Abstract: An electrically-powered VTOL aircraft has a fuselage with a cabin flexibly connected to a powerplane assembly that includes a plurality of electrically-powered rotors and booms. The powerplane assembly can pitch and roll relative to and independently of the cabin, thereby generating efficient fore, aft and lateral thrust while the cabin attitude remains unchanged. This provides a stable passenger experience and enhanced performance and controllability with reduced cost and complexity. In some embodiments, the fuselage is vertically elongated and the powerplane assembly mounts above the fuselage such that a person may walk beneath the rotors completely erect without the fear of being struck by any of the rotors. Using a vertically elongated cabin in conjunction with a relatively high powerplane provides various performance benefits that improve controllability and maneuverability particularly in congested environments, reduce complexity and costs, and enhance passenger safety and experience.

Abstract: A drone with extendable and rotatable wings and a multiple accessory securing panel is provided. The extendable wings help increase the lift of the drone and reduce the air drag on the drone. The multiple accessory securing panel allows various tools and objects to be temporarily and selectively secured to the drone. The multiple accessories may be secured to the drone by a ground based rotating delivery unit. The drone may have a removable front nose and legs which receive power from a power unit.

Abstract: Described herein are methods and systems for motorized control of a tether, such as for purposes of user interaction and feedback. In particular, a UAV's control system may determine one or more operational parameters of a motor for a winch disposed in the UAV, the winch including the tether and a spool. The control system may then detect in the one or more operational parameters, an operational pattern of the motor that is indicative of an intentional user-interaction with the tether. Based on the detected operational pattern of the motor that is indicative of the intentional user-interaction with the tether, the control system may determine a motor response process. Then, the control system may operate the motor in accordance with the determined motor response process.

Abstract: An electric vehicle charging connector, including a set of pins, a sensor, and a controller. The set of pins may include a DC pin, wherein the DC pin is configured to supply DC power to a charging port, wherein the charging port comprises a locking mechanism. The sensor can detect power flow from the pins to the charging port. The controller is communicatively connected to the sensor and configured to receive a signal from the sensor and send a locking signal to a locking mechanism. The locking mechanism comprises an engaged state wherein the charging connector is mechanically coupled to the charging port and a disengaged state wherein the charging connector is mechanically uncoupled form the charging port, wherein the locking mechanism is configured to receive a locking signal from the controller of the charging connector and enter the engaged state.

Abstract: A helicopter includes annular rotors surrounding a fuselage. Rotor blades extend radially outwardly from each annular rotor. One or more motors is provided. Each motor rotates a roller, which drives each annular rotor by traction. In an embodiment with two rotors, one rotor rotates in one direction and the other rotor rotates in the opposite direction. A swash device with a grooved outer cylindrical surface engages the free end of a crank arm of each rotor blade to provide collective and cyclic pitch control. Actuators, which may be electromechanical or hydraulic, control positioning and movement of the swash device. Batteries, an electric generator and/or a hydrogen fuel cell may supply electric power.

Abstract: An isolation system and method are disclosed. The isolation system includes a beam that includes a first end and a second end. The isolation system may include at least one clamping block comprising first elastomeric material, and the first end may be coupled with the first elastomeric material by the at least one clamping block. An end condition of the buckling beam may be varied based on compression stiffening of the first elastomeric material.

Abstract: An automatic aircraft powerplant control system includes a throttle servo for adjusting a throttle valve via a throttle control linkage. A throttle control lever provides a user input to the throttle servo, and a throttle controller controls the throttle servo for controlling a throttle valve. A propeller servo may be provided for adjusting a propeller governor setting of an engine. A propeller control lever provides a user input to the propeller servo, and a propeller controller controls the propeller servo. A full-authority digital engine control (FADEC) controller is used to automatically control mixing of fuel and air via a fuel-air mixture device. The FADEC controller may be used to automatically provide propeller control.

Abstract: A rotorcraft provided with a yaw motion control system comprising a fairing and a rotor provided with blades, the blades being arranged in the fairing and able to rotate about an axis of rotation of the rotor, the fairing comprising a casing defining an air stream, the air stream extending in a direction of flow of the air within the fairing from an intake section towards an outlet section. The rotorcraft comprises an ice protection system comprising at least one grille arranged upstream of the air stream in the air flow direction, the grille facing the intake section parallel to the axis of rotation and the casing, no grille facing at least one unprotected section of the intake section in a direction parallel to the axis of rotation.

Abstract: A rotor wing aircraft provided with a propulsion apparatus is disclosed. The aircraft has a rotating mast configured to rotate said rotor wing and the apparatus includes a pole mechanically connectable to the rotating mast of the aircraft. At one of the ends of the pole there is placed an electric turbine, powered by a battery, and configured to rotate the pole around an axis of the rotating mast in such a way that the rotation of the pole can be used to rotate the rotor wing. Preferably the pole is made of carbon fiber.

Abstract: A method and apparatus for estimating an airspeed of a rotorcraft by analyzing its rotor. The rotorcraft includes a fuselage and a main rotor that is equipped with a plurality of blades and that rotates about an axis of a hub of the rotor, and in which the free end or “tip” of each blade describes a path in the vicinity of a tip-path plane. The method makes it possible to determine said airspeed of the rotorcraft in a frame of reference united with the tip-path plane by solving a model of the rotor that puts a pitch angle of at least one blade relative to the tip-path plane into relation with the airspeed of the rotorcraft and with an auxiliary speed. The auxiliary speed may be an induced velocity of the air flowing through the rotor or else an axial airspeed at the upstream infinity of the rotorcraft.

Abstract: A vibration damping device equipped with a resonator mechanism comprising at least one resonator, the at least one resonator having a first beater extending from an embedded end to a free beating end. The resonator consists of an elastically deformable base equipped with a first branch and a second branch connected by a central section, the embedded end being embedded at the first branch, the first branch extending from a first end to a second end each rigidly fastened to a mount, the second branch extending from a first end section to a second end section each rigidly fastened to a vibration source.

Abstract: A rotor system for an aircraft is described and includes an open rotor assembly comprising a plurality of rotor blades connected to a rotor mast; and a drive system for providing rotational energy to the open rotor assembly via the rotor mast. The drive system includes at least one electric motor for providing rotational energy to a motor shaft; and a gearbox connected to the drive shaft for receiving rotational energy from the at least one electric motor via the motor shaft and providing rotational energy to the rotor mast via a rotor shaft.

Abstract: A battery-powered pilotless aerial vehicle has a center unit, a plurality of rotor units coupled to the center unit, a plurality of battery assemblies, and a plurality of electrical circuitry components including a central control circuitry and at least a flight control subsystem, a detecting and avoiding subsystem, and an emergency communication subsystem controlled by the central control circuitry. The center unit receives one or more of the electrical circuitry components and has a compartment for accommodating one or more passengers or cargo goods. Each rotor unit comprises a propelling module functionally coupled to the central control circuitry. The one or more battery assemblies are configured for being controlled by the flight control subsystem for at least powering the propelling modules, and are at a distance away from the center unit for reducing electromagnetic interference to the electrical circuitry components therein.

Abstract: A rotor for an aircraft is described that has a mast, an attenuating device to attenuate the transmission of vibrations from the mast in a plane orthogonal to the first axis; and a transmission device interposed between the mast and the attenuating device; the attenuating device comprises a first and a second mass unit with a first and a second mass rotatable about the first axis with a first and a second rotational speed, two control units operable to cause an additional rotation of at least one of the first and second masses; and a first and a second support assembly carrying the first and second masses; each control unit controls the angle between the first and second masses and each control unit comprises: a belt coupled to the support assembly and a drive unit coupled to the first belt, to cause the rotation of the first support assembly with respect to said transmission device.

Abstract: The present invention relates to an aerially distributable communications device (ACCD) including one or more gyrochutes and communications module configured for wireless communication with external communication nodes. The communications module can be configured for mesh network type communication with similar aerially distributable communications device, or as a gateway type communications device to a wide area network such as a satellite network. The ACCD is for deployment in remote areas and/or areas where normal communications networks are down, such as disaster areas. The ACCD can be deployed from an aircraft or a spacecraft. The ACCD can further be configured with emergency equipment such as water purification equipment, power charging equipment, or the like.

Abstract: A low-cost rocket includes an atmospheric flight part and an exo-atmospheric flight part, and uses the atmospheric air part to ascend into the atmosphere through the use of propellers for the atmospheric portion of the flight. The atmospheric flight part separates from the exo-atmospheric flight part in the vicinity of the exo-atmosphere and the exo-atmospheric rocket is launched thereupon. The atmospheric flight part descends through the atmosphere using autorotation of the propellers and, if necessary, a soft landing can be affected by controlling the pitch of the propellers just prior to landing.

Abstract: The present application discloses a three-steering gear direct-drive coaxial rotor system and a control strategy, and belongs to the technical field of helicopter structures. The system includes an upper rotor power module, an upper rotor assembly, an upper tilting mechanism, a driving steering gear group assembly, a lower tilting mechanism, a lower rotor assembly, a lower rotor power module, an upper fixing mast, and a lower fixing mast. According to the present application, three steering gears directly drives an upper-layer swashplate and a lower-layer swashplate, to make cyclic pitch and add-subtract collective pitch on rotors. The synchronous tilting mechanism of the present application provides a flexible design solution for the characteristic of cyclic pitch phase angle offset of the rotors gear.

Abstract: A rotor for an aircraft is described that has a mast, an attenuating device to attenuate the transmission of vibrations from the mast in a plane orthogonal to the first axis, and a transmission device interposed between the mast and the attenuating device; the attenuating device comprises a first and a second mass unit with a first and a second mass rotatable about the first axis with a first and a second rotational speed, two control units operable to cause an additional rotation of at least one of the first and second masses, and a first and a second support assembly carrying the first and second masses; each control unit controls the angle between the first and second masses and comprises a set of drive gear teeth integral with the first support assembly, a cogwheel with a set of control gear teeth meshing with the drive gear teeth, and an actuator to cause the rotation of the cogwheel about a second axis and of the first mass about said first axis.

Abstract: A multi-engine aircraft includes a first engine drivingly engaged to a common rotatable load and a second engine drivingly engaged to the common rotatable load, the second engine having a bleed air system and a control system in communication with a compressed air switching system. The control system controls operation of the second engine and/or the compressed air switching system. The compressed air switching system includes a switching valve that is displaceable between at least a first position and a second position, the first position interconnecting a lower pressure inlet and a switch outlet, and the second position interconnecting a high pressure inlet and the switch outlet. The switch outlet is in communication with the bleed air system of the second engine. The control system actuates the switching valve to switch between the first and second positions.

Abstract: A technique is introduced for touchdown detection during autonomous landing by an aerial vehicle. In some embodiments, the introduced technique includes processing perception inputs with a dynamics model of the aerial vehicle to estimate the external forces and/or torques acting on the aerial vehicle. The estimated external forces and/or torques are continually monitored while the aerial vehicle is landing to determine when the aerial vehicle is sufficiently supported by a landing surface. In some embodiments, semantic information associated with objects in the environment is utilized to configure parameters associated with the touchdown detection process.

Abstract: A propulsion system for providing propulsion of an aircraft includes a plurality of electric motors coupled with a rotor of the aircraft to drive the rotor and a propulsion motor control. The propulsion motor control includes at least one processor electrically connected with at least one electric motor to actuate the at least one electric motor and at least one battery electrically connected with the at least one processor and at least one electric motor to provide power to the at least one processor and the at least one electric motor. The propulsion motor control actuates the plurality of electric motors based on a desired torque level to drive the rotor to provide propulsion of the aircraft.

Abstract: The present invention includes an a plurality of first variable speed motors mounted on a tail boom of the helicopter; one or more fixed pitch blades attached to each of the plurality of first variable speed motors; and wherein a speed of one or more of the plurality of first variable speed motors is varied to provide an anti-torque thrust.

Abstract: An unmanned aerial vehicle (UAV) for transporting items between locations includes a frame and a propulsion system coupled to the frame, the propulsion system including at least one transmission and at least one motor. The UAV also includes a load support area of the frame, the load support area comprising at least one of a different material than the frame or structural supports.

Abstract: A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.

Abstract: An isolation system and method are disclosed. The isolation system includes a beam that includes a first end and a second end. The isolation system may include at least one clamping block comprising first elastomeric material, and the first end may be coupled with the first elastomeric material by the at least one clamping block. An end condition of the buckling beam may be varied based on compression stiffening of the first elastomeric material.

Abstract: A load balancing system for a system of rotating elements such as a helicopter rotor or an airplane propeller. The load balancing system includes two or more balancing tubes rotationally attached to blades or props on the system of rotating elements. The balancing tubes are slightly curved and enclose a hollow space containing a quantity of weighted fluid such as mercury. During operation of the system of rotating elements, the weighted fluid disperses throughout the hollow space in the balancing tubes so as to counter any imbalance in the system of rotating elements. Centrifugal forces will cause different dispersal of the weighted fluid throughout the hollow space depending on the overall pulling or pushing forces resulting from any imbalance.

Abstract: A tilting system for a propeller of an aerial vehicle, may include a propeller provided in front of the opening portion of the housing and configured to be selectively tilted with respect to the housing; a link assembly provided in the internal space of the housing, a first end portion of which is connected to the housing and a second end portion of which is connected to the propeller, and configured to tilt up or tilt down the propeller as the link assembly is extended from the housing or retracted into the housing; and an actuator coupled to the link assembly and configured to provide power for extension or retraction to the link assembly.

Abstract: A aircraft gas turbine engine and operation method, the engine including: a staged combustion system having pilot and main fuel injectors, and operates in a pilot-only range wherein fuel delivers to pilot fuel injectors, and a pilot-and-main operation range wherein fuel is delivered to at least the main fuel injectors. The engine further includes a fuel delivery regulator to pilot and main fuel injectors, which receives fuel from a first and second source containing fuels each with different characteristics. The staged combustion system switches between pilot-only and pilot-and-main range operation when in steady cruise mode, the mode defining a boundary between first and second engine cruise operation range. The fuel delivery regulator delivers fuel to pilot fuel injectors during at least part of the first engine cruise operation with different fuel characteristics from fuel delivered to one or both pilot and main fuel injectors the second engine cruise operation range.

Abstract: An aerial vehicle is programmed or configured to respond to reports of events or conditions within spaces of a facility. The aerial vehicle travels to a location of a reported event or condition and captures data using onboard sensors. The aerial vehicle independently determines whether the reported event or condition is occurring, or is otherwise properly addressed by resources that are available at the location, using images or other data captured by the onboard sensors. Alternatively, the aerial vehicle transmits a request for additional resources to be provided at the location, where necessary. A map of the location generated based on images or other data captured by the onboard sensors may be utilized for any purpose, such as to make one or more recommendations of products that are appropriate for use at the facility.

Abstract: A system for retaining a folded proprotor blade in flight. The system includes a rotary actuator mechanism operable to generate torque via a shaft that rotates about an axis generally parallel to a chordwise direction of the folded proprotor blade, a pair of clamping arms movable in a direction generally parallel to a beamwise direction of the folded proprotor blade, a pair of linkage arms interoperably responsive to the rotary actuator mechanism and coupled between the rotary actuator mechanism and the pair of clamping arms, and a first guide rod extending between the pair of clamping arms in the direction generally parallel to the beamwise direction.

Abstract: An oil cooling system for an aircraft engine, a bypass valve and an associate method of cooling aircraft engine oil are provided. The oil cooling system includes a heat exchanger having an inlet and an outlet. The inlet is in fluid communication with a first oil conduit to receive a first oil flow from the first oil conduit. The heat exchanger facilitates heat transfer from the first oil flow to another fluid. A flow restrictor defining a constriction is operatively disposed to restrict the first oil flow through the heat exchanger. A second oil conduit receives the first oil flow from the heat exchanger. A bypass oil passage provides fluid communication between the first oil conduit and the second oil conduit to allow a second oil flow received from the first oil conduit to flow to the second oil conduit and bypass the heat exchanger.

Abstract: A vibration attenuator for a rotor of an aircraft has a housing adapted for rotation with the rotor about an axis. A first ring is rotatably carried within the housing on a first bearing, a first weight being coupled to the first ring for rotation therewith relative to the housing about the axis. A second ring is rotatably carried by the first ring on a second bearing, a second weight being coupled to the second ring for rotation therewith relative to the housing and to the first ring. A first motor is configured for rotating the first ring relative to the housing, and a second motor is configured for rotating the second ring relative to the housing and to the first ring. The first and second motors are operated to rotate the weights within the housing and position the weights relative to each other for attenuating vibrations.

Abstract: Flight equipment according to an embodiment of the present invention includes: an aerial vehicle having a body and at least one rotor held on the body; a plurality of supporters mounted to the aerial vehicle and supporting a protective member stretched therebetween so as to surround an outside of the body; a support information detection unit configured to detect support information indicating a support state of the protective member; and a mounting state determiner configured to determine whether the support state of the protective member is suitable or unsuitable, based on a value detected by the support information detection unit.

Abstract: An electric aircraft charging connector, including a set of pins, a sensor, a controller, and a locking mechanism. The set of pins may include an AC pin, the AC pin configured to supply AC power to a charging port and/or a DC pin, the DC pin configured to supply DC power to the charging port. The sensor can detect power flow from the pins to the charging port. The controller is communicatively connected to the sensor and configured to receive a signal from the sensor and send a locking signal to a locking mechanism. The locking mechanism is communicatively connected to the controller, having an engaged state wherein the charging connector is mechanically coupled to the charging port and a disengaged state wherein the charging connector is mechanically uncoupled form the charging port, the locking mechanism configured to receive a locking signal from the controller and enter the engaged state.

Abstract: An unmanned rotorcraft includes an airframe, rotor blades that are coupled to the airframe for rotation therewith, a propulsion unit having a propeller, and an actuator that is coupled to the airframe and adapted to temporarily reorient the propulsion unit such that an axis of the propeller moves out of alignment with an axis of the rotor blades. Rotation of the propeller causes counter-rotation of the airframe and rotor blades. The rotor blades and blades of the propeller are adapted to deploy from collapsed positions when flight of the rotorcraft is initiated. A method of operation by the rotorcraft includes, when it is determined that a current heading does not correspond to a determined flight path, causing the actuator to temporarily reorient the propulsion unit in accordance with an angular orientation of the actuator relative to the current heading.

Abstract: An exemplary clamp system for securing a proprotor blade in a stowed position includes a clamp having a pair of opposing pads operable between an open position to receive a portion of a proprotor blade between the pair of opposing pads and a closed position to grip the portion of the proprotor blade with the pair of opposing pads and a rotary actuator in connection with the clamp to operate the clamp between the open and the closed position.

Abstract: An electric vertical take-off and landing (eVTOL) vehicle is positioned to be in a charging position on the ground, wherein the eVTOL vehicle is capable of performing vertical take-offs and landings. The battery is charged while in the charging position on the ground using a wind turbine that includes the rotor.

Abstract: A rotorcraft, and, more particularly, to a rotorcraft with a fuselage having a center line, at least one main rotor that generates vortices during operation, and a stabilizer wing, whereby the stabilizer wing has a planform that reduces the unsteady aerodynamic loads caused by the wake of the at least one main rotor. In particular, the stabilizer wing may be provided with a left wing tip, a right wing tip, a quarter chord line with a non-zero curvature, such that an interaction between the vortices generated by the at least one main rotor and the quarter chord line is spread out over time, a leading edge that is arc-shaped, and a trailing edge that is arc-shaped.

Abstract: A vibration suppression unit for an aircraft comprising a mass having a center of mass, a first rotor, a second rotor, a first coupling between the first rotor and the mass, a second coupling between the second rotor and the mass, the first and second couplings having first and second coupling centers offset perpendicularly from a central axis of rotation by different radial distances and offset in axially from the center of mass with respect to the central axis by different axial distances, the first and second coupling centers having a selectively variable displacement angle defined by the angle between lines extending between the central axis of rotation and the first coupling center and the second coupling center, respectively, wherein the first rotor and the second rotor are controllable to produce a vibration control force vector having a controllable magnitude and frequency about the central axis.

Abstract: A method for constructing at least two fleets of aircraft of different families for which each aircraft has a front part comprising windows, a framing of the windows and a windshield front fairing, comprising, for each aircraft, constructing a module composed of the framing of all of the windows allowing outward visibility from the cockpit and of the windshield front fairing whose form is identical and constant for all the aircraft of the fleets and independent of a form of the fuselages thereof, and constructing a section of fuselage of which at least a part of an edge of the fuselage is of a form identical to an edge of the module, such that the module can be assembled directly with the contiguous fuselage section, whatever the aircraft of the fleets.

Abstract: An illumination pattern changing apparatus is provided. The apparatus includes a stationary plate, a rotary plate disposed spaced apart from the stationary plate, the rotary plate configured to be rotatable, and a light source module including a light source configured to irradiate light, and a plurality of optical fibers configured to emit the light when the light is irradiated, wherein a first end of each optical fiber is connected to the stationary plate and a second end of each optical fiber is connected to the rotary plate to form an illumination pattern, and the illumination pattern is changed when the rotary plate is rotated.

Abstract: A drone includes a drone chassis, a plurality of motors attached to the drone chassis, and a plurality of propellers coupled to the plurality of motors, the plurality of propellers extending above the drone chassis. A net assembly is mounted to the drone chassis. The net assembly extends above the plurality of propellers. The net assembly includes a frame and one or more portions of netting.

Abstract: A passenger drone includes a processing device communicatively coupled to the flight components, cameras, radar, and wireless interfaces; and memory storing instructions that, when executed, cause the processing device to receive notifications from an air traffic control system via the one or more wireless interfaces, the notifications related to previously detected obstructions in a flight path associated with a flight plan of the passenger drone, wherein the previously detected obstructions include objects at or near ground level; monitor proximate airspace with at least one of the one or more cameras and radar; detect an obstruction based on monitoring the proximate airspace, wherein the detected obstruction includes one or more objects at or near ground level in the flight path; alter the flight plan, to be carried out by the flight components, if required, based on the detected obstruction.

Abstract: A rotor for an aircraft is described that comprises: a hub rotatable about an axis and, in turn, comprising a plurality of blades; a mast connectable to a drive member of the aircraft and connected to the hub to drive the hub in rotation about the axis; and damping means to dampen the transmission of vibrations to the mast in a plane orthogonal to the axis; the damping means comprising at least a first mass and a second mass that can eccentrically rotate about the axis with a first and a second speed of rotation, respectively; the first mass and second mass are operatively connected to the mast to generate, respectively, a first and a second damping force on the mast having a main component in a direction radial to the axis; the rotor comprises a transmission unit, which is interposed between the mast and the first and second masses so as to drive the first and second masses in rotation.

Abstract: A propulsion and non-propulsive electrical generation system for an aircraft having at least one turbomachine and at least two pairs of rotors, the rotors of the same pair of rotors being symmetrically opposite on the aircraft with respect to the same center of symmetry, at least four motors each driving a rotor, at least one generator coupled to a turbomachine, an even number of power lines and at most equal to the number of rotors, each power line having at least one propulsion branch coupled to a motor, a battery coupled at the output to the propulsion branch, and an AC-DC converter coupled between an output of a generator and the propulsion branch.

Abstract: In some examples, an aircraft gearbox comprises a housing, a barrier, a rotatable drive system component, a set of gears, and a lubrication system. The barrier separates a first compartment and a second compartment within the housing. Each of the rotatable drive system component and the set of gears operable to rotate based on torque received from an engine. The rotatable drive system component is located in the first compartment. The set of gears is located in the second compartment. The lubrication system comprises a first lubrication subsystem and a second lubrication subsystem, which are, at least in part, independent from one another. The first lubrication subsystem is operable to lubricate the rotatable drive system component in the first compartment. The second lubrication subsystem is operable to lubricate the set of gears in the second compartment. The barrier inhibits lubricant from passing between the first compartment and the second compartment.

Abstract: A helicopter includes annular electric motors surrounding a fuselage. Each annular electric motor includes an annular stator and an annular rotor. Rotor blades extend radially outwardly from each annular rotor. In an embodiment with two electric motors, one rotor rotates in one direction and the other rotor rotates in the opposite direction. A swash device with a grooved outer cylindrical surface engages the free end of a crank arm of each rotor blade to provide collective and cyclic pitch control. Actuators, which may be electromechanical or hydraulic, control positioning and movement of the swash device. Batteries, an electric generator and/or a hydrogen fuel cell may supply electric power.

Abstract: An attitude sensor system with automatic bias correction having a primary attitude sensor wherein the primary attitude sensor comprises at least one accelerometer and an auxiliary sensor system configured to automatically estimate a bias of the accelerometer of the primary attitude sensor such that the resulting error is removed from an output of the attitude sensor system.

Abstract: An information processing method includes the following steps performed using a processor: obtaining first region information indicating a first region; obtaining first position information indicating the position of an unmanned aerial vehicle tethered to a mobile tethering body using a tether; determining, using the first region information and the first position information, a first destination which is a destination of the mobile tethering body; and moving the mobile tethering body to the first destination. The first destination is a position located at least a predetermined distance from a point which is on the boundary of the first region and located the shortest distance from the position of the unmanned aerial vehicle, in the direction from the point on the boundary of the first region to the position of the unmanned aerial vehicle.

Abstract: The present invention includes an a plurality of first variable speed motors mounted on a tail boom of the helicopter; one or more fixed pitch blades attached to each of the plurality of first variable speed motors; and wherein a speed of one or more of the plurality of first variable speed motors is varied to provide an anti-torque thrust.