Abstract: A manual wing-fold mechanism provides a means by which to reconfigure the wing of an aircraft between a flight configuration and one that can be easily stowed and transported. The folding mechanism includes an extension tube that enables the outboard portion of the wing to be extended away from the inboard section of the wing, rotated about the lateral axis of the aircraft and then pivoted rearward so that the wing is aligned with the longitudinal axis of the aircraft along side the fuselage. The wing-fold mechanism is independent of the structural components of the wing used to convey aerodynamic loads during flight and provides a means for the user to bring the outboard wing section into a near alignment position while the wing-fold mechanism thereafter assists to refine the alignment into its final flight configuration.

Abstract: A termite barrier seal including a hollow seal body having a wall surrounding an axial bore extending from an insertion end to a surface end. A closure formation is located about the surface end for engagement with a closure for the orifice of the bore at the surface end of the seal body. A one-way valve at or intermediate the insertion end and the surface end of the seal body, the one-way valve arranged to permit liquid flow through the axial bore, but to prevent liquid flow to the surface end. An external seal about the seal body for sealing the wall of the seal body against the internal surface of a hole drilled through a concrete slab. An internal seal engages the seal body for sealing the wall against an external face of an injector when inserted into the bore of the seal body.

Abstract: A hermetically sealing, enclosure-type mousetrap is provided having a reusable housing and a disposable cartridge that contains an internal high voltage killing mechanism. Upon entry of a mouse into the cartridge through a rodent access opening, the opening is closed and the mouse is killed using the high voltage mechanism. Closure of the door hermetically seals the cartridge with the dead mouse inside, after which the cartridge can be disposed of without any contact between the user and the carcass along with any parasites and pathogens associated therewith.

Abstract: A turbine engine nozzle can include a primary outer wall extending from an engine core area to an annular wall terminus that surrounds an engine tail cone, to form a core nozzle. The turbine engine nozzle also includes a single engine core cowl extending from the engine core area to an annular cowl terminus to form a core compartment vent nozzle. The core compartment vent nozzle exhausts air from a core compartment in a trailing edge between the single engine core cowl and the primary outer wall.

Abstract: An embodiment of a plant manipulator is disclosed, which may have a flexible cylindrical member that is bent to hold a plant in a particular configuration to train the plant. The plant manipulator may include a first end and a second end, a long edge of the flexible cylindrical member, a length of the long edge of the flexible cylindrical member, and a slit along the length of the longest edge of the flexible cylindrical member. The plant manipulator may also have a malleable rigid member with a first and second end, a long edge of the flexible cylindrical member, and a length of the long edge of the malleable rigid member. The length of the long edge of the flexible cylindrical member may be coupled along the length of the long edge of the flexible cylindrical member.

Abstract: An aerodynamic structure comprising a shock bump (3) extending from its surface. The shock bump is asymmetrical about a plane of asymmetry, and the plane of asymmetry: passes through a centre (6) of the shock bump, is parallel with a principal direction of air flow over the structure, and extends at a right angle to the surface of the structure.

Abstract: A joint for coupling a wing tip to a wing base includes a linking member that extends from a first end to a second end. The linking member first end is coupleable to the wing base, and the linking member second end is coupleable to the wing tip. The linking member may be curved and may extend for a fixed distance between the wing tip and the wing base. The linking member defines first second hinge lines that are substantially parallel. The joint also includes at least two actuators. A first end of each actuator is coupled to the linking member, and a second end of each actuator is coupleable to one of the wing base and the wing tip. The actuators are operable to rotate the wing tip about the first and second hinge lines between a first orientation and a second orientation relative to the wing base.

Abstract: A spacecraft system may include a storage portion (e.g., a first portion and a second portion) and a solar array apparatus that may be configurable in at least a stowed configuration and a deployed configuration. The solar array apparatus may include at least one solar array to collect incident radiation when the solar array apparatus is in the deployed configuration. In one or more embodiments, the at least one solar array may extend away from the storage portion. In one or more embodiments, the at least one solar array may extend between the first portion and the second portion. The solar array apparatus may also include an extendable boom operable to extend the at least one solar array apparatus from the stowed configuration to the deployed configuration.

Abstract: A bell crank mechanism is configured to at least indirectly link movement of an aircraft wing spoiler-like hinge panel to the movement of a primary flight control device on an aircraft wing trailing edge. The aircraft wing is configured to be fixed to and to extend from an aircraft fuselage, the wing including a leading edge and a trailing edge. The primary flight control device is attached to the trailing edge, and any movement of the control device is directly subject to an aircraft input controller by a linear actuator. The moveable aerodynamic hinge panel, a secondary control device, is situated proximally to the primary flight control device, and the hinge panel is separately attached to the trailing edge. The bell crank mechanism slaves any hinge panel motion to movements of the primary control device.

Abstract: An electrical energy generator system for an aircraft, the system including a streamlined fairing containing at least one turbine housed in the front portion of the fairing, and an electrical energy generator connected to said turbine. The front portion of the fairing is fitted with air admission means that are movable between an open position in which the turbine is exposed to the stream of air outside the fairing and a closed position in which the turbine is masked inside the fairing. The system may serve to reduce the aerodynamic drag caused by turbulence present at a wing tip for a conventional wing having sharp edges during stages of takeoff, climbing, and cruising; and during stages of descent it makes it possible to recover the kinetic and potential energy that has been accumulated by the aircraft during its stages of climbing and cruising.

Abstract: A pet fountain assembly that includes a cover with a drinking bowl formed therein that straddles a sidewall of a basin that can be user-provided enclosing a pump within a pumping chamber defined therebetween. The cover has a downwardly extending sidewall divided by openings that can be generally U-shaped or V-shaped into a plurality of supports on which the cover. In a preferred embodiment, one of the supports is disposed outboard the basin sidewall resting on the ground and another one of the supports is disposed inboard the basin sidewall resting on a bottom of the basin providing a water passage enabling water from the basin to reach the pump. The inboard support can provide an overflow spillway as well as define a shroud disposed between the pump and water in a lower drinking bowl of the basin. The basin can include an outwardly offset seat that locates the pump.

Abstract: A pet leash is provided. The pet leash includes a housing with a handle formed thereon, a turntable rotationally disposed in the housing, and a hauling rope coiled on the turntable. The housing is provided with a rope hole for leading out the hauling rope, and the handle is provided with a button exposed out of the housing. A user can quickly restrain a pet from running away simply by pressing the button on the leash. The pet would therefore be kept within a controllable range from the user to avoid an accident. Moreover, the user can lock the leash in that state by moving a push button disposed inside the button, and then release the leash from the locked state by moving the push button in the opposite direction.

Abstract: A satellite system includes a so-called carrier satellite and a so-called piggyback satellite, each one having an Earth face. The piggyback satellite is attached to the carrier satellite by fastening elements that can be released on command. The piggyback satellite includes propulsion elements suitable for maintaining same in orbit, and the carrier satellite includes propulsion elements for performing a change of orbit of the satellite system including the carrier satellite and the piggyback satellite. The piggyback satellite is attached to the Earth face of the carrier satellite in such a way that the Earth face of the piggyback satellite is essentially perpendicular to the Earth face of the carrier satellite.

Abstract: An aerial platform receives power in the form of light, for example laser light, transmitted via an optical fiber from a remote optical power source. The platform comprises a receiver which converts at least a portion of the light to a different form of power, for example electric power. The platform also comprises a propulsion element which consumes the different form of power to generate propulsive thrust. Supplying power to the aerial platform from a remote source enables the platform to remain aloft longer than a battery or fuel tank carried by the platform would allow. Transmitting the power in the form of light is preferable in many cases to transmitting electric power, because electrical conductors are generally heavier than optical fibers, and are hazardous in the presence of lightning or a high-voltage power line.

Abstract: The invention pertains to a connecting device for connecting a first structural component and a second structural component that can be moved relative to the first structural component in an articulated fashion such that three rotatory degrees of freedom are provided.

Abstract: An aircraft landing gear including a wheel rotatable about an axle, a motor, and a bi-directional overrunning clutch, such as a roller or sprag clutch, operable to either connect the wheel with the motor or disconnect the wheel from the motor. The bi-directional clutch includes a ring-shaped overrunning track connected to the wheel by a plurality of drive keys, a ring-shaped drive track connected to the motor and concentrically aligned with the overrunning track, and a plurality of movable elements, each separately and individually movable, retained between the overrunning track and the drive track.

Abstract: A system and method is provided for controlling electric power in a plug-in vehicle, such as a pure electric vehicle or hybrid electric vehicle. The electric power is controlled from an external power source to one or more predetermined components in the plug-in vehicle. The power source is external to the vehicle and has a maximum power level. Electric power at a charging level from the external power source is received. Based on the charging level and the maximum power level, an available power level is determined. Based on the available power level, the electric power is controlled from the external power source to the predetermined components in the plug-in vehicle.

Abstract: A shape memory structure includes a plurality of bases directly attached to a composite structure and arranged along a first line at a first edge of the composite structure. A plurality of buckle-shaped shape memory structures are attached to corresponding ones of the plurality of bases, such that first ends of the plurality of buckle-shaped shape memory structures are raised relative to the composite structure. Second ends of the plurality of buckle-shaped shape memory structures are directly attached to the composite structure along a second line at a second edge of the composite structure, the second edge being opposite the first edge. When activated, the shape memory structure changes from a buckled shape to an original shape to cause the composite structure to assume a deployed shape; when deactivated, the shape memory structure to resumes a buckled shape and the composite structure an undeployed shape.

Abstract: An electrothermal heater mat for anti-icing or de-icing of a helicopter rotor blade or other aerodynamic surface comprises a substrate, such as a flexible polyimide sheet, bearing tracks of a material of selected electrical resistivity, these tracks being formed by printing onto the substrate with a thermosetting ink loaded with electrically conductive (e.g. carbon) particles. Electrical bus bars/terminals for the supply of electrical energy to the resistive tracks may also be printed, using an ink loaded with particles of higher conductivity material such as copper or silver.

Abstract: A system for indicating the pressure in an aircraft landing gear shock absorber is provided, the system comprising a source of collimated light and a target, the source of collimated light being attached to the aircraft, and being operable to emit light onto the target; the position of the point of incidence of the light emitted from the source of collimated light on the target being indicative of the pressure in the aircraft landing gear shock absorber. A kit for making such a system and a method of indicating the pressure in an aircraft landing gear are also provided.