Abstract: To facilitate on-orbit servicing, such as for a refueling operation, techniques are presented for a servicing satellite to cut through the multi-layer insulation blanket of a client satellite to provide access to the client satellite without releasing unacceptable quantities of foreign object debris from the multi-layer insulation. The serving satellite includes a sealing tool, such as a pair of heater rollers, that apply pressure and heat to the insulating blanket to melt the inner layers and seal the outer layers together. The servicing satellite can then use a cutting tool to cut the sealed region and access the client satellite.

Abstract: A device for anchoring an object to a ground surface includes a hollow tubular member having respective upper end and lower end; a spiral screw piece that is supported from the lower end and that extends away from the lower end of the hollow tubular member, the spiral screw piece being for engagement with the ground surface, the upper end of the hollow tubular piece having an opening for receiving the object, a rotatable center piece supported about the hollow tubular member and disposed between the respective lower and upper ends of the hollow tubular member, the rotatable center piece adapted for free rotation relative to the hollow tubular member, and an elongated rod that engages with the hollow tubular member to assist in rotating the hollow tubular member and, in turn, the spiral screw piece in order to securely engage with the device with the ground surface.

Abstract: Disclosed is a system for receiving and sending goods delivered by a drone, including a base assembly and a barrier assembly. The base assembly comprises a platform capable of being arranged on a building, the platform is provided with a working surface; an operating area used for a drone to land and for goods to be placed is arranged on the working surface. The barrier assembly comprises a movable barrier plate. When the drone needs to land to the operating area, the barrier plate moves to a position between the building and the operating area, enabling the barrier assembly to separate the drone and a user.

Abstract: A leading edge structure (1) for a flow control system of an aircraft (101) including a double-walled leading edge panel (3) surrounding a plenum (7). The leading edge panel (3) has a first side portion (11) extending to a first attachment end (17), a second side portion (13) extending to a second attachment end (19), an inner wall element (21) facing the plenum (7), an outer wall element (23) for contact with an ambient flow (25), a core assembly (97). The outer wall element (23) includes micro pores (31) forming a fluid connection between the core assembly (97) and the ambient flow (25). The inner wall element (21) includes openings (33) forming a fluid connection between the core assembly (97) and the plenum (7). The outer wall element (23) extends from the first attachment end (17) to the second attachment end (19).

Abstract: A wing for an aircraft is disclosed having a main wing, a high lift body, and a connection assembly movably connecting the high lift body to the main wing, such that the high lift body can be moved between a retracted position and at least one extended position. The connection assembly includes a drive system having a first drive unit and a second drive unit, wherein the first drive unit has a first input section coupled to a drive shaft, a first gear unit and a first output section drivingly coupled to the high lift body. The second drive unit has a second input section coupled to the drive shaft, a second gear unit, and a second output section drivingly coupled to the high lift body.

Abstract: A vertical tail of a composite-wing unmanned aerial vehicle (UAV) having a body, a rudder face section, a rotor section, shock absorbing component and a quick installation assembly of circuit. The body includes a tail body frame and a shell. The rudder face section has a rudder machine and a rudder surface. The rudder surface is connected to one end of the tail for steering the directional deflection of the UAV. The shock absorbing component is connected to the lower end plate and the shock absorbing component absorbs the shock to the body. The quick installation assembly of circuit includes a plug, a positioning sleeve and a bias piece, the positioning sleeve is located on the outer circumference of the plug and slidingly connected to the plug, the bias piece is set between the plug and the positioning sleeve, the bias piece can absorb the impact on the plug.

Abstract: A floating pet confinement system for the recreational enjoyment of small pet owners that enables a pet to safely float on water while remaining dry and confined. The system has a buoyant base that can be inflatable or molded. Holes are formed in the top surface of the buoyant base. A pet enclosure with an open bottom is set atop the top surface. The pet enclosure engages the holes on the buoyant base when the pet enclosure is upright. However, the pet enclosure is free to disengage from the holes and fall away from the buoyant base should the buoyant base tip. A pet is placed within the enclosure atop the buoyant base. Should the buoyant base tilt past a certain angle of inclination, the pet enclosure will fall away from the buoyant base. The pet is then free to exit the enclosure through the open base of the enclosure.

Abstract: A piloting device for piloting an aircraft comprises a first and a second control stick mounted movable on a support. The device comprises a priority selection module configured to switch the first and second control sticks between a piloting configuration and a non-piloting configuration. The device further comprises a detection system for detecting the positions of the first and second control sticks; a first and second actuation system configured to generate respective first and second forces on the respective first and second control stick; and a control module configured to control the actuation system of the control stick which is in a non-piloting configuration such that the positions of the control sticks are identical.

Abstract: The presently disclosed subject matter includes a system and a method for launching a projectile towards a target, wherein the system comprises a control circuitry, a booster engine, and one or more thrusters adapted to be connected to the projectile and capable of being spun during launch around a longitudinal axis of the projectile, the control circuitry being operatively connected to the one or more thrusters; wherein responsive to ignition of propellant stowed in a combustion chamber of the booster engine, the booster engine causes the projectile to launch from its cell; following launch of the projectile, cause the projectile to turn at a certain rate and a certain azimuth.

Abstract: An aircraft includes a main body having an empennage, a main rotor assembly mounted on the main body, and a movable control surface assembly supported on the empennage. The movable control surface assembly includes a tube extending from the empennage along a tube axis to a free end, the tube being supported for rotation about the tube axis with respect to the empennage, and a movable control surface mounted on the tube for rotation therewith. The movable control surface is supported on the tube by a connection element that couples the movable control surface to the free end of the tube to rotatably fix the movable control surface with respect to the tube.

Abstract: Embodiments provide a VTOL aircraft including a plurality of tilting propeller assemblies each coupled to a support structure and configured to transition between a vertical flight and a forward flight position. Each tilting propeller assembly comprising a propeller and a movable fairing provided downstream of the propeller. The movable fairing is configured to extend along an axis of rotation of the propeller. When the tilting propeller assembly transitions between the vertical and forward flight position, the movable fairing is configured to swivel to extend parallel to the direction of resultant airflow over the tilting propeller assembly into a minimum drag orientation. The movable fairing is damped enough to prevent any oscillations from the propeller wake shedding, and at the same time, keep the propeller aligned in a minimum-drag orientation with the resultant flow.

Abstract: The present invention provides an engine 310 of a vertical take-off and landing aircraft 300, wherein the engine is configured to be movable with respect to an aircraft component 342 of the aircraft 300 between a hover position for take-off and landing, and a cruise position for forward flight, wherein the engine 310 comprises an aerodynamic component 332 having at least one aerodynamic element 334 movable between a first position 336 according to a first operational state of the aircraft, and a second position 338 according to a second operational state of the aircraft, the aerodynamic element defining an aerodynamic surface in contact with an airstream passing through the engine.

Abstract: A three piece failsafe clevis includes a center portion having a center top surface, a planar first outer surface and a planar second outer surface. The second outer surface is oppositely oriented to the first outer surface. A channel in the center portion is configured to receive a tension and compression member. A left lateral portion is connected adjacent the first outer surface. The left lateral portion has a planar first inner surface received against the first outer surface and a left top surface coplanar with the center top surface. A right lateral portion is connected adjacent the second outer surface. The right lateral portion has a planar second inner surface received against the second outer surface and a right top surface coplanar with the center top surface.

Abstract: Module for operational control of the guided advance/withdrawal device of the needle added to the smart substance injection device on board equipment for inoculating substances inside a fertile egg and smart method for injection inside a fertile egg, wherein the “inoculation of substances” inside a fertile egg, be this into the embryo, in the case of vaccines, and even into the amniotic fluid, in the case of a nutrient or nutritional vaccine complex, allows the injection needle (11) to be brought close at a controlled speed.

Abstract: A horizontal stabilizer assembly includes a stabilizer connector assembly having a center multi-spar box, a first horizontal stabilizer having a first multi-spar box connected to a first side of the center multi-spar box with a plurality of first lug and clevis connections, and a second horizontal stabilizer having a second multi-spar box connected to a second side of the center multi-spar box, opposite the first side, with a plurality of second lug and clevis connections.

Abstract: A leading edge structure (1) for a flow control system of an aircraft (101) including a double-walled leading edge panel (3) with a first side portion (11) extending to a first attachment end (17), a second side portion (13) extending to a second attachment end (19), an inner wall element (21) facing a plenum (7), an outer wall element (23) facing ambient flow (25), and a core assembly (97). The outer wall element (23) includes micro pores (31) and the inner wall element (21) includes openings (33) which form a fluid connection from ambient flow, through the core assembly (97) and to the plenum (7). The thickness of the outer wall element is reduced due to the first attachment end (17) and/or at the second attachment end (19) attached to the inner wall element (21) by both bonding and fasteners (85, 87, 89, 91).

Abstract: An air vehicle has an airframe, aerodynamic lift-generating wings, and a propulsion system. The propulsion system provides propulsion to the air vehicle in powered aerodynamic flight mode and in vectored flight mode, and stability and control in vectored flight mode. The propulsion system includes a first set of non-pivotable first propulsion units, arranged in polygonal arrangement with respect to the airframe, enclosing the air vehicle center of gravity, providing a fixed vertical thrust vector and an aggregate vertical thrust sufficient for enabling vectored flight mode. The propulsion system includes a second set of pivotable second propulsion units, arranged in spaced relationship with respect to the center of gravity, and provide vectored control moments to the air vehicle in three rotational degrees of freedom.

Abstract: A vertical takeoff and landing (VTOL) aircraft is configured with a front set of propellers mounted to a front wing and an aft set of propellers mounted to an aft wing wherein the propellers may be repositioned by rotating them around a front thrust vectoring axis and an aft thrust vectoring axis respectively. The positioning of the propellers with respect to the thrust vectoring axes and the positioning of the thrust vectoring axes with respect to the upper and lower limits of the passenger compartment ensure that, as the propellers are rotated from a vertical thrust position to a horizontal thrust position, the plane of rotation of the propellers never intersects with the portion of the passenger compartment where a failure of propeller components could result in debris penetrating the passenger compartment and causing injury.

Abstract: A vertical take-off and landing aircraft may include a fuselage; at least one wing connected to the fuselage; a first plurality of proprotors mounted to the at least one wing, positioned at least partially forward of a leading edge of the at least one wing, and 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; and a second plurality of proprotors mounted to the at least one wing, positioned at least partially rearward of a trailing edge of the at least one wing, and 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; wherein the first plurality of proprotors and the second plurality of proprotors are independently tiltable.

Abstract: A separated lift-thrust (SLT) aircraft includes a longitudinal-thrust engine and articulated electric rotors, at least some of which are variable-position rotors having variable orientations based on rotor position signals. Control circuitry independently controls thrust of the longitudinal-thrust engine and the thrust and orientation of each of the variable-position rotors, relative to the aircraft lifting surface and longitudinal thrust engine, to provide for commanded thrust-vectoring maneuvering of the aircraft during VTOL, fixed wing flight, and intermediate transitional states, including maintenance of a desired pose of the lifting surface independent of orientation of the rotor orientations when hovering the aircraft in windy conditions. A flight and navigation control system automates flight maneuvers and maintains desired aircraft pose and position relative to static or dynamic coordinates during station keeping, tracking, avoidance, or convergence maneuvers.