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.

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: Vertical short takeoff and landing (VSTOL) aircraft include primary airfoils extending outwardly from a forward region of the aircraft fuselage, and secondary empennage airfoils extending outwardly from an aft region of the aircraft fuselage so as to be separated from the forward primary airfoils and thereby define a space therebetween which accommodates non-cyclic controllable propellers operably driven by a respective engine of a propulsion unit. The propulsion units are mounted for pivotal movement within the defined space between the primary airfoil and the secondary empennage airfoils so as to achieve a first operational position wherein the thrust line of the propellers is orientated substantially parallel to the longitudinal axis of the fuselage and a second operational position wherein the thrust line of the propellers is oriented substantially perpendicular to the longitudinal axis of the aircraft. The propulsion units may be mounted aft of the aircraft center of gravity (CG).

Abstract: Disclosed herein is a helicopter flight support for use in case of emergencies. The helicopter flight support comprises a motor which causes a threaded shaft to turn which is coupled to an underside of the helicopter. This causes outer supports and inner supports to be deployed until they reach a wing-like configuration. The interior of the wing comprises a plurality of support cables for tensioning the wing. The helicopter flight support further comprises upper and lower support cables mounted to the tips of the wing to provide horizontal stability.

Abstract: Provided herein are various enhanced systems, apparatuses, and techniques for on-surface analysis of celestial or terrestrial surfaces, such as for discovery and analysis of water ice deposits, locations, abundances, and depths. An example herein includes a swarm of spherical payloads sequentially deployed by a deployment host across a large area of a surface to impact the surface, sense properties of the surrounding environment using avionics and scientific instrumentation, and to establish a communication network to collect and transmit collected data.

Abstract: A support structure to mount landing gear to a wing spar of an aircraft. The support structure includes a trunnion assembly having a first trunnion and a second trunnion that are connected together with the first trunnion positioned on a first side of the wing spar and a second trunnion positioned on an opposing second side of the wing spar. The trunnion assembly is configured to support a first section of the landing gear.

Abstract: A teeter flap lock for an aircraft may include at least one pair of diametrically positioned teeter flap lock plates extending from a rotor teetering hinge, spaced apart from a rotor mast of the aircraft. A teeter flap lock block is positioned about the rotor mast and is configured to fit between the teeter flap lock plates and the rotor mast. The teeter flap lock block fits between and contacts the teeter flap lock plates in an engaged position, and is movable between the engaged position and a disengaged position relative to the teeter flap lock plates. The teeter flap lock enables flapping of rotors coupled to the rotor mast via the teetering hinge when the teeter flap lock block is in the disengaged position and disables flapping of the rotors when the teeter flap lock block is in the engaged position.

Abstract: A rotor blade assembly connectable to a rotor hub configured to rotate about a center axis includes a torsional pitch member coupled to the rotor hub, a torque tube coupled to the torsional pitch member, wherein the torsional pitch member extends away from the center axis through a portion of the torque tube, a blade coupled to the torque tube, and a pitch control member coupled to the torque tube and configured to control a pitch angle of the blade, wherein the torsional pitch member includes a first curvilinear channel and a second curvilinear channel each having a front side and a back side, wherein the first curvilinear channel and the second curvilinear channel are disposed adjacent to each other, such that the back side of the first curvilinear channel faces the back side of the second curvilinear channel.

Abstract: A satellite assembly is disclosed, including a satellite and a shroud. The satellite is stowed in a launch vehicle and the shroud includes a frame supporting a flexible thermal blanket enclosing the satellite.

Abstract: A variable-sweep wing VTOL (vertical take-off and landing) aerial vehicle with distributed propulsion adapted for VTOL flight and horizontal flight includes a fuselage, a pair of symmetrical swiveling canards extending outward from forward portion of the fuselage, a pair of first symmetrical wings extending outward from the upper-rear portion of the fuselage and a pair of second symmetrical wings extending outward from the lower-rear portion of the fuselage. The first and second wings are spaced apart longitudinally and vertically. The pylon joins the first wing and second wing at the tip to form the box-wing. The wings can transition between VTOL mode or airplane mode. The wings are mounted with rotors for propulsion. Moreover, at the trailing edge of the wings, the blown flap work as blown lift system for both VTOL flight or STOL flight. Finally, the fuselage mounted pusher rotor provides propulsive thrust for horizontal flight.

Abstract: An aircraft including a fuselage extending in an aircraft longitudinal direction, a wing coupled to the fuselage and extending in an aircraft lateral direction perpendicular to the aircraft longitudinal direction, and a displacement assembly configured to translate the wing relative to the fuselage in the aircraft lateral direction between a flight position and a stowed position. In the flight position, the displacement assembly is positioned at a central portion between opposite end portions of the wing such that the displacement assembly is positioned a first distance from one of the end portions of the wing. In the stowed position, the displacement assembly is positioned proximate one of the end portions of the wing such that the displacement assembly is positioned a second distance from the one of the end portions of the wing, the second distance being less than the first distance.

Abstract: Disclosed are systems and methods for reconnectably coupling an aft vehicle to a forward vehicle in flight. A docking structure is affixed to the forward vehicle. A coupler has a line connection portion, a probe receiver port, and a plurality of aerodynamic controls. The probe receiving port receives and releasably retains a probe portion of the aft vehicle. A tow line has a proximal end, a distal end, and a line extension length. The proximal end may be attached to the tow actuation element. The distal end is connectable to the coupler. The tow actuation element is configured to adjust the line extension length. The aerodynamic control elements are configured to adjust lateral and vertical positioning of the coupler with respect to the probe portion when the system is in flight. Movement of the coupler is restrained with respect to the docking structure when docked thereto.

Abstract: The present invention relates to an apparatus for weed control. It is described to provide (210) a processing unit with at least one image of an environment. The processing unit analyses (220) the at least one image to determine at least one location within the environment for activation of at least one mulch application unit. The at least one mulch application unit is configured to apply at least one mulch to the at least one location for weed control. An output unit outputs (230) information that is useable to activate the at least one mulch application unit.

Abstract: Examples include an apparatus for restraining an aircraft during engine acceleration, the apparatus including: a collet shaft that is configured to attach to the aircraft, a rod that is configured to attach to a runway, and a release mechanism that is configured to restrain the collet shaft to the release mechanism and configured to release the collet shaft in response to the release mechanism receiving an electric current.

Abstract: A wing leading-edge device is disclosed having a slat body having a front side with a forward skin and a back side with a rearward skin, and at least a drive arrangement having at least one lug and a slat track, wherein the back side extends between an upper spanwise edge of the forward skin and a lower spanwise edge of the forward skin. The back side is defined by a continuously curved profile contour for receiving a fixed leading edge, and the at least one lug is at least partially arranged between the back side and the front side. The slat track is coupled with the first lug. The connection points to the slat body are shifted far forward to improve the load introduction and reduce moments acting on the drive mechanism.

Abstract: A transport system for an animal to be received in a motor vehicle. The transport system comprises a carrier configured to be received on a transport surface of the motor vehicle and a boarding aid including a first tread element and at least a second tread element. The first tread element can be swivelably attached to the carrier, wherein the boarding aid is movable from a transport position to a boarding position. The boarding aid can be arranged in the transport position on a first side of a plane defined by the carrier, and the boarding aid is an obstacle for the animal after the transport system has been received in the motor vehicle. The boarding aid can be arranged in the boarding position on a second side of the plane defined by the carrier and the animal is able leave the motor vehicle via the boarding aid.

Abstract: Embodiments are directed to a tiltrotor aircraft having a wing, a proprotor pivotably mounted on the wing, and a downstop striker attached to the proprotor using a load pin, wherein the load pin is configured to generate an output signal representing a force between the proprotor and the wing. A downstop mounted on the wing is aligned to be in contact with the downstop striker when the proprotor is in a horizontal position. A conversion actuator moves the proprotor between a horizontal position and vertical position. A flight control computer is coupled to the output signal from the load pin and configured to control the conversion actuator, wherein the flight control computer is configured to cause the conversion actuator to increase the force if the force is less than a first selected preload value or to decrease the force if the force is greater than a second selected preload value.

Abstract: Open-sea aquaculture systems and methods are provided, which employ a semisubmersible platform with vertical columns, having storage and maintenance facilities for supporting aquaculture. Systems comprise a rigid assembly of aquaculture cages, with vertical cavities having forms configured to receive the corresponding vertical columns of the semisubmersible platform. The rigid assembly is mechanically connected to the semisubmersible platform in operational positions: (i) a raised position in which the rigid assembly encloses the corresponding vertical columns in the vertical cavities to limit a horizontal movement of the rigid assembly, and (ii) a lowered position in which the rigid assembly is below the corresponding vertical columns. Systems further comprise a control unit configured to control the mechanical position control mechanism to lower the rigid assembly upon occurrence of specified rough sea conditions, or whenever needed, and to raise the rigid assembly upon specified conditions.

Abstract: Convertiplane comprising a fuselage; a pair of wings, a pair of nacelles fixed with respect to the wings, and a pair of rotors rotatable about respective second axes and tiltable about a third axis between a first position, reached when the convertiplane is in an aeroplane configuration, and a second position, reached when the convertiplane is in a helicopter configuration. The wing comprises a wing box and a first appendage movable when the convertiplane is in the aeroplane configuration, between a first neutral position, a second raised operating position, and a third lowered operating position; the wing comprises a second appendage movable between a first neutral position assumed when the convertiplane is in the aeroplane configuration and in which it defines an extension of the wing box, and a second position assumed when the convertiplane is in the helicopter configuration and in which it defines, with the wing box, an opening through which the downwash generated by the rotor can flow.

Abstract: A system for disconnecting a battery from an electric aircraft upon impact. The system includes an electric aircraft and a battery assembly electrically coupled to the electric aircraft. The battery assembly is configured to include at least a sensor. The at least a sensor is configured to detect impacts to the electric aircraft. The battery assembly is configured to include a connector. The connector attaches the battery assembly to the electric aircraft. The connector includes an electrically actuating disconnection mechanism. The battery assembly is configured to include a control circuit. The control circuit is electrically connected to the electrically actuating disconnection mechanism. The control circuit is configured to detect, using the at least a sensor, an impact to the aircraft. The control sensor disconnects the connector from the electric aircraft using the electrically actuating disconnection mechanism as a function of the detection of impacts to the electric aircraft.