Abstract: A fishing rod including a fishing rod body and a fishing rod holder is disclosed. The fishing rod holder may include a sleeve configured to attach to the fishing rod body. The sleeve may include a proximal extended edge and a distal extended edge. The fishing rod holder may further include a ground support structure that includes a proximal end and a distal end. The proximal end may be configured to engage with the sleeve via a locking mechanism and the distal end may include a spike configured to be inserted in ground. The ground support structure may be configured to slide along a sleeve longitudinal axis between an original position and an extended position. Further, the proximal extended edge and the distal extended edge may be configured to limit ground support structure movement along the sleeve longitudinal axis.

Abstract: Embodiments of the present invention are directed to articles used as an artificial reef and/or used as a part of an artificial reef, methods of making the articles, methods of using the articles, and methods of forming artificial reefs. The articles include a top, at least one support member, and optionally, a base. In some embodiments, the water permeability of the top of the article is greater (and in some embodiments, at least 10% greater) than the water permeability of the support, the water permeability of the optional base, or both. In preferred embodiments, the top, support(s), and optional base are formed of concrete.

Abstract: A connector, a connector assembly, an aircraft fuel breather system and an aircraft wing are disclosed. The connector connects a breather pipe or float valve to a hat section stringer duct attached to an aircraft panel. The connecter has a bridge to bridge over the duct and to cover an aperture in a wall of the duct. The bridge has a flange on either side for attachment of the connector to the panel. The connector has a seal to seal the bridge to the duct, an aperture defined in the bridge and a flow controller connector to connect and provide fluid connection between the connector and pipe or float valve. The assembly comprises the connector, the duct and aircraft panel and the fuel breather system includes one or more fuel tanks, a breather pipe and a vent to atmosphere.

Abstract: A lift unit for an aircraft, having the following features: a fan, an engine bearing axially offset from the fan, and a cylindrical electric engine having a sheath surface framed by the engine bearing.

Abstract: A vertical take-off and landing aircraft and method which uses fixed rotors for both VTOL and forward flight operations. The rotors are positioned to achieve a high span efficiency. The rotors are positioned to even out the lift across the span of the wing. The wing may also have narrow front and rear airfoils which may provide structural support as well as providing lift during forward flight, or may have a single center wing. The wing rotors are tilted forward and provide some forward propulsion during horizontal flight.

Abstract: An aircraft is disclosed, including a fuselage having a compartment configured to house refueling apparatus. An auxiliary power unit is mounted in the compartment.

Abstract: The present invention provides a rubber teat element which, on account of the radial expandability of the head part, is able to adapt to different teat geometries, in particular in the case where an animal has small, thin and short teats. A teat cup and a milking cluster with a corresponding rubber teat element are also provided.

Abstract: The invention relates to an aircraft undercarriage provided at its bottom end with a rocker arm (2) carrying at least two axles (4, 5), including one in front of a hinge between the rocker arm and the undercarriage and the other behind said hinge. According to the invention, one of the axles is fitted with one or more braked wheels (6) and the other axle is fitted with one or more motor-driven wheels (8).

Abstract: Rotor flight vehicle includes a first rotor, a power unit, a transmission from the power unit to the first rotor, wherein said transmission comprises at least one belt, a group of rotational axes, at least one power output axle connected to the power unit and at least one rotor axle connected to said first rotor, the belt is applied to the power output axle, the power output axle is concentric with a rotational axis, the belt transmits power to the rotor axle, the rotor axle is concentric with a rotational axis, wherein consecutive rotational axes of the group of rotational axes extend in a relation to each other such that the angle between them is in the range of 80-100 degrees, wherein the belt has a maximal torsion of 80-100 degrees, in the belt's transition between two respective consecutive rotational axes of the group of rotational axes.

Abstract: An oscillation system includes an oscillation circuitry configured to cause at least one motor of a first set of motors to provide an oscillation of a user-input device in at least one axis of the user-input device. The oscillation may be triggered in response to an input from at least one sensor, the user-input device for operating an aircraft control system of an aircraft. The oscillation circuitry is configured to operate independently from a resistive force circuitry. The resistive force circuitry is to provide a resistive force to the user-input device, using the at least one motor of the first set of motors.

Abstract: An anti-torque rotor is described comprising: a mast rotatable about a first axis; a plurality of blades hinged on the mast and rotatable about respective second axes to vary the respective angles of attack; a control element sliding along the first axis with respect to the mast, rotatable with the mast and connected to the blades to cause the rotation about the second axes; a control mechanism, axially sliding and angularly fixed with respect to the mast; and a connection element interposed between the control mechanism and the control element, sliding integrally with the control mechanism along the mast; the control mechanism comprises a first and a second rod; the rotor comprises a coupling, which is configured to enable/prevent rotation of the second rod with respect to the first rod when the torque exerted by the first connection element on the second rod about the first axis is greater/less than a threshold value in the event of failure of the connection element.

Abstract: The invention relates to horse bit (10, 100), comprising a mouthpiece (20, 120) configured to be inserted into a horse's mouth and comprising a first cheek (40, 140) and a second cheek (60, 160). The mouthpiece includes a first end (21, 121) and a second end (22, 122) and a center portion (30, 130) between the first end and the second end, wherein the center portion comprises at least one curved portion (31, 32; 131, 132). Each cheek includes a shank (50, 70; 150, 170) with an upper arm (53, 73; 153, 173) and a lower arm (54, 74; 154, 174) for attachment of reins and a central portion (55, 75; 155, 175) between the upper arm and the lower arm. The central portion of the first cheek is attached to the first end and the central portion of the second cheek is attached to the second end.

Abstract: An aircraft includes a wing positioned below a vertical rotor, the wing extending in a transverse direction to a wingtip having an outboard face, and a turbulence feature located on the wingtip and oriented to induce turbulence in the rotor downwash flowing across the outboard face in a direction from a top surface of the wing to a bottom surface of the wing.

Abstract: An automatic dog back scratcher system that scratches a dog, comprising a frame assembly; a housing covering the frame assembly; a movable arm assembly supported by the frame assembly and including a movable finger assembly; a treat dispenser assembly; a camera; a motion sensor; a controller configured to sense motion of an object via the motion sensor, determine the object in motion is a dog via the camera, dispense a treat via the treat dispenser assembly to attract the dog to a location adjacent to the automatic dog back scratcher system, and operate the movable arm assembly to move the arm adjacent to the dog and scratch the dog with the movable finger assembly.

Abstract: An aircraft fuselage end cargo door mechanism including a hinge rotatably coupling an aircraft fuselage end cargo door to a fuselage. The hinge being coupled to both the aircraft fuselage end cargo door and the fuselage so that an entirety of an axis of rotation of the aircraft fuselage end cargo door, defined by the hinge, relative to the fuselage is located forward of an entirety of a major joint line between the aircraft fuselage end cargo door and the fuselage. An uppermost portion of the major joint line comprises a joint line radius where a portion of the joint line radius formed by the aircraft fuselage end cargo door pivots within another portion of the joint line radius formed by the fuselage.

Abstract: Trailing edge assemblies, couplers and methods for deploying a trailing edge flap of an aircraft wing are disclosed. An exemplary method disclosed herein comprises guiding an aft portion of the trailing edge flap along an elongated track member as the trailing edge flap moves toward the deployed position; guiding a forward portion of the trailing edge flap along the elongated track member as the trailing edge flap moves toward the deployed position; and accommodating transverse movement of the forward portion of the trailing edge flap relative to the elongated track member.

Abstract: A remote piloted aircraft comprising a secondary flight assembly adapted to intervene in case of failure or an emergency of the aircraft, said secondary flight assembly being provided with an additional control unit configured to process flight relevant data and which includes an additional receiver configured to receive commands from the remote pilot by means of a remote control unit, in case of failure or emergency said additional control unit being configured to generate, as a response, an activation command adapted to activate a first device to expel an upper wing placed in a first compartment of the aircraft and to inflate a lower wing housed in a second compartment of the aircraft, and also to generate an interdiction command of the primary propulsion unit, said upper wing being maneuverable by means of a further remote control unit.

Abstract: System for precision irrigation is disclosed, the system comprises a main line. A plurality of sub main lines, wherein the plurality of sub main lines are configured to receive fluid from the main line. Further the system comprises a plurality of emitters lines emerging from at least one of the plurality of the sub main lines; wherein each emitter lines from the plurality lines has a length of at least 150 ft. A plurality of valves, wherein each valve is configured to connect at least one emitter line, from the plurality of emitter lines, with the at least one sub main line, from the plurality of sub main lines. The system further comprises a drone configured to communicably connect with the plurality of valves, wherein the drone is configured to receive a set of pre-defined instructions from a remote server and control the plurality of valves based on the instructions.

Abstract: In a hybrid flight vehicle, having multiple rotors attached to a frame, a gas turbine engine to drive the rotors; a generator connected to the gas engine to generate electric power, a battery store the electrical power generated by the generator. multiple first electric motors connected to the rotors to drive the same by the electric power supplied from the battery, a second electric motor connected to the gas turbine engine to motor the engine by the electric power supplied from the battery and a control unit to control flight, wherein the control unit stops supply of the fuel to the engine when a detected residual of the battery is equal to or greater than a predetermined value, and supplies electric power to the second electric motor to motor the engine when a detected temperature of the engine is equal to or higher than a predetermined temperature.

Abstract: An aircraft-floor element comprising a first cladding element configure to be swung from a first position to a second position. In the first position, the first cladding element is arranged parallel to a main plane of the aircraft-floor element and on a side of the aircraft-floor element which is directed towards a passenger cabin. In the second position, the first cladding is arranged at an angle to the main plane of the aircraft-floor element, wherein it forms a cladding for a cargo space. An aircraft zone having an aircraft-floor element and an aircraft having such an aircraft zone are also disclosed.