control parameter requires less than a first set pressure for activation. The second gauge is connected to the outlet passage downstream from the first gauge. The second gauge has a second gauge control parameter. The second gauge control parameter requires more than a set second pressure for activation. The first gauge control parameter and the second gauge control parameter must both be fulfilled for opening the outlet valve.

Abstract: A propulsion assembly including a primary structure of a pylon having right and left extensions projecting with respect to right and left lateral panels of the primary structure and also right and left brackets, each having a first flank connected to the right or left lateral panel of the primary structure and a second flank pressed against the right or left extension, a front engine mount having first and second links, each connected to an engine and directly to the front transverse reinforcement by a first or second reinforcement connection pin passing through the right or left extension and the second flank of the right or left bracket.

Abstract: Compliant mounting systems, devices, and methods for mounting a vehicle engine to a vehicle structure or base include a top mount, a lower mount, a center trunnion mount, and an aft mount which are configured to react forces transmitted by the engine to the vehicle structure. Metallic and elastomeric elements can provide vibrational and force isolation characteristics. Stops (e.g., snubbing elements) allow for a specific range of motion before internal mount structures contact each other to act as a conventional hard mount. Fluid elements and compressible gas-filled spaces/bladders may be incorporated to provide fluid damping behaviors to complement the metallic and elastomeric elements.

Abstract: A propulsion assembly for an aircraft, comprising a pylon to be secured below a wing of the aircraft and having a front face and a lower face, and a turbomachine comprising, from upstream to downstream in a direction of a flow of air passing through the turbomachine during operation, a fan and an engine driving the fan. The fan is faired by a fan casing and the engine is faired, from upstream to downstream, by an intermediate casing and an engine casing, the intermediate casing having a hub and an outer ring extending the fan casing, the ring being spaced apart radially from the hub and secured to the latter by arms extending in an air duct. The propulsion assembly comprises a front engine attachment secured between the pylon front face and the hub and a rear engine attachment secured between the pylon lower face and the engine casing.

Abstract: A front engine attachment system for an engine of an aircraft. The front engine attachment system has an engine pylon having, in its front part, a frontal part having an attachment wall with a front face, and a front engine attachment having a beam fastened to the front face and to which a link-rod system is fastened on either side of a median plane. The beam is made up of a front plate and a rear plate that are fastened together in a removable manner. The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. Each link-rod system is fastened to the rear plate in an articulated manner by at least one first connection point and is configured to be fastened to a front part of the engine in an articulated manner by at least one second connection point.

Abstract: A metallic-composite joint fitting is provided. The fitting may comprise a composite structure, an integral bearing comprising a first frustoconical portion and a second frustoconical portion each having a complimentary shape to the composite structure, a sleeve comprising a third frustoconical portion coupled to a cylindrical bearing surface of the integral bearing, and a metallic end fitting coupled to the third frustoconical portion, wherein the metallic end fitting comprises a bearing portion contacted with the cylindrical bearing surface.