Abstract: An aircraft comprising a rear opening and a rear door to close such rear opening, wherein the rear door is attached to the fuselage of the aircraft by means of an arrangement having two links due to which the rear door can be displaced longitudinally and in elevation up to a position at the interior of the fuselage.

Abstract: Airfoil and hydrofoil systems include structures having a surface texture defined by fractal geometries. Raised portions or fractal bumps can be included on the surfaces, forming a surface texture. The surface textures can be defined by two-dimensional fractal shapes, partial two-dimensional fractal shapes, non-contiguous fractal shapes, three-dimensional fractal objects, and partial three-dimensional fractal objects. The surfaces can include indents having fractal geometries. The indents can have varying depths and can be bordered by other indents, or bumps, or smooth portions of the airfoil or hydrofoil structure. The fractal surface textures can reduce vortices inherent from airfoil and hydrofoil structures. The roughness and distribution of the fractal surface textures reduce the vortices, improving laminar flow characteristics and at the same time reducing drag. The systems are passive and do not require applied power.

Abstract: An apparatus is provided for promoting laminar flow. The apparatus includes a panel extending between an interior surface and an exterior air flow surface. The panel includes a plurality of macro apertures and a plurality of micro apertures. A first one of the macro apertures extends into the panel from the interior surface. A first one of the micro apertures extends into the panel from the exterior air flow surface and is fluidly coupled with the first one of the macro apertures.

Abstract: Apparatuses for and methods of deicing aircraft surfaces, engine inlets, windmill blades and other structures. Deicing apparatuses can comprise at least one standoff coupled with an actuator and a first region of an inner surface of a skin. A standoff can act as a moment arm and can create efficient, tailorable skin bending and acceleration, breaking an ice to skin bond. Integral as well as modular leading edges can comprise deicing apparatuses.

Abstract: A decoy for luring waterfowl has a body that has an upper reservoir partially filled with water. A neck is partially submerged in the upper reservoir. A head, is attached to the neck and configured to raise a neck center of gravity and lower a neck center of buoyancy. Wherein the neck is configured to rotate within the upper reservoir.

Abstract: A method and apparatus for operating an airfoil system. A gas may be generated. The gas may be sent into an inflatable airfoil system comprising an inflatable air foil and a section. The inflatable airfoil may have an inner end and an outer end in which the inflatable airfoil may be comprised of a number of materials that substantially pass electromagnetic waves through the inflatable airfoil. The section may have a number of openings in which the inner end of the inflatable airfoil may be associated with the section. The section may be configured to be associated with a fuselage. The number of openings may be configured to provide communications with an interior of the inflatable airfoil. The section with the number of openings may be configured to reduce reflection of the electromagnetic waves encountering the section.

Abstract: An aircraft wing including a fuel tank located in the wing, a channel defining a cavity in the fuel tank, the channel including at least two channel ends terminating at an upper or lower wing surface, a driveshaft located in the cavity; and an access panel located on the wing surface and being movable between an open position so that access to the cavity is permitted, and a closed position so that the cavity is at least partially covered by the access panel to inhibit access to the cavity.

Abstract: A flex-drive actuator for a satellite boom hinge or other hinge applications. Using a motor-driven cog and a unique drive chain, the hinge can be reversibly driven between open and closed positions, thereby deploying or stowing the boom and attached payload. The chain includes links designed so that, when bent in one direction, the chain pre-buckles into a rigid circular arc form that matches the deployment path of the hinge. This pre-buckling essentially converts the chain into a rigid gear segment that can carry a moment to actuate the hinge. As the cog retracts the chain and the hinge closes, the circular shape of the chain de-buckles on the free side of the cog, where the chain can be stored as a straight section inside of a boom tube or folded into a magazine. The flex-drive actuator can accommodate any desired actuation angle by addition of links to the chain.

Abstract: A portable gate including a center gate section, a center divide gate, a first end divide gate, a second end divide gate, a first end gate, and a second end gate. If the portable gate is located in a building, the portable gate will also include a wall mounted gate. If the portable gate is located in an area bounded by a fence, a fence mounted gate replaces the wall mounted gate. The gates may be hingedly moved to form four holding pens. When the gates are folded so as to be positioned adjacent the inner and outer sides of the center section, a front-end loader may move the portable gate to another location. The opposite ends of the center gate section are provided with double-knuckle hinge joints.

Abstract: A floor panel apparatus comprises: beams arranged inside an aircraft main body; floor panels arranged on the beams; and ball transfer unit bolts each including a ball transfer unit in which a rotatable ball is disposed and a bolt portion which is integral with the ball transfer unit, the ball transfer unit bolts configured such that the floor panels and the beams are detachably fastened together by the bolt portions with the balls protruding on the floor panel side.

Abstract: Systems, methods, and devices are configured to implement hydraulic actuators. Devices may include a housing having an internal surface defining an internal cavity that may have a substantially circular cross sectional curvature. The devices may include a rotor that includes a first slot having a substantially circular curvature. The devices may include a first vane disk partially disposed within the first slot of the rotor, where the first vane disk has a substantially circular external geometry. The first vane disk may be mechanically coupled to the rotor via the first slot, and the first vane disk may be configured to form a first seal with the internal surface of the housing. The devices may include a first separator device that may be configured to form a second seal with the internal surface of the housing and a third seal with an external surface of the rotor.

Abstract: A latching mechanism having a camming surface to engage the latching mechanism without human intervention when a door is traversed from an opened position to a closed position is disclosed. Other latching mechanisms are also disclosed. The latching mechanism may also be rotatable to engage the latching mechanism and prevent opening of the door from the closed position.

Abstract: A projectile incorporates one or more spoiler-tabbed spinning disks to effect flow around the projectile and thus impart steering forces and/or moments. The spoiler tabs may be deployed only during steering phases of travel thus minimizing the drag penalty associated with steering systems. The disks are driven by motors and informed and controlled by sensors and electronic control systems. The spoiler tabs protrude through the surface of the projectile only for certain angles of spin of the spinning disk. For spin-stabilized projectiles, the disks spin at substantially the same rate as the projectile, but the disks may function in fin-stabilized projectiles as well. Any number of such spinning flow effector disks may be incorporated in a projectile, with the manner of functional coordination differing slightly for even and odd numbers of disks.

Abstract: A composite structure forming a load bearing composite shell for a helicopter, with a shell which defines the exterior of a fuselage and includes a central fuselage section and tail boom, a fuselage which is adapted house an engine or drive train, a layered composite crashworthy seat and support structure and a fastening and a method of fastening by providing an adhesive between two layers which is allowed to flow through opposing holes in the layers to provide a chemical and mechanical attachment between the layers.

Abstract: A propulsion assembly includes a turbojet incorporating a fan casing and a central casing around a longitudinal axis, a mounting pylon having a rigid structure, a forward engine attachment interposed between a forward extremity of the rigid structure and an upper part of the fan casing, the upper part being in a vertical median plane (P) passing through the longitudinal axis, an aft engine attachment interposed between a median zone of the rigid structure and an upper aft part of the central casing, and a device for absorbing the thrust forces generated by the turbojet, including two links placed either side of the median plane (P) and hinged, on one hand, forward, on a forward part of the central casing, and on the other, aft, directly on the rigid structure. Such an arrangement enables a reduction of the stresses, and the possibility of designing a simplified rigid structure.

Abstract: A bladder external to a fuel tank of a vehicle that allows an operational range of the vehicle to be increased. Preferably the bladder is external to the rest of the vehicle and the vehicle is an aircraft. The external bladder allows fuel in the fuel tank to expand and contract without requiring additional space within the vehicle, thus allowing more fuel mass to be held by the vehicle and a smaller vehicle profile that is more aerodynamically efficient. More preferably, the bladder is disconnectable from the rest of the vehicle to allow increasing of aerodynamic efficiency and weight reduction during use.

Abstract: A method and apparatus is provided for controlling the location in which herbivore fowl populations congregate by altering the behavior of the fowl through the combination of providing a strong disincentive to populate areas where the presence of the fowl is not desired and a strong incentive to populate a proximate area where the presence of fowl can be tolerated. For herbivore waterfowl, and in particular Canada geese, the adjacent area also provides the waterfowl with a means of egress to water as an escape from predators and other perceived threats. The method uses a deterrent in the form of adulterated feed to dissuade the herbivore fowl from congregating in areas in which their presence is not desired and the use of an attractant in the form of non-adulterated feed to encourage the herbivore fowl to congregate in a proximate area in which their presence can be tolerated.

Abstract: An automated aerial vehicle (“AAV”) and systems, devices, and techniques pertaining to moveable ballast that is movable onboard the AAV during operation and/or flight. The AAV may include a frame or support structure that includes the movable ballast. A ballast controller may be used to cause movement of the ballast based on one or more factors, such as a type of flight, a type of operation of the AAV, a speed of the AAV, a triggering event, and/or other factors. The ballast may be moved using mechanical, electrical, electromagnetic, pneumatic, hydraulic and/or other devices/techniques described herein. In some embodiments, the ballast may be moved or located in or toward a centralized position in the AAV to enable more agile control of the AAV. The ballast may be moved outward from the centralized location of the AAV to enable more stable control of the AAV.

Abstract: Perforated rotating attraction drum of a general cylindrical shape and featuring openings, this drum being fitted for being mounted on a leaf-stripping head of the leaves of a foliage wall such as a row of vine-stock, characterized in that it features the superposition of a plurality of rings presenting an outside cylindrical surface, and of a plurality of annular openings made between two successive rings, these openings allowing the passage of a suction air flow across and towards the inside of the perforated rotating attraction drum featuring, internally, means of rigid assembly of the plurality of stacked rings and a coupling means to a motorization for its rotational drive.

Abstract: Apparatuses for and methods of deicing aircraft surfaces, engine inlets, windmill blades and other structures. Deicing apparatuses can comprise at least one standoff coupled with an actuator and a first region of an inner surface of a skin. A standoff can act as a moment arm and can create efficient, tailorable skin bending and acceleration, breaking an ice to skin bond. Integral as well as modular leading edges can comprise deicing apparatuses.