Abstract: Scratching apparatus 1 comprising a plurality of scratchable sacrificial elements 7 that can be assembled together to form a tower 5, and a base 3 having a first surface on which the tower 5 can be mounted so that the tower 5 is generally upstanding from the base 3 when the apparatus 1 is in use.

Abstract: A method to modify an aircraft including: disconnecting a first engine control device from command cables and transmission cables, wherein the first engine control device is in a fuselage section forward of a pressure bulkhead; replacing the engine control device with a jumper connector positioned in the fuselage section, wherein the jumper connector electrically connects the command cables to the transmission cables; installing a second engine control device in the fuselage aft of the pressure bulkhead, wherein the second engine control device is in an engine compartment of the fuselage; connecting the second engine control device to transmission cables at a location at or near the pressure bulkhead; connecting sensor cabling directly to the second engine control device, and connecting the engine control device directly to the engine.

Abstract: A window unit for an aircraft includes a wall module having a side wall laterally delimiting an aircraft cabin. The side wall has a window opening and the wall module has retaining portions. A window module has a window frame accommodating at least one windowpane and the window module has fastening portions. A fastening configuration fastens the window module on the side wall in a region of the window opening. The fastening configuration is formed by a respective fastening portion engaging with a respective retaining portion. The retaining portions and the fastening portions are movable into a plug-in position by a plug-in movement of the window module and are movable from the plug-in position into a securing position by a rotary movement of the window module. The wall module and the window module are interconnected by a form-locking connection in the securing position.

Abstract: A propulsion system for an aircraft, comprising at least one rotor and a nacelle fairing extending around the at least one rotor with respect to an axis of rotation of the rotor, the nacelle fairing comprising: an upstream section forming an inlet section of the nacelle fairing; a downstream section wherein a downstream end forms an outlet section of the nacelle fairing; and an intermediate section connecting the upstream and downstream sections, wherein the downstream section comprises a radially inner wall and a radially outer wall made of a deformable shape memory material, and further comprising at least one actuator mechanism with at least one cylinder configured to cooperate with one or more components, projections, etc., embedded in an inner surface of the radially outer wall so as to vary an outer diameter of the outlet section between a minimum diameter and a maximum diameter.

Abstract: The present invention is to a collar for animals that can be converted on-the-fly for use in both training purposes by providing cinching around the animal's neck and for non-training purposes wherein the cinching is reduced or prevented.

Abstract: Disclosed is a plant growing system (100), comprising: a plurality of plant growing zones (122); a control apparatus (120) configured to control one or more environmental conditions in each of the plurality of plant growing zones (122); and a receiver (142) configured to receive input data indicating plant type characteristics of a plurality of plant characteristics types to be grown in a plant growing apparatus (120). Also disclosed is a plant growing apparatus (120) configured to grow a plurality of plant types, a method to control a plant growing apparatus (120) configured to grow a plurality of plant types, and a computer program including computer-readable instructions executable to perform a method to control a plant growing apparatus (120) configured to grow a plurality of plant types.

Abstract: A rotorcraft has a horizontal stabilizer movable about an axis of rotation and a horizontal stabilizer control system configured to control the horizontal stabilizer to at least one of move the rotorcraft into a minimum drag position, maintain the aircraft in a minimum drag position, efficiently achieve a maneuver, enter efficient autorotation, and maintain efficient autorotation.

Abstract: An aircraft seating module (20) includes a seating mount (26) having a horizontal mounting rail (28) integrally joined to a vertical mounting post (30) at an adjoining elbow (32). The rail (28) includes a mounting boss (34) longitudinally spaced from the post (30) for attachment to an aircraft cabin seat track (18). Both the rail (28) and post (30) include mounting holes (38) for attaching a passenger seat (22) and appended furniture (24) directly to the seating mount (26) and in turn indirectly to the seat track (18) in the cabin floor (12).

Abstract: An aircraft fuselage body is constructed of an upper body section having a curved cross-section configuration and a lower body section having a curved cross-section configuration. The upper body section and the lower body section are joined together to form an aircraft fuselage body by splice straps that are secured, end to end along interior surfaces of the upper body section and the lower body section. The aircraft fuselage body being constructed of an upper body section and a lower body section enables installation of systems separately into the upper body section and the lower body section prior to the upper body section and lower body section being joined together.

Abstract: A method and apparatus for facilitating the attachment of an internal module in an internal space of an aircraft part is disclosed. The attachment device includes at least one attachment member comprising an attachment shank, a chamber for introducing the attachment member, the chamber including a first orifice through which the attachment shank passes in the installed configuration of the internal module, and a second orifice which serves for the introduction of the attachment member into the chamber from the outside.

Abstract: Embodiments of the present disclosure generally relate to fishing lures, and more particularly, to attachable floats for artificial fishing lures. In one embodiment, a float comprises a buoyant body having a first end, a second end opposite the first end, and an outer wall connecting the first and second ends. The float comprises a keeper extending from the body. The keeper is configured to attach the body to a polymeric artificial lure.

Abstract: A leading edge structure for a flow control system of an aircraft is disclosed having a leading edge panel that surrounds a plenum, wherein the leading edge panel has a first side portion, a second side portion opposite the first side portion, an inner surface facing the plenum and an outer surface in contact with an ambient flow, and wherein the leading edge panel comprises a plurality of micro pores forming a fluid connection between the plenum and the ambient flow, wherein the plenum is connected to an air outlet arrangement configured for causing an underpressure in the plenum, so that air from the ambient flow is drawn through the micro pores into the plenum and from there discharged through the air outlet arrangement into the ambient flow.

Abstract: A releasable attractor blade system is provided. One embodiment has an attractor blade defined by an aperture proximate to an edge of a leading blade portion, defined by a release slot proximate to an edge of a trailing blade portion of the attractor blade. A release system has a retainer at the first end of a cord that passes through the aperture and is configured to be frictionally retained outside of the aperture; a release hook at the second end of the cord that is inserted into the release slot of the attractor blade to releasably secure the releasable attractor blade system to the attractor blade release system; and an elastic portion secured between the first and second cord ends, wherein the release system holds the attractor blade in position along a longitudinal axis of the attractor blade during trolling so that the attractor blade attracts game fish.

Abstract: An aircraft nacelle air intake includes sectors each having a lip forming portion, an outer panel forming portion and an inner panel forming portion. The outer panel forming portions and lip forming portions are formed by a continuous one-piece wall. At at least one junction between two adjacent sectors, an opening and a hatch are provided between the outer panel forming portions of the sectors. The inner panel forming portions and the lip forming portions of the sectors are edge to edge and fixed to each other by fixing devices accessible from the inside of the sectors and invisible from outside of the sectors. A maintenance method in which, when a zone of a sector is damaged, the sector concerned is removed as a whole and is replaced by a new of “recycled” sector is also described.

Abstract: An electric aircraft includes rotors for providing lift for vertical take-off and landing of the aircraft, proprotors that are tiltable between lift configurations for providing lift for vertical take-off and landing of the aircraft and propulsion configurations for providing forward thrust to the aircraft, a first battery pack for powering a first rotor and a first proprotor, a second battery pack for powering a second rotor and a second proprotor, a first electric power bus electrically connecting the first battery pack to the first rotor and proprotor, and a second electric power bus electrically connecting the second battery pack to the second rotor and proprotor, wherein the second electric power bus is electrically isolated from the first electric power bus.

Abstract: A propulsion system for providing propulsion of an aircraft includes a plurality of electric motors coupled with a rotor of the aircraft to drive the rotor and a propulsion motor control. The propulsion motor control includes at least one processor electrically connected with at least one electric motor to actuate the at least one electric motor and at least one battery electrically connected with the at least one processor and at least one electric motor to provide power to the at least one processor and the at least one electric motor. The propulsion motor control actuates the plurality of electric motors based on a desired torque level to drive the rotor to provide propulsion of the aircraft.

Abstract: A method and system for attaching a vertical stabilizer to an aircraft fuselage using a clevis system is disclosed. A composite skin is installed over the aircraft fuselage. The composite skin has apertures for receiving a plurality of clevises in a clevis system. The plurality of clevises is inserted through the apertures in the composite skin. Each of the plurality of clevises is secured to a frame member in the aircraft fuselage. The vertical stabilizer has a multi-spar box connected with a base rib assembly having a plurality of lugs. The base rib assembly of the vertical stabilizer is engaged with the clevis system. The plurality of lugs in the base rib assembly is secured to the plurality of clevises in the clevis system. Attachment of the vertical stabilizer to the aircraft fuselage, as well as subsequent inspection, may be performed from outside the aircraft.

Abstract: A display vase adapted to hold a variety of longitudinal stems or sticks, the vase including a retainer mountable within the transparent vase that can hold a multitude of display items. The retainer may sit on a shelf or retaining ring inside the vase. The retainer may include an array of hexagonally shaped cells that may interlock with a lower level of interlocking cells. Also included is a method of arranging and displaying stemmed items in a vase. A retainer is set in a vase and stems are secured therethrough, preferably into a frog apparatus at bottom of vase.

Abstract: A knotless coupler for securing a fishing line to a fishing implement is disclosed. The knotless coupler comprises a shaft portion and a nut. The shaft portion is configured to be attached to the fishing implement. The shaft portion comprises a plurality of external threads and an external line-receiving groove formed across at least some of the external threads. The nut is configured to be threadably engaged with the external threads of the shaft portion. The nut is movable between a non-gripping position and a line-gripping position. A portion of the fishing line is inserted through an opening in the nut and into the external line-receiving groove when the nut is in the non-gripping position. The portion of the fishing line is secured within the external line-receiving groove by the nut when the nut is in the line-gripping position.

Abstract: Various embodiments of space launch vehicle systems and associated methods of manufacture and use are disclosed herein. In some embodiments, the systems include a reusable, horizontal takeoff/horizontal landing (HTHL), ground-assisted single-stage-to-orbit (SSTO) spaceplane that is capable of providing frequent deliveries of people and/or cargo to Low Earth Orbit (LEO). In some embodiments, the spaceplane can takeoff with the aid of a rocket-powered sled that, in addition to providing additional thrust for takeoff, can also provide propellant for the spaceplane engines during the takeoff run so that the spaceplane launches with full propellant tanks.