Abstract: The present disclosure provides a deployment mechanism for arms of a drone. This mechanism is particularly of relevance to a drone that is housed in a container and is configured to be launched therefrom, and therefore is required to have an efficient deployment mechanism for its arms to be deployed immediately after the launch. The deployment mechanism is biased to its deployed state and is retained in its non-deployed state by external forces, such as the normal forces that are applied by the walls of the container on the arms while the drone is housed within the container. After the launch from the container, the above-mentioned forces are no longer applied to the arms of the drone and the deployment mechanism, causing a transition of the arms from their non-deployed state to their deployed state, in which they are in a position suitable for flying, i.e. activation of the rotors mounted on the arms.

Abstract: An electronic device includes a host processor including a data transmitter, a driving driver, and a display panel. The data transmitter includes a phase locked loop that generates a first clock and a second clock, a clock block that receives the first clock, a plurality of data blocks that receives the second clock, a first buffer connected between the phase locked loop and the clock block, and a plurality of second buffers respectively connected between the phase locked loop and the plurality of data blocks, and the first buffer and each of the plurality of second buffers may be activated or deactivated depending on an interface mode.

Abstract: The invention is for a VTOL (vertical take-off and landing) rotorcraft with the annular contra-rotating rotary wings and auxiliary propulsor. The rotary wing of the annular contra-rotating rotary wings is driven by a plurality of tangential forces applied at multiple locations of the inner stator hub. The annular contra-rotating rotary wings can be shrouded for the improvement of propulsive efficiency, reduction of noise and protection of the rotary wing. The fuselage is mounted along the center axis of the annular contra-rotating rotary wings to be outside of the thrust slipstream. The auxiliary propulsor includes a quad independent pusher propeller to propel the rotorcraft to reach faster forward speed.

Abstract: A device for determining a state of a rotor of a rotorcraft. The rotorcraft comprises a fuselage and a main rotor provided with a hub rotating about a mast of the rotor and with a plurality of blades whose second ends describe a trajectory defining a tip path plane. The device includes a sensor for measuring an angular velocity of a blade about a pitch axis. The device thus makes it possible to determine a state of the rotor, comprising, for example, estimates of a longitudinal cyclic pitch and of a lateral cyclic pitch of the blade with respect to the tip path plane.

Abstract: A heavy-lift UAV frame includes a central frame portion and a pocket area for receiving an avionics package. Top and bottom plates are secured to the central frame portion and include four corner members that extend diagonally outward therefrom. A plurality of boom hinges are interposed between each of the corner members pivot a boom arm between an extended position for flight and a retracted position for storage and transport. Each boom arm and hinge combination includes a complementary dimension to one side of the central frame portion to position a boom arm parallel thereto when in the retracted position. A plurality of landing gear hinges are positioned along the bottom of the frame and transition a plurality of landing gear legs between a ready for flight position and a storage position. In the storage position each of the legs are positioned diagonally beneath the central frame portion.

Abstract: An improved propeller system is disclosed, including at least one resilient component configured with a mounting arrangement of a propeller of the propeller system. The resilient component is made of a resilient material that allows the propeller to tilt about a tethering axis under conditions of differential lift force on blades of the propeller under an advancing condition and a retreating condition. The resilient component includes a pair of cutouts for locating inserts made of a rigid material and positioned with a longitudinal axis of the inserts oriented in radial direction. The orientation of the inserts results in a radially oriented line contact between the propeller and the inserts to ensure that tilting of the propeller is about longitudinal axis of the inserts, defining the tethering axis of the propeller system.

Abstract: A tethered drone system has a drone that carries telecommunication equipment, such as one or more cellular transceivers and an antenna, that enables the system to provide access to a telecommunication network for a plurality of remote communication devices in a vicinity of the drone. The drone may be disassembled to facilitate transport to a location at which additional cellular service is desired, such as a remote location or an area impacted by a catastrophic weather or geological event. At or near such location, the drone may be quickly assembled and launched. While airborne, the drone may hover for an extended period of time, such as several, hours, days, weeks, or even longer, while the telecommunication equipment carried by the drone provides access to the telecommunication network.

Abstract: A device for detecting the approach of a vortex ring state for a rotary wing aerodyne, the detection device including a set of vibration sensors configured to be distributed in or on the aerodyne, and a data processing unit configured to receive in real time measurement data from the sensors, process the data in order to calculate in real time the vibration spectrum of the aerodyne, detect in real time, by vibration analysis, the approach of a vortex ring state as a function of the calculated vibration spectrum, and issue an alarm in the event of detection of the approach of a vortex ring state.

Abstract: One example of a mount for a rotorcraft comprises a structural support member, a bracket, and an elastomer. The bracket is configured to attach to a component of the rotorcraft. The component of the rotorcraft produces vibrations at a first frequency. The structural support member configured to transfer a weight of the component of a rotorcraft to an airframe of the rotorcraft. A rotor system of the aircraft vibrates the airframe of the rotorcraft at a second frequency. The elastomer is located between a structural support member and a bracket. The elastomer is configured to attenuate noise caused by the vibrations at the first frequency by isolating the vibrations at the first frequency from reaching the airframe of the rotorcraft while the airframe vibrates at the second frequency.

Abstract: A modular quadcopter is provided for vertical flight. The quadcopter includes a housing, a quadrilateral set of extensions, and a quadrilateral set of arms. The housing contains flight control and sensor equipment, and has a relative vertical orientation. The housing is configurable for either stowage or deployment. The extensions are disposed on each corner of the housing. Each extension has a hinge that pitches outward and upward. Each arm is disposed on the hinge and contains an electric motor and a speed controller. The configurable below the housing for the stowage and extends radially from respective the extension in relation to the orientation for the deployment.

Abstract: In an embodiment, a rotorcraft includes an airframe; a main rotor transmission; one or more brackets mounting the main rotor transmission to the airframe, longitudinal axes of the one or more brackets being substantially parallel with a longitudinal axis of the rotorcraft; and one or more restraints mounting the main rotor transmission to the airframe, the one or more restraints being mounted at an angle non-orthogonal to the longitudinal axis of the rotorcraft and a lateral axis of the rotorcraft.

Abstract: A rotor-regulation system includes a rotor comprising a plurality of blades, a mechanically driven hydraulic pump, a rotor drive shaft operable to drive the rotor and the mechanically driven hydraulic pump, and a throttling valve coupled to the mechanically driven hydraulic pump and operable to modulate rotation of the rotor.

Abstract: An adjustable control link for transferring rotor shaft rotation to a rotating swashplate, the adjustable control link includes an elongate element rotatable with the rotor shaft, the elongate element having a first end. A structure has an opening and a second end. At least one cam component is disposed within the opening and is rotatable relative to the structure about a central axis of the opening. A pin is configured to couple the elongate element to the at least one cam component. The pin is eccentrically rotatable about the central axis to move the first end of the elongate element relative to the second end of the structure.

Abstract: A kit for a helicopter is described, the helicopter comprising a fuselage and a rotor; the kit comprises at least one device adapted to dampen the vibrations transmitted from the rotor to the fuselage and to be interposed between the fuselage and the rotor; the device, in turn, comprises a first threaded element operatively connectable to the rotor and adapted to, in use, vibrate parallel to a first axis; a second threaded element operatively connectable to the fuselage and operatively connected to the first threaded element so as to, in use, rotationally vibrate about the first axis; and a plurality of threaded rollers, which are screwed on the first and second threaded elements; the rollers being rotatable about their respective second axes parallel to and separate from the first axis with respect to the first and second threaded elements; the rollers are also rotatable about the first axis with respect to the first threaded element and the second threaded element.

Abstract: A heavy-lift UAV frame includes a central frame portion having a symmetrical shape and forming a pocket area for receiving an avionics package. Top and bottom plates are secured to the central frame portion and include four corner members that extend diagonally outward therefrom. A plurality of boom hinges are interposed between each of the corner members and an elongated boom arm. Each of the boom hinges pivot the boom arms between an extended position for flight and a retracted position for storage and transport. Each boom arm and hinge combination includes a complementary dimension to one side of the central frame portion to position a boom arm parallel thereto when in the retracted position.

Abstract: Provided is a high efficiency long range drone, and more particularly, a high efficiency long range drone capable of increasing flight time and efficiently using power during long range cruising flight by selectively using the power among an engine generator and a battery and applying an auxiliary wing.

Abstract: An advancing blade concept rotorcraft includes an airframe and a pylon assembly subject to vibration. The pylon assembly includes a dual rotor system having coaxially disposed top and bottom rotor assemblies that counter rotate relative to one another. The advancing blade concept rotorcraft includes a vibration isolation system including at least one pylon link coupled to the airframe and the pylon assembly. The pylon link includes a Liquid Inertia Vibration Eliminator unit operable to reduce transmission of the pylon assembly vibration to the airframe. The advancing blade concept rotorcraft includes active force generators adjacent to the pylon assembly. The active force generators include a first active force generator producing a force in a first direction and a second active force generator producing a force in a second direction to counteract multidirectional oscillations of the pylon assembly, thereby reducing vibration of the advancing blade concept rotorcraft.

Abstract: A mount system for tiltably supporting a pylon assembly of a rotorcraft. First, second, third and fourth pylon links are each coupled between the pylon assembly and the airframe of the rotorcraft. The first pylon link has a first axis, the second pylon link has a second axis, the third pylon link has a third axis and the fourth pylon link has a fourth axis. Each of the axes intersects at a focal point located proximate a coaxial rotor system having counter-rotating upper and lower rotor assemblies such that the focal point provides a virtual pivot point about which the pylon assembly tilts to generate a control moment about a center of gravity of the rotorcraft that counteracts lateral and fore/aft moments generated by the upper and lower rotor assemblies during rotorcraft maneuvers.

Abstract: One example of a mount for a rotorcraft comprises a structural support member, a bracket, and an elastomer. The bracket is configured to attach to a component of the rotorcraft. The component of the rotorcraft produces vibrations at a first frequency. The structural support member configured to transfer a weight of the component of a rotorcraft to an airframe of the rotorcraft. A rotor system of the aircraft vibrates the airframe of the rotorcraft at a second frequency. The elastomer is located between a structural support member and a bracket. The elastomer is configured to attenuate noise caused by the vibrations at the first frequency by isolating the vibrations at the first frequency from reaching the airframe of the rotorcraft while the airframe vibrates at the second frequency.

Abstract: In some examples, an aircraft comprises an airframe, a rotor system coupled to the airframe, and a vibration attenuation system. The rotor system is operable to exert a vibratory force on the airframe. The vibration attenuation system comprises two or more batteries and elastic devices. The two or more batteries are operable to supply power to the rotor system. The elastic devices coupled to the two or more batteries and the airframe. The elastic devices are configured to attenuate the vibratory force based on facilitating oscillation of the two or more batteries. In other examples, a method comprises coupling elastic devices to two or more batteries and an airframe of an aircraft. The elastic devices receiving a vibratory force via the airframe and attenuate the vibratory force based on facilitating oscillation of the two or more batteries.

Abstract: A vibration attenuation system for attenuating vibrations in a mast of an aircraft includes a weight attached to the mast but free to orbit about the mast. The weight can be comprised of one or more weight assemblies. Embodiments can include a single weight, or plural weight assemblies wherein each weight assembly can include a mechanical interconnecting mechanism so that each weight assembly receives feedback regarding the position and movement of one or more other weight assemblies. Each weight can be associated with a spring that urges the weight towards a neutral position. Rotation of the mast can cause the weight to orbit about the mast and self-excite such that the weight acts against the urging of the spring towards an attenuating position.

Abstract: An active vibration control system for an aircraft includes a gearbox operably coupling a power source and a component rotatable about an axis. The gearbox includes a flexible region which allows flexure between a first stage and a second stage. At least one active vibration control actuator is arranged in vibrational communication with the flexible region to counteract vibrations transmitted between the power source and the rotatable component.

Abstract: A transmission tilt control device includes a transmission rotatably coupled to an airframe of a helicopter, a rotor mast coupled to the transmission, and an actuator coupled between the transmission and the airframe. The actuator being configured to rotate the transmission fore and aft about a tilt axis that is perpendicular to an axis of rotation of the rotor mast.

Abstract: A multirotor aircraft with an airframe and a thrust producing units arrangement, wherein the thrust producing units arrangement comprises a predetermined number of thrust producing units for producing thrust in a predetermined direction, and wherein a flexible suspension unit is rigidly mounted to the airframe, wherein the flexible suspension unit comprises at least one bearing that mechanically couples the thrust producing units arrangement to the airframe such that the thrust producing units of the predetermined number of thrust producing units are inclinable in relation to the airframe.

Abstract: An unmanned aircraft system (UAS) configured for both vertical take-off and landing (VTOL) and fixed-wing flight operations includes forward and aft wing assemblies mounted to the fuselage, each wing assembly including port and starboard nacelles terminating in motor-driven rotors powered by an onboard control system capable of adjusting rotor speeds. The UAS may transition between a powered-lift VTOL configuration to a winged-flight configuration by shifting its center of gravity forward, pivoting the wing assemblies from a powered-lift position perpendicular to the fuselage to a winged-flight position parallel to the fuselage. The forward rotor blades may be folded back so that the aft rotors may provide primary thrust for winged flight operations. Onboard attitude sensors may detect rotor or control failures, to which the control system responds by triggering a conversion to the winged-flight configuration for recovery operations.

Abstract: A head for a rotor of a rotorcraft, the head comprising a cap extending radially from an axis of rotation in elevation towards a periphery and extending in azimuth over 360 degrees, the cap extending in thickness between an inside face that is to face a hub of the rotor and an outside face overlying the inside face, the periphery being crenellated to define a succession of crenellations and of notches, each notch allowing a blade of the rotor to perform flapping motion.

Abstract: A helicopter is described that comprises: a rotor; a fuselage; a drive transmission unit operatively connected to the rotor; a support body, which supports the transmission unit; and constraining means interposed between the support body and the fuselage; the constraining means in turn comprise a crosspiece connected in a fixed manner with respect to the support body and having a first lying plane; the crosspiece is formed in part by a metallic material and in part by a visco-elastic material.

Abstract: The discovery concerns a rotor hub cover for a helicopter, whereby the rotor hub cover has been constructed as a rotational body with a dome-shaped cover and the rotor hub cover has performance and control electronic components, characterized by the arrangement of the performance electronic components and the control electronic components on a surface of the internal side or the dome-shaped cover.

Abstract: A control system for resonant inertial actuators estimates operating parameters of the resonant inertial actuators based on voltage and current feedback and dynamically limits selected parameters to maintain the safe, efficient, and cost effective operation of the resonant inertial actuators. Resistance within the electrical drives for the resonant inertial actuators is estimated from the voltage and current feedback and in conjunction with the modeling of the resonant inertial actuators other operating parameters are calculated or otherwise estimated. Having regard for the responsiveness of the resonant inertial actuators to changes in command signals, the command signals are adjusted to dynamically limit the estimated parameters.

Abstract: The present application discloses an unmanned aerial vehicle. The unmanned aerial vehicle includes a support having a plurality of receiving slots; a plurality of arms attached to the support; and a plurality of propellers respectively attached to the plurality of arms. Each of the plurality of receiving slots is configured to receive one of the plurality of arms and one of the plurality of propellers attached to the one of the plurality of arms.

Abstract: Systems and methods for cueing a helicopter pilot when a flight parameter (such as rotor-induced vibration level, airspeed, bank angle, icing accumulation, etc.) exceeds operational constraints. This is accomplished by reformulating the on-board cockpit active vibration control system to add a pilot cueing aid. When the measured flight parameter becomes excessive, the active vibration control system is temporarily detuned, which reduces the amount of vibration suppression it provides or turns off vibration suppression, causing an increase in airframe vibration levels to cue the pilot to take action (e.g., to fly within operating limits).

Abstract: The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors.

Abstract: The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors.

Abstract: A method of selectively preventing flapping of a rotor hub includes providing a flapping lock proximate to a rotor hub and shaft assembly and moving the flapping lock from an unlocked position to a locked position, the flapping lock operable in the locked position to prevent at least some flapping movement of the rotor hub relative to the shaft, the flapping lock operable in the unlocked position to allow the at least some flapping movement of the rotor hub relative to the shaft.

Abstract: A suspension device (10) provided with at least one suspension means (20) comprising a flapper (21) performing pendulum motion, the flapper (21) being provided with a mass support (25) supporting at least one flapping mass (30). The mass support (25) is hinged to a carrier structure (2) for isolating and to a holder bar (15) for holding said mechanical assembly. The suspension device (10) includes at least one force generator (70), said suspension device (10) having at least one computer (50) connected to a measurement system (55) measuring the levels of vibration, and to said force generator (70) to regulate said amplitude and said phase actively by controlling the force generator (70) as a function of at least one measurement signal coming from said measurement system (55).

Abstract: A resilient hub assembly comprises a top plate, bottom plate, central hub, and outer spars. The central hub is coupled between the top plate and the bottom plate. The outer spars are coupled between the top plate and the bottom plate, and the outer spars are positioned in a circular arrangement about a common longitudinal axis of the top plate and the bottom plate. The resilient hub assembly is configured to be flexible. The top plate and/or the bottom plate may comprise cutouts, and/or the outer spars may be positioned as to allow a gap between the central hub and the outer spars to promote flexibility.

Abstract: According to one embodiment, a flapping lock for a rotor system includes a downstop, a flapping stop, and an actuator. The downstop is in mechanical communication with a shaft. The flapping stop is in mechanical communication with a rotor hub. The actuator is operable to move the downstop towards the flapping stop.

Abstract: According to one embodiment, a flapping lock for a rotor system includes a downstop, a flapping stop, and an actuator. The downstop is in mechanical communication with a shaft. The flapping stop is in mechanical communication with a rotor hub. The actuator is operable to move the downstop towards the flapping stop.

Abstract: An unmanned, towable aerovehicle is described and includes a container to hold cargo, an autogyro assembly connected to the container and to provide flight characteristics, and a controller to control operation the autogyro assembly for unmanned flight. The container includes a connection to connect to a powered aircraft to provide forward motive force to power the autogyro assembly. In an example, the autogyro assembly includes a mast extending from the container, a rotatable hub on an end of the mast, and a plurality of blades connected to the hub for rotation to provide lift to the vehicle. In an example, an electrical motor rotates the blades prior to lift off to assist in take off. The electrical motor does not have enough power to sustain flight of the vehicle.

Abstract: According to one embodiment, a bearing is situated between a pitch link and a swashplate or a hub. The bearing comprises an outer housing having a first opening therethrough, an elastomeric bearing adjacent the housing inside the first opening and having a second opening therethrough, and an inner housing adjacent the elastomeric bearing inside the second opening and having a third opening therethrough. The inner housing comprising a first inner surface and a second inner surface defining the third opening. A first member is adjacent the first inner surface inside the third opening having a fourth opening therethrough. A second member is adjacent the second inner surface inside the third opening having a fifth opening therethrough coaxial with the fourth opening.

Abstract: Systems, devices, and methods for a transformable aerial vehicle are provided. In one aspect, a transformable aerial vehicle includes: a central body and at least two transformable frames assemblies respectively disposed on the central body, each of the at least two transformable frame assemblies having a proximal portion pivotally coupled to the central body and a distal portion; an actuation assembly mounted on the central body and configured to pivot the at least two frame assemblies to a plurality of different vertical angles relative to the central body; and a plurality of propulsion units mounted on the at least two transformable frame assemblies and operable to move the transformable aerial vehicle.

Abstract: An antivibration suspension device (10) comprising at least one tie bar (15) hinged via a bottom end (17) to suspension means (20), the suspension means (20) having a lever (25) extending from a distal end (26) supporting at least one flyweight (30) to a proximal end (27) having a first hinge (35) to a carrier structure (2), a tie bar (15) being hinged via a second hinge (40) to the lever (25). The device includes torsion return means (45) having a rotary actuator (46) with an outlet shaft (47) secured to said lever (25) to generate torque on said lever (25), said device having a computer (50) controlling said actuator (46) to adapt torsion stiffness of the lever (25) to flight conditions.

Abstract: A mechanical linkage includes first and second end members and a pair of generally parallel arcuate beams, interconnecting the end members and defining a lateral space therebetween. A plurality of alternating fingers extend from each beam into the lateral space, and a damping member is attached between each adjacent pair of fingers within the lateral space.

Abstract: A carrier structure for a rotor and a method of preventing the coupling of the vibration modes of a carrier structure of a flying machine with the vibration modes of a rotor are provided. The carrier structure has an airframe and a mounting structure suitable for being engaged with the rotor. A vibration-damper mechanism is fitted to the mounting structure and has a resonator that includes a weight element, a damper, and a first deformable member. The weight element is a flapping weight element and is carried by the mounting structure via the first deformable member. The first deformable member allows the weight element to move with respect to the mounting structure and restrains the mobility of the weight element. The damper is interposed between the weight element and the mounting structure for damping the movement of the weight element.

Abstract: A system and method to isolate vibrations from a vibrating structure. The system includes an adjustable vibration isolator that creates a reacting force matching the vibratory force of the vibrating structure. The method includes continuously monitoring the reacting force and vibratory force with a sensor system operably associated with a control unit having an algorithm to determine if adjustment of the vibration isolator is required. If required, the control unit commands a driver to selectively adjust the vibration isolator.

Abstract: A vibration isolator includes an upper housing and a lower housing; an upper reservoir housing defining a upper fluid chamber; a lower reservoir housing defining a lower fluid chamber; a piston spindle resiliently coupled to the upper housing with an upper elastomer member, the piston spindle being resiliently coupled to the lower housing with a lower elastomer member; an elongated portion having a tuning passage; and a tuning fluid disposed there within. The vibration isolator cancels vibratory forces at an isolation frequency. The vibration isolator is utilized in a pylon system for mounting a transmission in an aircraft. The vibration isolator is located between a pylon structure and a roof structure. The isolator includes a spherical bearing assembly that is located near a waterline location of a rotational axis of a drive shaft.

Abstract: The invention is a modular vehicle having an air vehicle that can be coupled to cargo containers, land vehicles, sea vehicles, medical transport modules, etc. In one embodiment the air vehicle has a plurality of propellers positioned around a main airframe, which can provide vertical thrust and/or horizontal thrust. The propellers are mounted on supports which have an airfoil shape to generate additional lift. One or more of the propellers may be configured to tilt forward, backward, and/or side-to-side with respect to the airframe.

Abstract: A magnetic de-rotation system includes an inner ring which supports an eddy current ring and at least one inner ring magnet and an outer ring which supports at least one outer ring magnet, attraction between the at least one inner ring magnet and the at least one outer ring magnet produces a stable rotational position for a fairing.

Abstract: The present invention relates to a method of reducing the vibration of a lift and propulsion rotor (5) of a rotorcraft (1), the rotor having a plurality of airfoil assemblies (10) that perform rotary movement around a drive axis (AX) of the rotor (5), each airfoil assembly (10) comprising a blade (20) extending longitudinally from a root (22) suitable for being fastened to hinge means (4) of a hub (6) of said rotor (5) to a free end (21), a first distance (D1) extending between said free end (21) and said hinge means (4). In the method, said first distance (D1) is caused to vary cyclically so that the projection (TR) of the center of gravity (Cg) of a blade (20) on a horizontal plane (P) perpendicular to said drive axis (AX) and containing said hinge means (4) describes a circle.

Abstract: A method of minimizing the consequences for the occupants of a rotary wing aircraft (1, 10) of an off-specification landing with forward and/or downward acceleration vectors. The aircraft (1, 10) extends along an anteroposterior longitudinal plane of symmetry (4) in elevation separating a first side (5) of said aircraft (1) from a second side (6) thereof. Said rotary wing (10) comprises at least one rotor (11) driven in rotation by a main gearbox (20) and being provided with a plurality of blades (12). Said main gearbox (20) being fastened to a structure (30) of said aircraft (1) by a plurality of fastener elements (40) comprising at least one first fastener element (51, 52) disposed on said first side (5) and at least one second fastener element (61, 62) disposed on said second side (6).