Abstract: An atmospheric parameter measuring device includes a cone top, a balance rod an upper propeller, a lower propeller, a transmission module, an accelerating module, a DC generator, an object-carrying shell, an inertial generation module, a wireless energy-carrying communication module, a sensor carrier, a base, an airbag and a low-power-consumption sensor. Electric energy can generate by using four methods of wind energy, microwave, inertia and solar energy, so the energy supply for the carried low-power-consumption sensor can be ensured and the measuring device can generate electric energy at day and night to ensure the working state of the carried low-power-consumption sensor and measure the atmospheric temperature, humidity, wind speed, intensity of pressure and cloud and water grain shape parameters at the current position conveniently; the measuring device can float in the air by the lift force provided by the rotation of the two propellers.

Abstract: A parallel manipulator with six degrees of freedom may include a base that attaches to a unmanned aerial vehicle and a movable gripper element that may be positioned below the UAV. The positioning of the gripper element my reduce impact of the center of gravity of the attached UAV. The gripper element may include a geometric shape that complements objects routinely used in high-throughput screening (HTS) laboratories, such as microplates. The parallel manipulator and gripper element may be used to quickly, safely, and securely move objects in HTS laboratories and/or the like.

Abstract: An electronic device is provided, including a device shell and a flight photographing device. The device shell is provided with an opening and an inner cavity. The opening communicates with the inner cavity. The flight photographing device is movably arranged on the device shell. The flight photographing device is capable of extending out of the device shell through the opening or retracting into the device shell. In a case that the flight photographing device is located outside the device shell, the flight photographing device is separable from the device shell.

Abstract: A flight-capable imaging system includes a set of parallel rails, a power source mounted to the set of parallel rails, an imaging device mounted to the set of parallel rails, an aerial vehicle body mounted to the set of parallel rails, a set of aerial vehicle arms attached to the aerial vehicle body that each include a set of propellers and a motor configured to turn the set of propellers to enable flight of the flight-capable imaging system, and at least one processing module configured to control the flight of the of the flight-capable imaging system based on controlling a motor speed of the motor of each of the set of aerial vehicle arms.

Abstract: A device launcher can be carried and be used to launch a device by an airborne UAV against an airborne or ground target. The target can be a moving target with the device configured to slow or disable the movement of the target. The device can be triggered manually or through an automated targeting system. The launch apparatus can be configured to launch a single device or a plurality of devices. The device launched against the target can be separated from the launch vehicle or tethered to the launch vehicle. The device can be a net that entangles the rotors of a rotor-driven vehicle. The device can include a parachute to retard movement of target vehicle whether it is falling or if it continues to move. A method of patrolling a perimeter with an airborne vehicle includes the steps of moving the airborne vehicle within the perimeter to sense unauthorized targets and launching a device against those sensed targets.

Abstract: Walking VTOL vehicles and related systems and methods are disclosed. A representative system can include one or more vertical thrust propulsion systems for providing vertical thrust for the vehicle, one or more horizontal thrust propulsion systems for providing horizontal thrust for the vehicle, and leg elements that are rotatable between a first configuration in which each leg element extends downwardly and a second configuration different from the first configuration. A representative method of operating a vehicle includes using vertical thrust to raise the vehicle upward, rotating a leg element forward, lowering the vehicle, and then rotating the leg element rearward to propel the vehicle forward.

Abstract: A self-charging modular portable survival drone that recharges by natural elements is disclosed. The self-charging modular portable survival drone is capable of conventionally charging other devices, performing remote flight operations, and signaling for help. The natural elements include wind and water. The self-charging modular portable survival drone is configured to rapidly and repeatedly charge mobile battery units stored in ducted fan assemblies. The ducted fan assemblies can be used to charge personal electronic devices and power remote flight operations via modular drone. The self-charging modular portable survival drone can be used to signal for help using onboard high-output LEDs during SOS flight operations. The self-charging modular portable survival drone can further be used, during SOS flight operations, to broadcast current GPS coordinates over local search and rescue bands.

Abstract: By providing propellers for vertical ascent and descent and for horizontal flight, and a blade for horizontal flight, it is possible to obtain an aerial vehicle capable of high speed horizontal flight and capable of flying a long distance.

Abstract: A system with a first turbine rotating in a first direction and a second turbine rotating in a second direction, wherein there is negative clearance associated with blades of the first turbine and the blades of the second turbine.

Abstract: To provide a rotorcraft capable of improving flight efficiency. The rotorcraft according to the present invention is capable of moving forward along at least a first direction and comprises an arm part, a plurality of motors mounted on the arm part, and a rotary blade mounted on each of the motors. The rotorcraft is configured to have one or more motors one or more front motors located at a front side and one or more rear motors located at a rear side, wherein the output characteristics of a motor included in the front motor and the output characteristics of a motor included in the rear motor are different.

Abstract: Disclosed is a nighttime cooperative positioning method based on an unmanned aerial vehicle (UAV) group, falling within the technical field of aircraft navigation and positioning. According to the present disclosure, the cooperative visual positioning and the collision warning for UAVs are realized by means of light colors of the UAVs, respective two-dimensional turntable cameras and a communication topology network, without adding additional equipment and without relying on an external signal source, avoiding external interference. Compared with the positioning method in a conventional manner, in the present disclosure, the system is effectively simplified, and the cooperative positioning among the interiors of a UAV cluster can be realized relatively simply and at a low cost to maintain the formation of the UAV group.

Abstract: An unmanned aerial vehicle cluster system, a method, apparatus, and system of launching, and a readable medium. The unmanned aerial vehicle cluster includes a plurality of unmanned aerial vehicles located in a launch area. The method of launching the unmanned aerial vehicle cluster includes: acquiring (S210) launch positions for the plurality of unmanned aerial vehicles in the launch area; acquiring (S220) an assembly area which corresponds to the launch area and includes a plurality of target positions; determining (S230) a target position for each unmanned aerial vehicle of the plurality of unmanned aerial vehicles according to the launch positions for the plurality of unmanned aerial vehicles and the plurality of target positions; and launching (S240) the plurality of unmanned aerial vehicles according to the launch position for each unmanned aerial vehicle of the plurality of unmanned aerial vehicles and the target position for each unmanned aerial vehicle.

Abstract: A tilt rotor-based linear multi-rotor unmanned aerial vehicle (UAV) structure for crop protection and a control method thereof are provided. The tilt rotor-based linear multi-rotor UAV structure for crop protection includes main lift power structures, tilt power structures, and a main frame structure, where the main frame structure is located in a middle; the main lift power structures are distributed at left and right ends of the main frame structure; and the tilt power structures are symmetrically distributed between the main frame structure and the main lift power structures. A vector power structure is adopted to ensure flexible attitude changes and smoother and more accurate UAV operations, and improve the operation efficiency. Meanwhile, the tilt rotor-based linear multi-rotor UAV structure is adapted to the complex working environment in China's ever-changing terrains.

Abstract: An unmanned aerial vehicle includes a central body, a plurality of arms extendable from the central body, and one or more joints. Each of the plurality of arms is configured to support one or more propulsion units, and is configured to transform between (1) a flight configuration in which the arm is extending away from the central body and (2) a compact configuration in which the arm is folded against the central body. Each joint is configured to couple one arm to the central body. At least one of the one or more joints includes an elastic element configured to cause at least one of the plurality of arms to automatically retract when the at least one of the plurality of arms is reversibly folded to a first predetermined state, and automatically extend when the at least one of the plurality of arms is reversibly extended to a second predetermined state.

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: Various examples of a high-speed omnidirectional fully-actuated underwater propulsion mechanism are described. In one example, a propulsion system includes two decoupled counter-rotating rotors centered on a main axis, with each rotor comprising a plurality of pivotable blades projecting radially from the main axis, a servo-swashplate actuation mechanism comprising a plurality of servos and a linkage assembly connected from the servos to the pivotable blades, a blade-axis re-enforcing flap adapter comprising a plurality of stationary flaps, with the blade-axis re-enforcing flap adapter being positioned in a region between the two decoupled counter-rotating rotors centered on the main axis, and a controller.

Abstract: In one aspect, an unmanned aerial system for crowd control, includes a chassis for attaching components of the unmanned aerial system and one or more rotary wings, each of the one or more rotary wings drivable by a respective motor. A container stores a pressurized source of a crowd control agent and a nozzle is provided for dispersing the crowd control agent into the air. An electronically controlled valve selectively places the nozzle into fluid communication with the container. In a further aspect, a modular unmanned aerial system for crowd control is provided.

Abstract: A linking member between a first and a second structural member of a fuselage of an aircraft allowing improved dissipation of stresses. The linking member has a first part made of a solid structure and at least one second part made of a lattice structure. The first part made of the solid structure is configured to dissipate static stresses and to withstand fatigue up to a predetermined maximum stress and fatigue threshold. This configuration allows improved dissipation of the stresses exerted on the linking member.

Abstract: The invention relates to a method for automatically guiding a drone with a computer, with a view to landing the drone on a docking and recharging platform, the drone comprising a first luminous means that emits a first light signal and a second luminous means that emits a second light signal different from the first light signal, the first luminous means and the second luminous means being fastened at two separate points to the drone, the station receiving images captured by a camera, said method comprising: —analyzing the images captured by the camera so as to locate the first and second luminous means, —determining the position and orientation of the drone depending on the determined position of the first and second luminous means, —generating, with the computer, piloting instructions intended for the drone, said instructions being configured to guide the drone towards the docking and recharging platform, —transmitting said instructions to the drone, —the drone receiving and implementing said instructions.

Abstract: A multirotor aircraft that includes a chassis, three or more vertical rotors, one or more free wings and one or more fixed horizontal rotors. The free wing is attached to the chassis by an axial connection so that the angle of the free wing is changed relative to the chassis according the flow of air over the free wing. The fixed horizontal rotor enables the multirotor aircraft to lower and climb while flying forward at a stable horizontal pitch of the chassis.

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: A rotor assembly includes a propeller, a motor, and a connection assembly. The motor includes a stator and a rotator rotatable with respect to the stator. The connection assembly is configured to connect the propeller to the motor and includes a locking member that is arranged between the propeller and the motor. The locking member is configured to rotate with respect to the rotator and the propeller in a rotation direction identical to a rotation direction of the propeller in operation to lock the propeller to the motor.

Abstract: An aircraft includes wings having integrated ducted fans. The integrated ducted fans each have a duct with a stiffness ring. Each stiffness ring is made up of stiffness boxes and circular-arc-shaped ring segments. The stiffness boxes can include first stiffness boxes and second stiffness boxes, and the first stiffness boxes and second stiffness boxes differ in terms of height.

Abstract: Disclosed are systems, apparatuses, and methods for and related to dynamic control of torque and or lateral thrust applied to a load suspended load on a suspension cable to thereby achieve a target orientation or position or to otherwise move through use of a hyperparameter, wherein the hyperparameter comprises a normalized moment of inertia, wherein the hyperparameter comprises a ratio of a force command to a thruster and an angular acceleration.

Abstract: A tailsitter aircraft for deploying a tow line includes an airframe having wings with pylons extending therebetween and a thrust array attached to the airframe, the thrust array including propulsion assemblies configured to transition the airframe between a forward flight orientation and a VTOL orientation. The tailsitter aircraft includes an attenuation spool coupled to the airframe and an attenuation cable having a first end coupled to the attenuation spool and a second end coupled to the tow line, the attenuation cable partially or fully wound around the attenuation spool. The tailsitter aircraft also includes a spool sensor to detect movement of the attenuation spool and a flight control system implementing a tow line tension monitoring module in communication with the spool sensor to determine a tow line tension parameter and a tow line tension reaction module to initiate an aircraft response based on the tow line tension parameter.

Abstract: Introduced here is an ingestible device comprising a capsule having a central axis therethrough, at least one propulsion component, and at least one motor configured to supply motive power to the propulsion component(s). The propulsion component(s) may be disposed at locations radially offset from the central axis. Upon receiving input indicative of a request to alter a position and/or an orientation of the ingestible device, the motor(s) can supply motive power to some or all of the propulsion component(s) to cause movement of the ingestible device.

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: 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: 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: 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: 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: 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 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: 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 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: 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: 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: 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.