Abstract: Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45? diameter) footprint.

Abstract: A torsional moment acting on a component in a drive train of an aircraft may be determined using at least one sensor, where the determined torsional moment is used for adjusting at least one adjustable damping element located in or on the component and/or for regulating a torsional stiffness in the torque-conducting component. As a result, the torsional load in the component may be reduced.

Abstract: A multicopter aircraft with boom-mounted rotors may include a fuselage; a port side wing coupled to the fuselage; and a starboard side wing coupled to the fuselage. Each of the wings has mounted thereto one or more booms, each boom having a forward end extending forward of a corresponding wing to which the boom is mounted and an aft end extending aft of said corresponding wing to which the boom is mounted. The aircraft further includes a first plurality of lift rotors, each rotor in said first plurality being mounted on a forward end of a corresponding one or said booms; and a second plurality of lift rotors, each rotor in said second plurality being mounted on an aft end of a corresponding one or said booms. Each rotor produces vertical thrust independent of the thrust produced by the other rotors.

Abstract: An underwater and aerial vehicle includes a fixing frame, a core navigation system and an energy supply system. The fixing frame has a circular ring configuration in a middle part thereof, and the waterproof sealing cabin is fixed in the circular ring configuration, and multiple cantilever arms extend around the circular ring configuration. An underwater navigation control module and a relay are provided on an auxiliary fixing platform. A second brushless motor is provided on each of the cantilever arms. Each second brushless motor is provided with a marine propeller. A flight control module, a remote control receiver and a power management module are provided on a fixing platform. A first brushless motor is provided on each of the cantilever arms. Each first brushless motor is provided with a rotor via a coupling. The energy supply system is arranged in a lower part of the waterproof sealing cabin.

Abstract: The disclosure describes an automated aerial vehicle (AAV) and system for automatically detecting a contact or an imminent contact between a propeller of the AAV and an object (e.g., human, pet, or other animal). When a contact or an imminent contact is detected, a safety profile may be executed to reduce or avoid any potential harm to the object and/or the AAV. For example, if a contact with a propeller of the AAV by an object is detected, the rotation of the propeller may be stopped to avoid harming the object. Likewise, an object detection component may be used to detect an object that is nearing a propeller, stop the rotation of the propeller, and/or navigate the AAV away from the detected object.

Abstract: Rotorcraft including a fuselage, at least three rotor system arms, a forward propulsion unit for providing forward propulsion to the rotorcraft and a flight control system. Each rotor system arm has a rotor system including a mast having at least two rotor blades and an electric rotor motor coupled to the mast for driving the mast whereupon the rotor blades act as a rotating rotor disc. Each rotor system has an individually controllable collective rotor blade pitch. At least one rotor system has a controllable cyclic rotor blade pitch. The flight control system controls the at least three electric rotor motors, the collective rotor blade pitch of each rotor system, the cyclic rotor blade pitch of the at least one rotor system and the forward propulsion unit in response to an input control indicating a desired maneuver to operate the rotorcraft for takeoff, flight and landing.

Abstract: A system for fault detection and control in an electric aircraft including an inertial measurement unit, the inertial measurement unit including at least a sensor configured to detect a torque datum associated with at least a propulsor. The system includes an observer, the observer configured to generate a torque prediction datum associated with the at least a propulsor, compare the torque prediction datum with the torque datum, and generate a residual datum as a function of the comparison. The system includes a mixer, the mixer comprising circuitry configured to generate, as a function of the residual datum, a torque priority command datum and transmit, to the at least a propulsor, the torque priority command datum.

Abstract: A control system for an electric motor powered by a battery can be configured to receive an input instantaneous power or torque command corresponding to a commanded instantaneous power or torque. The control system can be configured to determine if the battery is capable of supplying the commanded instantaneous power or torque based on a state of charge (SOC) of the battery. The control system can be configured such that if the battery is capable of supplying the commanded instantaneous power or torque, the control system outputs the input instantaneous power or torque command, and such that if the battery is not capable of supplying the commanded instantaneous power or torque, the control system outputs an available maximum instantaneous power or torque command corresponding to an available maximum instantaneous power or torque that is less than the commanded instantaneous power or torque.

Abstract: This disclosure describes an aerial vehicle, such as an unmanned aerial vehicle (“UAV”), which includes a plurality of maneuverability propulsion mechanisms that enable the aerial vehicle to move in any of the six degrees of freedom (surge, sway, heave, pitch, yaw, and roll). The aerial vehicle may also include a lifting propulsion mechanism that operates to generate a force sufficient to maintain the aerial vehicle at an altitude.

Abstract: An unmanned aerial vehicle (UAV) has a flight-only mode with a motor only rotating propellers and not rotating on-board wheels to configure the UAV to fly away from a surface of a structure, and a crawling-only mode in which the UAV is configured to crawl on the surface due to the motor only rotating the wheels while not rotating the propellers. In the flight-only mode, a clutch disengages a motor from the wheels so that the motor only engages the propellers to fly to lift from the surface. In the crawling-only mode, the clutch disengages the motor from the propellers so that the motor only engages the wheels to move the UAV on the surface.

Abstract: A vectored thrust control module for an aircraft that includes a servo system that couples to the aircraft structure at an output shaft connection point. A thrust motor assembly is fully supported by the servo system and rotates a bladed component to provide thrust to the aircraft. Further, the thrust motor assembly is rigidly connected with the servo system to rotate together about a longitudinal axis thrust line with respect to the aircraft structure. The bladed component and the thrust motor assembly generate a line of thrust that extends through the connection point of the servo system to the aircraft structure.

Abstract: An unmanned aerial vehicle (UAV) that provides increased operational flight endurance and efficiency. The UAV includes a power generation system, which includes an internal combustion engine and one or more batteries (batteries). The power generation system is configured to generate power for propulsion of the UAV. The internal combustion engine is configured to power a lift propeller, generating vertical lift of the UAV, and the batteries are configured to power a micro-propeller assembly, propelling the UAV in a forward direction or multiple additional directions.

Abstract: An exemplary ducted fan includes a duct having a central longitudinal axis, a rotor hub and stator hub extending along the central longitudinal axis, rotor blades extending from the rotor hub, each of the rotor blades operable to rotate about its own pitch-change axis, the pitch-change axes lying in a rotor plane that is generally perpendicular to the central longitudinal axis, each of the rotor blades having a rotor trailing edge and a rotor chord length, stators extending from the stator hub to an interior surface of the duct, each of the stators having a stator leading edge and a stator thickness, and a first separation between the rotor plane and the stator leading edge of not less than approximately 1.5 times the stator thickness.

Abstract: An electric propulsion system for a vertical take-off and landing (VTOL) aircraft, the electric propulsion system including an electrical motor having a stator and a rotor. The electric propulsion system may include a main shaft possessing at least one shoulder on an outer surface of the main shaft. The electric propulsion system may include a gearbox assembly comprising a sun gear that is concentrically aligned with the main shaft at least one planetary gear that interfaces with the sun gear. The electric propulsion system may include a planetary carrier, wherein a center of the planetary carrier is concentrically aligned with the main shaft. The electric propulsion system may include a propeller flange assembly that travels through the rotor, and an axial buttress positioned in the at least one shoulder located on the main shaft.

Abstract: A battery-powered aerial vehicle has a central controller, one or more propelling modules, and one or more battery assemblies for powering at least the one or more propelling modules. The battery assemblies are at a distance away from the central controller for reducing electromagnetic interference to the central controller. In some embodiments, the aerial vehicle is a fixed-wing unmanned aerial vehicle (UAV) having a central controller, a plurality of rotor units, and one or more battery assemblies. The central controller is in a center unit and the propelling modules are in respective rotor units. Each battery assembly is in a rotor unit in proximity with the propelling module thereof. In some embodiments, the central controller also has a battery-power balancing circuit for balancing the power consumption rates of the one or more battery assemblies.

Abstract: An inner middle rotor is rotated while an inner front rotor, an inner back rotor, and an outer rotor are not rotated. The inner middle rotor is surrounded by the inner front rotor, the inner back rotor, the outer rotor, and a fuselage. After rotating the inner middle rotor while not rotating the inner front rotor, the inner back rotor, and the outer rotor, the inner middle rotor, the inner front rotor, the inner back rotor, and the outer rotor are simultaneously rotated.

Abstract: An amphibious drone having a fuselage, a linear support, a wing and a take-off and landing device. The take-off and landing device is on the lower surface of the linear support or the wing. The take-off and landing device has a buoyancy unit and a power device, and the power device is capable of generating thrust to push the buoyancy unit to move. The take-off and landing device can be on the lower surface of the drone, and realizes the water support of the drone by symmetrically providing the take-off and landing device. At the same time, the take-off and landing device is further provided with a power device for pushing the drone to be started. The amphibious drone can take off and land by relying on the take-off and landing device, which can be disassembled to adapt to different usage conditions.

Abstract: To provide a rotary wing aircraft capable of self-leveling and ensuring a stable landing state. The rotary wing aircraft according to the present disclosure comprises a plurality of rotary blades, an arm part for supporting the plurality of rotary blades, a mounting part for mounting an object, and a connecting part for connecting the mounting part to the arm part in a state where the mounting part is movable within a predetermined range. The position of the connecting part of the rotary wing aircraft of the present disclosure is above the center of gravity of the arm part. Thereby, self-leveling is made possible and a stable landing state can be ensured.

Abstract: Example positioning systems and methods are described. In one implementation, a landing platform includes a base having an aperture and multiple positioning arms attached to the base. Each of the multiple positioning arms can rotate between an unlocked position and a locked position. Additionally, each of the multiple positioning arms are configured to engage a positioning ring on an unmanned aerial vehicle (UAV) and further configured to reposition the UAV on the base.

Abstract: To provide a flying object in which a working part can be close to an operation target at an appropriate distance the flying object according to the present disclosure includes a flight part including at least a plurality of rotary wings and a motor for driving the rotary wings, a main body elongated in a vertical direction, and a connection part that connects the flight part and the main body in a mutually displaceable manner, wherein a total length of the main body in the vertical direction is at least twice a maximum diameter of the flight part in a horizontal direction. The main body has an upper part that is provided above the connection portion, and a lower portion that is provided below the connection portion, and the length of the upper part is three times or more the length of the lower part.

Abstract: An unmanned aerial vehicle (UAV) includes a fuselage assembly, a further portion that attaches with the fuselage assembly, and a propulsion assembly coupled with the further portion. The propulsion assembly is constructed and arranged to provide propulsion for the UAV. The fuselage assembly includes a fuselage body constructed and arranged to operate as a forward portion of the UAV, lateral stringers coupled with the fuselage body and extending laterally along the fuselage body, and a set of interchangeable covers to cover at least a portion of a payload bay opening defined by the fuselage body. Utilizing such a fuselage assembly offers a highly configurable mounting architecture to accommodate a wide variety of payloads.

Abstract: A VTOL aircraft (1), including: a fuselage (2) for transporting passengers and/or load; a front wing (3) attached to the fuselage (2); an aft wing (4) attached to the fuselage (2), behind the front wing (3) in a direction of forward flight (FF); a right connecting beam (5a) and a left connecting beam (5b), which connecting beams (5a, 5b) structurally connect the front wing (3) and the aft wing (4), which connecting beams (5a, 5b) are spaced apart from the fuselage (2); and at least two propulsion units (6) on each one of the connecting beams (5a, 5b). The propulsion units (6) include at least one propeller (6b, 6b?) and at least one motor (6a) driving the propeller (6b, 6b?), preferably an electric motor, and are arranged with their respective propeller axis in an essentially vertical orientation (z).

Abstract: An example of a collapsible pylon for a drone aircraft includes a bore extending through a length of a barrel, a first and a second flex-pin bore formed through a wall of the barrel, a first arm slidably positioned within a first end of the bore, a first flex pin disposed on the first arm to engage the first flex-pin bore, a second arm slidably positioned within a second end of the bore, and a second flex pin disposed on the second arm to engage the second flex-pin bore.

Abstract: A system, method and apparatus for unfolding and folding a multi-arm device that includes a support member and an actuator. A first arm is coupled to the actuator and extends from a folded position to an unfolded position upon actuation of the actuator. A second arm is coupled to the actuator and moves from a folded position to an unfolded position upon actuation of a linkage that causes the second arm to rotate. A third arm moves from a folded position to an unfolded position, via an elbow joint, upon release of a tether attached to the third arm.

Abstract: A method of controlling an overly determined actuator system that has a first number of actuators (?i) which is greater than a second number of the actuators needed to perform a predetermined physical task. The method includes: automatically controlling the first number of actuators by a control unit (CU) for jointly performing the predetermined physical task; repeatedly checking a functional state of the first number of actuators to detect an actuator failure of any one thereof; in case of any detected actuator failure, generating at least one emergency signal (EM) representative of an adapted physical task to be performed by a remaining number of the actuators. The emergency signal is generated based on kinematics of the actuator system, on known physical capacities at least of the remaining actuators, and optionally on a computational performance model of the actuator system.

Abstract: Variations of an aerial vehicle, all with capability of vertical take-off and landing (VTOL), with one variation comprising at least three engines, at least three rotors, a flight control system, battery, and propulsion system. The second VTOL aerial vehicle variation being a hybrid with engine-powered rotors and electric-powered rotors configured to work with a flight control system and battery. The first and second variations having the option of a genset system which recharges the battery. The third VTOL aerial vehicle variation being all-electric-powered rotors configured to work with a flight control system and a genset system which powers the rotors and/or recharges the battery.

Abstract: A method of capturing an aerial vehicle comprises rotating a first blade of the aerial vehicle, the first blade coupled to a hub of the aerial vehicle and having a contour configured to facilitate entanglement of a payload line of a winch system around the aerial vehicle. The method further comprises contacting, by a leading edge of the first blade, the payload line of the winch system and pulling the payload line towards the hub of the aerial vehicle, wherein the payload line is pulled towards the hub as the first blade continues to rotate and wherein continued rotation of the first blade causes the payload line to be tangled around the hub of the aerial vehicle.

Abstract: Vehicles such as unmanned air vehicles that are capable of movement from an open, flight configuration to an enclosed configuration in which all major flight components can be protected by an outer shell are disclosed. In the enclosed configuration, the vehicles can take on standard geometric shapes such as a rectangular prism, sphere, cylinder, or another shape, so as to not be recognizable as an unmanned air vehicle. Embodiments of vehicles can also include interchangeable and/or wireless motor arms, motor arms which are electrically connected to the remainder of the vehicle only when in an open configuration, remote controllers removably attached to the remainder of the vehicle, and clip or other attachment mechanisms for attachment to objects such as backpacks.

Abstract: A system for fault detection and control in an electric aircraft including an inertial measurement unit, the inertial measurement unit including at least a sensor configured to detect a torque datum associated with at least a propulsor. The system includes an observer, the observer configured to generate a torque prediction datum associated with the at least a propulsor, compare the torque prediction datum with the torque datum, and generate a residual datum as a function of the comparison. The system includes a mixer, the mixer comprising circuitry configured to generate, as a function of the residual datum, a torque priority command datum and transmit, to the at least a propulsor, the torque priority command datum.

Abstract: A system comprising a reel, a tether configured to be wound about the reel, and at least one unmanned aerial vehicle attached to the tether. When unmanned aerial vehicle is at rest, the unmanned aerial vehicle resides on the reel. Related methods of operating such a system can be used to extract crop from a field.

Abstract: A compound aircraft embodies an array of rotors for vertical flight positioned on support booms and wing elements for cruise flight coupled to a central fuselage housing avionics and a pusher propeller for forward propulsion. The aircraft accommodates a cargo-carrying container with mating of the surfaces between container and fuselage and latching mechanisms for attaching and detaching the container and vehicle.

Abstract: The disclosure provides a method of controlling the yaw of a fixed-wing UAV, with two propulsion propellers arranged parallel to each other and providing thrust for the UAV; A plurality of motors configured to drive the two propulsion propellers, wherein the thrust ratio provided by the two propulsion propellers is changed to generate asymmetric thrust which controls the active yaw of the UAV. The fixed-wing UAV provided by the disclosure improves the reliability of the thrust system and active yaw.

Abstract: A foldable aerial vehicle may take the form of a flying wing. The flying wing includes port and starboard wings having port and starboard root and tip portions. The port and starboard root and tip portions are hinged one to another so that the span axes of all of the root and tip portions are parallel in the stowed condition and so that the tip portions are separated by the root portions in the deployed condition to define the flying wing. The wings are not symmetrical about the longitudinal axis of the vehicle, with the span axes of the root and tip portions being stepped from one wing tip to the other. Folding winglets are disposed on opposing wing tips, with the higher winglet extending in an upward direction and the lower winglet extending in the downward direction.

Abstract: Embodiments herein describe UAVs that utilize tail boom assemblies from pre-existing aircraft designs as lift generating elements. In one embodiment, a UAV includes a fuselage having a first end and a second end opposite the first end, a first tail boom coupler disposed at the first end, and a second tail boom coupler disposed at the second end. Each of the first tail boom coupler and the second tail boom coupler are configured to mechanically couple with a plurality of tail boom assemblies procured from a pre-existing aircraft design.

Abstract: A supporting wing structure for an aircraft, in particular for a load-carrying and/or passenger-carrying aircraft, preferably an aircraft in the form of a vertical take-off and landing multicopter having a plurality of electrically driven rotors which are disposed in a distributed manner. The supporting wing structure has a plurality of struts. A first number of the struts are at least largely disposed in a first direction, while a second number of the struts are at least largely disposed in a second direction, the second direction being oriented orthogonal to the first direction. At least the struts of the second number have an aerodynamic profile in cross section, and/or in the struts are connected to one another at least in pairs between neighboring struts by a connecting structure, preferably from individual connecting segments, and the connecting structure or the connecting segments have an aerodynamic profiling. Furthermore an aircraft is provided equipped with such a supporting wing structure.

Abstract: An aircraft having a high efficiency forward flight mode. The aircraft includes an airframe having at least one wing. A distributed propulsion system is attached to the airframe and includes a first plurality of propulsion assemblies and a second plurality of propulsion assemblies. A flight control system is operably associated with the distributed propulsion system and is operable to independently control each of the propulsion assemblies. The aircraft is configured for thrust-borne lift in a vertical takeoff and landing flight mode and wing-borne lift in the forward flight mode. In the vertical takeoff and landing flight mode, each of the propulsion assemblies is configured to generate vertical thrust. In the forward flight mode, the propulsion assemblies of the first plurality of propulsion assemblies are configured to generate forward thrust and the propulsion assemblies of the second plurality of propulsion assemblies are configured to shut down.

Abstract: A foldable blade assembly may include a first blade, a motor configured to rotate the first blade, a second blade of which a rotation center coincides with a rotation center of the first blade, and an actuator configured to move the second blade upward or downward to selectively couple the second blade to the first blade so that the second blade and the first blade are rotated together or configured to release the coupling between the second blade and the first blade.

Abstract: An unmanned aerial vehicle capable of VTOL operation can include: a vehicle body defining longitudinal and transverse directions and opposing longitudinal sides; a first support boom coupled to the vehicle body at a first transverse axis and extending outwardly from the opposing longitudinal sides; a second support boom coupled to the vehicle body at a second transverse axis positioned rearward from the first transverse axis and extending outwardly from the opposing longitudinal sides; a plurality of electric motors coupled to a one of the first and second support booms, at least two electric motors of the plurality of electric motors positioned on each of the first and second support booms, a rotation axis of each of the at least two electric motors coupled to the second support boom offset in a transverse direction from a rotation axis of each of the at least two adjacent electric motors coupled to the first support boom; a plurality of rotors; and a propulsion system.

Abstract: The application discloses a coaxial helicopter, the cyclic pitch-changing mechanism simultaneously adjusts the pitches of the upper and the lower rotor systems, to make uniformity cyclic pitch-changing adjustment of the upper and lower rotors, and make independent collective pitch adjustment of the upper rotor system; the differential pitch-changing mechanism and the cyclic pitch-changing mechanism jointly act on the lower rotor system, to perform differential collective pitch adjustment of the upper and lower rotor systems. The synchronous rotating mechanism drives the swashplate members to synchronously rotate along with the drive shaft.

Abstract: An unmanned aircraft capable of vertical takeoff, vertical landing, and/or flight in a hovering orientation is presented; its fixed-wing is positively-swept and of low aspect-ratio with suitable airfoils. The unmanned aircraft includes a thruster comprising two contra-rotating motors and propellers forward of the fixed-wing's leading-edge and a rudderless fin aft of the center-of-mass, all of which lie on the aircraft's plane-of-symmetry. Two elevons provide pitch and roll control. The unmanned aircraft can stand upright on its feet. A control system for aircraft with at least one wing is also presented. The control system includes a mount and attached thruster which lie on the plane-of-symmetry forward of the fixed-wing's leading-edge. A hinge axis approximately perpendicular to the aircraft's horizontal plane passes through the mount. The thruster rotates about the hinge axis for aircraft yaw control.

Abstract: The disclosure provides a method of controlling the yaw of a fixed-wing UAV, with two traction propellers arranged parallel to each other and providing thrust for the UAV; A plurality of motors configured to drive the two traction propellers, wherein the thrust ratio provided by the two traction propellers is changed to generate asymmetric thrust which controls the active yaw of the UAV. The fixed-wing UAV provided by the disclosure improves the reliability of the thrust system and active yaw.

Abstract: An unmanned aerial vehicle having a dynamic balance system that comprises a moveable battery support to secure a vehicle battery to the vehicle, the moveable battery support being attached to an actuator that will shift the moveable battery support relative to the vehicle body under the control of an electronic controller during vehicle operations to help maintain the balance and orientation of the vehicle.

Abstract: One embodiment is an electric drive system including a plurality of redundant motors, wherein power generated by the plurality of motors is used to drive a rotor system comprising a rotor shaft having a plurality of rotor blades connected thereto via a swashplate; a gear box associated with the plurality of redundant motors; a cyclic actuation system for controlling an individual pitch of the rotor blades connected to the swashplate; and at least one structural element for retaining the redundant motors, the gear box, and the cyclic actuation system together as a single integrated unit.

Abstract: According to an aspect, a pivoting sail fairing system includes a rotatable fairing, for rotation about a first axis of rotation of an aircraft, that includes a housing that defines a compartment arranged inward from the housing, the housing including a first orifice on a first surface and a second orifice on a second surface of the housing, and a first actuator mounted on a surface of the compartment inward from the housing.

Abstract: [Problem] To provide a flying body having a new structure capable of improving flight efficiency. [Solution] The problem is addressed by a flying body capable of traveling along at least a first direction and comprising an airframe part and an auxiliary part wherein the airframe part has a body part and a lift generating part, the body part having a right part and a left part extending along the first direction and a connecting part whereby the ends of the right part and the left part in a second direction opposing to the first direction are connected. The flying body is thus configured so as to create a surrounded space surrounded by the left part, the right part, and the connecting part when seen from a third direction perpendicular to the first direction.

Abstract: This disclosure describes an aerial vehicle, such as an unmanned aerial vehicle (“UAV”), which includes a plurality of maneuverability propulsion mechanisms that enable the aerial vehicle to move in any of the six degrees of freedom (surge, sway, heave, pitch, yaw, and roll). The aerial vehicle may also include a lifting propulsion mechanism that operates to generate a force sufficient to maintain the aerial vehicle at an altitude.

Abstract: A vertical takeoff and landing aerial vehicle. A left linear support and a right linear support of the unmanned aerial vehicle are respectively provided with a first group of multiple lift propellers and a second group of lift propellers, and the aerial vehicle is provided with a left dorsal fin and a right dorsal fin. By arranging a plurality of lift propellers, a left dorsal fin, and a right dorsal fin on the vertical takeoff and landing aerial vehicle provided by the disclosure, the aerial vehicle is higher in stability in the flight process.

Abstract: An unmanned aerial vehicle comprises a housing, a plurality of first arms, a plurality of second arms, and a landing gear. The housing includes a gimbal attachment to couple a gimbal with a camera. Each of the plurality of first arms and the plurality of second arms rotatably couple with the housing at one end and has a motor coupled with a propeller on the other end. The landing gear includes a plurality of foldable legs and releasably couples with an underside of the housing. The aerial vehicle may be programmed with aerial flight path data that corresponds with a prior traced route.

Abstract: A VTOL aircraft has fixed wings and a rotor blade system for providing lift in active and passive modes thereof. Operation of the rotor blade system may be switched between the active mode in which the rotor blade system is driven by a power system of the aircraft and the passive mode in which the rotor blade system is not driven by the power system, the rotor blade system being configurable to provide lift in the passive mode during forward flight of the aircraft. The rotor blade system provides lift in the passive mode, allowing the fixed wings to be shorter than in the case where the rotor system provides lift during vertical take-off and landing but otherwise has no function, thus providing aircraft which is lighter, more compact and more efficient than similar aircraft of the prior art.

Abstract: A system for landing an unmanned aerial vehicle has an unmanned aerial vehicle and a ground-based platform. A guide structure for receiving the unmanned aerial vehicle is mounted on the ground base platform. The guide structure has an inner diameter greater than a smallest outer diameter of the unmanned aerial vehicle landing gear and less than the largest outer diameter of the unmanned aerial vehicle landing gear.