Abstract: The present disclosure relates to bearings, guide sleeves and head restraint assemblies for automobiles.

Abstract: A method and system for disinfecting and disinfesting a commodity, such as a perishable agricultural commodity, by treatment with an environment of low oxygen/high ballast gas with cycled pressure changes that overwhelm and damage the respiratory system of the insect without damaging the host commodity. The system and method may also include the introduction of disinfectants, antiseptics and other toxic chemicals or the exposure to radio frequencies with intense electric fields that may increase the metabolic activity of the pest or decrease the fitness of the pest within the low oxygen environment. Treatments according to the methods can also increase the shelf life of agricultural commodities by eradicating or delaying the growth of bacteria, fungi, protozoa and other microbial pests.

Abstract: A mounting support for a photovoltaic module is described. The mounting support includes a foundation having an integrated wire-way ledge portion. A photovoltaic module support mechanism is coupled with the foundation.

Abstract: Quasi-isotropic chopped prepreg is used to make parts found in aerospace vehicles. Exemplary aerospace parts that are made using quasi-isotropic chopped prepreg include aircraft window frames, wing fairing supports, flange supports, frame gussets, rudder actuator brackets, shear ties, seat pedestals, cargo floor flange supports, storage bin fittings, antenna supports, torque tube pans, handle boxes, side guide fittings, wing box covers and intercostals.

Abstract: The invention refers to appetence measurement for animals. In particular, the invention proposes an automated system for measuring the appetence of animals, including a feeding area (2) and an accommodation area (1), wherein the feeding area includes a room (3) whose dimensions are chosen so that the animal is able to move therein, and the system also includes access control resources (6, 10-12) that are designed so that the animals can gain access in turn to the room (3) from the accommodation area.

Abstract: An attachment device for an aircraft engine that includes a rigid structure and an attachment mechanism of the engine to the rigid structure. The attachment mechanism includes a device reacting to thrust forces generated by the engine, the reacting device including two link rods mechanically connected to a balance beam at a rear end by a first mechanical connection, a main fitting fixed to the rigid structure to which the balance beam is mechanically connected, and two additional fittings fixed to the rigid structure to which the link rods are mechanically connected with play. The mechanical connections between the balance beam and the main fitting and between the link rods and the additional fittings each include a pin orthogonal to a mid-plane of transmission of the forces.

Abstract: An aircraft comprises a wing (2) defining an aerofoil surface, the wing (2) comprising a drooped leading edge flap (1) being moveable between a stowed position and a deployed position. The wing (2) is so arranged that during flight when the high-lift device is in the deployed position, air may flow through an opening (7) in the wing (2) and over the aerofoil surface. During flight, air preferably flows into the boundary layer (13) on the upper surface of the wing (2). This energises the boundary layer (13), aft of the trailing edge of the drooped leading edge flap increasing its stability allowing the maximum achievable lift coefficient to be increased and hence reducing aircraft take-off and approach speeds.

Abstract: To provide a combination of at least one motivational object for dogs, which comprises of a bite body, and a carrying device for the at least one motivational object, which comprises of a clamping element, on which the bite body of the motivational object is detachably secured, which allows for an easy carrying or storing of the motivational object while not in use, it is proposed that the bite body comprises a of a recess in which the insertion section of a clamping element of the carrying device is insertable in an insertion direction.

Abstract: The recovery and rescue system includes a sail (5) with rigging (10) fitted around a spreader conduit (4), with an intake and outlet nozzle, wherein a starting system (6) is provided, including mechanical (12-13) and electromechanical (17-18) opening mechanisms, in the first case operated by a manual lever (16) and in the second case operated by a button (19). Air driven through the intake of the spreading conduit (4) activates the starting system (6) in order to spread the sail (5) and by parachute means retain or brake the aircraft wherein the said system assembly is fitted. Said system can be housed inside the aircraft in a container provided for the purpose.

Abstract: An aircraft arrangement for Mini or Micro UAV comprising a fore wing (14) and an aft wing (12) in tandem closed-coupled arrangement. The aft wing (12) has side panels (18) and control surfaces (19), and tapered planform with positive sweep, while the fore wing (14) has non-positive trailing edge sweep. The fore wing (14) and the aft wing (12) are disposed at different height, and the aircraft arrangement has no other wings or tail arrangements.

Abstract: The present disclosure includes various apparatus, system, and method embodiments for vehicle energy absorption. One embodiment includes an inflatable structure for impact of a vehicle thereon and one or more cords coupled to one or more deflation vents on the inflatable structure, where at least one of the one or more cords is an activation mechanism to activate the deflation vent upon impact of the vehicle.

Abstract: A mounting system for a gas turbine engine includes a thrust ring and a linkage assembly. The linkage assembly is at least partially received by the thrust ring. The linkage assembly reacts at least a side load and a thrust load communicated from the thrust ring.

Abstract: An aircraft comprising an elongated framework provided with propelling means and direction-control planes. The framework is coupled to a pneumatic chamber suited to be filled with lighter-than-air gas and comprising two tubular branches joined to form a V-shaped profile, with an aerodinamic-lift surface extending therebetween.

Abstract: An aircraft venting tank (for example a surge tank) has a stack pipe unit. The stack pipe unit comprises first and second portions and houses a frangible overpressure protector element (for example a frangible disc). The stack pipe unit may be arranged to have a fitted configuration in which the first portion of the stack pipe unit is attached to a part of the venting tank structure, the first portion is coupled to the second portion, and the second portion is coupled to another part of the venting tank structure. The first portion may be held in a relationship with the second portion so as to form a seal between the frangible element, and the first and second portions. In a frangible element-replacement configuration the second portion may be coupled to the venting tank structure, such that the frangible overpressure protector element can be replaced without removal of the second portion from the venting tank structure.

Abstract: A canine wound boot is fabricated using a breathable substrate having two layers of generally open weave and a fibrous material spacing and bonding the two layers together. Onto the substrate, various friction pads, wear pads, one or more straps, and strategically located cushions are attached. Specially configured slits ensure that a wide range of leg sizes relative to paw sizes may be accommodated, while easing application of the boot and eliminating any risk of bunching. Elastic material serves as a gusset in the boot which expands to cover a bandage or cast.

Abstract: Aircraft nacelle including a cowling and an engine, the cowling including a fixed portion and a mobile portion able to slide in order to define a radial opening with the mobile portion, a thrust reverser system including a plurality of flaps intended to be deployed in order to seal at least partially an annular channel surrounding the engine, the mobile portion of the cowling including an annular housing extending longitudinally in order to receive the flaps in rest position. Each flap is linked to the fixed portion by a pivot joint and is linked to the mobile portion by a sliding-pivot joint, in such a way that a sliding of the mobile portion in separating from the fixed portion provokes a rotation of each flap around the axis of rotation of the joint with the fixed portion.

Abstract: A slotted aerofoil configuration is provided in which the leading element thereof is contoured to provide mild stall characteristics. A wing based partially or fully on such an aerofoil, an air vehicle including such wings, and a method for designing an aerofoil are also disclosed.

Abstract: An airship may include a hull substantially shaped as an oblate spheroid, one or more frame members defining a support structure, wherein the support structure forms at least a partial support for the hull, at least one horizontal stabilizing member operably coupled to a lower surface of the airship, and at least one horizontal stabilizing member having a first end and a second end. The at least one horizontal stabilizing member may define an anhedral configuration. The airship may also include a vertical stabilizing member having a first end pivotally coupled to the airship and a second end oriented to remain below an upper surface of the airship. The vertical stabilizing member may be configured to pivot within a vertical plane, and the first end of the vertical stabilizing member and the first end of the at least one horizontal stabilizing member may be operably coupled to one another.

Abstract: An aircraft fuel tank assembly comprises a first fuel tank, a second fuel tank and a tank-to-tank overpressure protector therebetween. The overpressure protector has a closed state and an open state. The fuel tank assembly further comprises an indicator for indicating whether the overpressure protector is in the open or closed state, the indication of the indicator being able to be sensed at a location outside of the fuel tanks. The fuel tank assembly may comprise a test mechanism arranged to effect movement of the overpressure valve from the closed state to the open state, the test mechanism being operable from a location outside a fuel tank. The fuel tank assembly may comprise an overpressure valve re-set mechanism, the re-set mechanism being operable from a location outside the fuel tanks.

Abstract: A window arrangement is provided for enlarging a window area in an aircraft. The window arrangement includes, but is not limited to at least one first installation element. The at least one first installation element is designed to convey fluids, and furthermore includes, but is not limited to a transparent region which covers a first window region such that light waves in the visible spectrum can be let through.