Abstract: A system for installing a self-supporting truss structure having interconnected truss elements on an aircraft fuselage. The truss structure has radially outer closed truss nodes and radially inner releasable connecting nodes. The installation system has a carrying device, movable on a fuselage floor and with an upper receptacle, a stand for temporarily holding truss elements in predetermined relative positions, and a movement device, on the upper receptacle, and holding the stand in a settable position relative to the support surface. The stand is further away from the support in installation positions than in a transport position. The installation system is configured, with the stand in the transport position, to move the carrying device into a predetermined internal fuselage position and to lock it there, to move the stand into a suitable installation position via the movement device, and to lock the at least one lockable connecting node via a drive.

Abstract: A method according to certain embodiments generally involves operating a system including an unmanned aerial vehicle (UAV) and a base station. The base station includes a nest including an upper opening having an upper opening diameter and a lower opening having a lower opening diameter less than the upper opening diameter. The lower opening is accessible from within the base station. The method generally includes landing the UAV within the nest such that a portion of the UAV is accessible via the lower opening, releasably attaching a load to the UAV, and operating the UAV to deliver the load to a destination.

Abstract: An introduced autonomous aerial vehicle can include multiple cameras for capturing images of a surrounding physical environment that are utilized for motion planning by an autonomous navigation system. In some embodiments, the cameras can be integrated into one or more rotor assemblies that house powered rotors to free up space within the body of the aerial vehicle. In an example embodiment, an aerial vehicle includes multiple upward-facing cameras and multiple downward-facing cameras with overlapping fields of view to enable stereoscopic computer vision in a plurality of directions around the aerial vehicle. Similar camera arrangements can also be implemented in fixed-wing aerial vehicles.

Abstract: A hover-capable flying machine such as a drone includes a robotic arm extending from the body, and an instrumentality for balancing the machine in response to disturbances such as those caused by picking up and dropping of the payload by the extended robotic arm. In embodiments, the end of the arm is equipped with a balancing rotor assembly that may provide lift sufficient to counteract the weight of the payload and/or of the arm. In embodiments, the machine's power pack is shifted in response to the disturbances. The power pack may be moved, for example, on a rail within and/or extending beyond the machine in a direction generally opposite to the extended arm. The power pack may also be built into a bandolier-like device that can be rolled-in and rolled out, thus changing the center of gravity of the machine.

Abstract: A drone system and method for deploying and autonomously refuelling. The drone system includes a base station and a drone. The base station and drone are configured for autonomous refuelling when the drone has landed in the base station. The base station also provides portability and security of the drone.

Abstract: An unmanned aerial vehicle launch tube that has a tube, a sabot disposed in an interior of said tube, said sabot having a first clasp tab, and a clasp detachably coupled to said first clasp tab and contacting an inner circumferential wall of said tube so that said clasp is rotationally constrained by the inner circumferential wall and said first clasp tab.

Abstract: In accordance with at least one aspect of this disclosure, a contoured class divider for dividing an aircraft cabin arrangement between at least one forward passenger seat and at least one aft passenger seat, includes a panel positioned adjacent to and rearwardly of the at least one forward seat. The panel has a contoured shape for receiving the back of the forward passenger seat in at least one of a reclined position and an upright position. The panel extends substantially from an underside of an overhead bin to a cabin floor. In embodiments, at least a portion of the panel is configured to deform or break during a crash event due to one or more of a head impact by a passenger in the aft passenger seat with the panel and/or inertial forces of the crash event acting on the panel.

Abstract: A propulsion system of an aircraft includes a hybrid electric gas turbine engine, and a nacelle at least partially enclosing the hybrid electric gas turbine engine. The nacelle includes a first nacelle half and a second nacelle half. Each of the first nacelle half and the second nacelle half include an outer nacelle sleeve, an inner nacelle sleeve radially offset from the outer nacelle sleeve such that a flowpath is defined between the outer nacelle sleeve and the inner nacelle sleeve, and an upper bifurcation connecting the outer nacelle sleeve to the inner nacelle sleeve at an upper end of the nacelle. The flowpath is circumferentially continuous between the upper bifurcation of the first nacelle half and the upper bifurcation of the second nacelle half.

Abstract: An adjustable lift modification wingtip may be attached to a baseline wing of an aircraft. The adjustable lift modification wingtip may comprise a horizontal portion including a control surface and a vertical portion coupled to the horizontal portion. The vertical portion may move about an axis that may be substantially perpendicular to the horizontal portion. The control surface and the vertical portion may be adjusted in conjunction to increase wing efficiency at a flight condition.

Abstract: A cleaning system and a method suitable for an ultra-large-scale photovoltaic power station are provided; including a control terminal, an intelligent control center, and a large-load unmanned helicopter, the control terminal is provided with an operation interface to receive an instruction from an operator and transmit the instruction to the intelligent control center through a wireless communication, the intelligent control center is provided with a processor, a wireless communication module, a flight monitoring and control module, and a data feedback and optimization module; the present invention adopts the above system and method, the use of large-load unmanned helicopters is wide, which is more suitable for ultra-large-scale photovoltaic power stations, the high-pressure gas-liquid two-phase flow cleaning device is mounted on the large-load unmanned helicopter, which can carry out precise cleaning operations along the arrangement of photovoltaic panels, and spray high-pressure water and gas to remove dus

Abstract: A portable launch and landing pad for a rotor drone is disclosed, comprising a circular arrangement of rigid panels, each having a generally triangular profile shape. The rigid panels are connected by hinges along their side edges, allowing articulation between adjacent panels. This design enables the launch and landing pad to be easily, compactly transported and assembled, providing a stable and secure platform for the rotor drone during takeoff and landing operations. This design may better hug or conform to undulating terrain, and does not blow away when drone thrust hits the pad. This may provide benefits of keeping a drone camera lens and gimbal clean, preventing prop strikes and lens strikes from pebbles or tall grass, and preventing dirt and debris from entering motor bearings and shortening useful life.

Abstract: An assembly including a wing with a pressure-side panel and a suction-side panel through which two bores pass, an engine pylon including a blade with three bores and two fastening lugs, each of which has a sixth bore, two first shackles fastened between the blade and the suction-side panel, two second shackles fastened between the blade and the suction-side panel and two fittings, which are fastened beneath the pressure-side panel and each have a female clevis for housing a fastening lug therein.

Abstract: The consumption of stored energy by an unmanned aerial vehicle is reduced by raising the unmanned aerial vehicle through an unmanned aerial vehicle support device, and accordingly, the cruising distance is increased. An unmanned aerial vehicle support device 10 includes a loading unit 1 and a control unit that controls raising and lowering of the loading unit. The loading unit 1 is raised to a predetermined height to enable the unmanned aerial vehicle 100 to take off. An unmanned aerial vehicle support system includes a server 5 that can communicate with the unmanned aerial vehicle support device 10 and selects a route on which the unmanned aerial vehicle 100 flies and one or more unmanned aerial vehicle support devices 10 on the route based on movement information including at least a departure point and a destination of the unmanned aerial vehicle input from the outside.

Abstract: An apparatus for facilitating the landing and takeoff of electric vertical takeoff and landing aircraft (EVTOL) can comprise a moveable landing platform, a moveable charging assembly comprising a high voltage cable adapted for electrical, magnetic induction positioned within a vertically moveable column having a magnetic plate and multiple access connections, and weight sensors positioned on the landing platform. The weight sensors are operatively connected to the charging assembly such that when the sensors detect the landing of an EVTOL on the platform, the sensors trigger the charging assembly to rise up to contact the EVTOL and begin charging the EVTOL.

Abstract: According to various embodiments, there may be provided a monocopter. The monocopter may include a body chassis. The monocopter may further include a wing structure extending from the body chassis, the body chassis being at a root of the wing structure. The wing structure may include a plurality of rigid wing segments distributed along a spanwise direction extending between the root and a tip of the wing structure. The wing structure may further include a plurality of flexible wing segments, each flexible wing segment adjoining a pair of adjacent rigid wing segments of the plurality of rigid wing segments. The monocopter may further include a propulsion unit coupled to a rigid wing segment of the plurality of rigid wing segments between a midspan of the wing structure and the tip of the wing structure.

Abstract: A wing load support structure of a fuselage includes a first joint on a front spar of a wing unit of the fuselage, a center bulk head including a first spar joint coupled to the first joint and configured to support a vertical load of the front spar transmitted by the wing unit, a second joint mounted on a rear spar of the wing unit, a spar cover including a second spar joint coupled to the second joint and connected to a rear bulk head by a bulk head upper support, and a support unit configured to support the spar cover and the rear bulk head inside the fuselage and configured to support a vertical load of the rear spar transmitted by the wing unit.

Abstract: An unmanned aerial vehicle (UAV) includes a fuselage, a power driving unit, and an UAV arm. The UAV arm includes a cantilever, a mounting base, and a connecting portion. The mounting base is connected to a first end of the cantilever. The mounting base is configured for a power driving unit of the UAV to be mounted. The connecting portion is connected to a second end of the cantilever. The connecting portion is configured to be connected to the fuselage of the UAV. An upper end of a cross section of the cantilever is arc-shaped, and a lower end of the cross section of the cantilever is pointed. The cross section of the cantilever is a section perpendicular to a direction from the first end of the cantilever toward the second end of the cantilever.

Abstract: A satellite apparatus is disclosed, including a housing having first and second opposing walls, and a support structure inside the housing spanning the first and second walls. The support structure is structurally connected to the housing only at the first and second walls, and an end portion of the support structure is configured for connection to a launch vehicle by a separation system.

Abstract: A wing system is provided for an air vehicle, the air vehicle having a fuselage including a fuselage longitudinal axis. The wing system includes a set of wings, configured for transitioning between a stowed configuration and a deployed configuration. The set of wings includes a first said wing having a first wing tip, a first wing longitudinal axis, and a first pivot axis; and a second said wing having a second wing tip, a second wing longitudinal axis, and a second pivot axis. The first pivot axis and the second pivot axis are non-coaxial. In the stowed configuration, the first wing and the second wing are in overlying relationship such that at least a majority of a pressure surface of one wing is facing a suction surface of the other wing, and the first wing tip is spaced from the second wing tip by a first lateral spacing.

Abstract: The invention relates to a logistics station for drones, which can be adapted to different drones (12) and comprises at least one landing zone including means for holding a drone, a robot (30) for replacing the drone batteries and/or charging the drone, and a battery store (20).