Entries |
Document | Title | Date |
20080245924 | ROTARYCRAFT POWER AND PROPULSION SYSTEM - A rotary wing vehicle includes a body structure having an elongated tubular backbone or core and a counter-rotating coaxial rotor system having rotors. The rotor system is used to move the rotary wing vehicle in directional flight. | 10-09-2008 |
20090114764 | Automatic conversion system for tiltrotor aircraft - One embodiment of the present invention is a method for automatically controlling the conversion of a tiltrotor aircraft. An airspeed command for the tiltrotor aircraft is received. The airspeed command is converted to a pylon position. A difference between the airspeed command and a measured airspeed is calculated. The difference between the airspeed command and a measured airspeed is converted to a dynamic pylon position. A total pylon position is calculated from the pylon position and the dynamic pylon position. A pylon of the tiltrotor aircraft is moved to the total pylon position. Another embodiment of the present invention is a system for calculating a position of a pylon of a tiltrotor aircraft based on an airspeed command. The system includes an airspeed command module, a pylon trim position module, a dynamic pylon position module, and a pylon position module. | 05-07-2009 |
20090236468 | DUAL FREQUENCY HUB MOUNTED VIBRATION SUPPRESSOR SYSTEM - A vibration suppressor system includes an annular electric motor system which independently controls rotation of at least two masses about the axis of rotation to reduce in-plane vibration of the rotating system. A method of reducing vibrations in a rotary-wing aircraft includes independently controlling a relative angular position of a multiple of independently rotatable masses to reduce vibrations of a main rotor system. | 09-24-2009 |
20090242691 | SWASHPLATE TRAJECTORY CONTROL - A system and method of controlling a rotary-wing aircraft includes transforming a non-rate limited servo position command into a rate limited servo position command. | 10-01-2009 |
20090321555 | HYBRID DEVICE FOR VIBRATION CONTROL - Disclosed herein are control systems relating generally to the field of aerodynamics and more particularly to the control of vibration of rotor blades such as helicopter blades. Such systems involve devices for vibration control of each rotor blade, which incorporate control systems of the flow control type (e.g. actively controlled flap) and structural control type (e.g. active pitch link). Also disclosed are related methods of controlling vibration in a rotor blade, wherein the rotor blade is coupled to a rotor hub and has at least a torsional stiffness and a pitch angle associated therewith. | 12-31-2009 |
20100012768 | ROTARY WING AIRCRAFT ROTATING MACHINERY VIBRATION CONTROL SYSTEM - Helicopters and rotary wing aircraft vibration control system for controlling rotating machinery vibrations are provided for rotating machinery vibrations correlating with operational rotating frequencies. The vibration control system includes a first imbalance rotor with a first mass concentration, the first imbalance rotor driven to rotate with a first controllable phase, a second imbalance rotor with a second mass concentration, the second imbalance rotor driven to rotate with a second controllable phase, a third imbalance rotor with a third mass concentration, the third imbalance rotor driven to rotate with a third controllable phase, a fourth imbalance rotor with a fourth mass concentration, the fourth imbalance rotor driven to rotate with a fourth controllable phase. The vibration control system includes vibration sensors for monitoring the vibration and outputting vibration signals. The vibration control system includes a controller, the controller receiving an operational rotating frequency reference signal, the controller also receiving the vibration sensor signals with the controller controlling the first imbalance rotor first controllable phase, the second imbalance rotor second controllable phase, the third imbalance rotor third controllable phase, and the fourth imbalance rotor fourth controllable phase relative to the rotating frequency reference signal to produce a biaxial force which reduces the vibration signals outputted from the vibration sensors. | 01-21-2010 |
20100025524 | FORCE GRADIENT USING A NON-CONTACT PROXIMITY SENSOR - An improved design for a force gradient using a proximity sensor is disclosed. A force gradient comprises a shaft having a first end and a second end. The switch includes a spring contained between the first end and the second end and a non-contact proximity sensor mounted on the second end. The spring has a first position and is compressed to a second position so that the non-contact proximity sensor signals an AFCS to change state. | 02-04-2010 |
20100090054 | METHOD AND SYSTEM FOR CONTROLLING HELICOPTER VIBRATIONS - A method/system for controlling helicopter vibrations is provided that includes a vibration canceling force generator for actively generating a vibration canceling force. The system includes a resonant actuator having a natural resonant frequency and a resonant actuator electronic control system. The resonant actuator electronic control system provides an electrical drive current to the resonant actuator to drive the resonant actuator about the resonant frequency when commanded by a received command signal. The resonant actuator has a feedback output with the feedback output fed back into the resonant actuator electronic control system wherein the resonant actuator electronic control system adjusts the electrical drive current based on the resonant actuator feedback output to generate the vibration canceling force. | 04-15-2010 |
20100116925 | Stabilization for flight platforms - A flight platform, comprising a rotor rotating about a rotor shaft for providing the platform with an active driving force, and a flight control system that controls the flight based on measured flight parameters that are measured by sensors, wherein at least one of the sensors is located substantially along the axis of rotation of the rotor. | 05-13-2010 |
20100270422 | Rotorcraft with opposing roll mast moments, and related methods - In rotorcraft having rotors on multiple masts, a controller causes opposing roll mast moments to be applied to the different rotors. In preferred embodiments, the opposing roll moment is the result of increasing the lift on the advancing blade and reducing the lift on the retreating blade on the second rotor. This can be accomplished in any suitable manner, such as by applying differential cyclic roll control to the two rotors by tilting the two Swashplates of the two rotors or by using Individual Blade Control (IBC). | 10-28-2010 |
20100308155 | HELICOPTER, ROTOR THEREOF, AND CONTROL METHOD THEREOF - A helicopter rotor include a blade, a rotor hub which supports the blade, and a lead-lag angle mechanism configured to change a lead-lag angle of the blade, in synchronization with a rotation of the rotor hub. The lead-lag angle mechanism changes the lead-lag angle of the blade such that a circumferential speed of a blade tip of the blade ( | 12-09-2010 |
20110031345 | Human interface rotor system helicopter (HIR) - A single place helicopter comprising a lower airframe and an upper airframe, having a rotor shaft attached thereto, rotor blades, and a hub on said rotor shaft with means to change blade pitch for vertical flight. The upper airframe comprising a rotor system, engine, tail boom and tail rotor tilt as one unit with the pilot forward, rearward and in a lateral attitude for directional flight control by means of a hinged gimbal joint or block fastened between the vertical tubes on the lower airframe that connect the upper and lower airframes. By allowing the pilot to move with the rotor system, this configuration combines weight and CG manipulation in a tilt rotor design that eliminates the angular differences between advancing and retreating rotor blades during lateral flight and allows for a simplified human interface flight control system in a single-main-tilt rotor helicopter. | 02-10-2011 |
20110031346 | METHOD OF ASSISTING PILOTING, PILOTING ASSISTANCE MEANS, AND A PILOTING ASSISTANCE DEVICE FOR A ROTORCRAFT USING SAID PILOTING ASSISTANCE MEANS TO IMPLEMENT SAID PILOTING ASSISTANCE METHOD - The present invention relates to a device and method of assisting the piloting of a rotorcraft, the rotorcraft having a flight control ( | 02-10-2011 |
20110049290 | METHOD OF PILOTING A ROTARY-WING DRONE WITH AUTOMATIC STABILIZATION OF HOVERING FLIGHT - This method, applicable in particular to radio-controlled toys comprises the operations consisting in: fitting the drone with a telemeter and a video camera; acquiring the altitude of the drone relative to the ground by means of a telemeter; acquiring the horizontal speed of the drone; and automatically stabilizing the drone in hovering by: servo-controlling the vertical thrust force of the drone so as to stabilize the altitude acquired by the telemeter; and servo-controlling the horizontal thrust force of the drone so as to obtain zero horizontal speed. The video camera is a front-sight camera pointing towards the front of the drone; and the horizontal speed of the drone is acquired from a plurality of video images captured by said front-sight camera. | 03-03-2011 |
20110057071 | LIFE IMPROVING FLIGHT CONTROL SYSTEM - A flight control system includes a command model modified in response to a Life Improving Control (LIC) algorithm. An inverse aircraft model is in communication with the command model to generate a flight control system command to command an aircraft state. A feedback path from the command model and the aircraft state is also modified in response to the Life Improving Control (LIC) algorithm. | 03-10-2011 |
20110079678 | Method of and Device for Actively Damping Vertical Oscillations in a Helicopter Carrying a Suspended External Payload - For damping vertical oscillations in a helicopter having a rotor drive-unit and an airframe and carrying an external payload suspended via a lifting gear from a load attachment point on the airframe, oscillation sensors are arranged on the helicopter, and an actively operated linear actuator is provided between the load attachment point and the lifting gear. With the oscillation sensors excitations of a first mode of the vertical oscillations, in which the external load and the rotor drive-unit oscillate together relative to the load attachment point, and of a second mode of the vertical oscillations, in which the load attachment point oscillates relative to the external load and the rotor drive-unit, are sensed, and forces opposed to the vertical oscillations are applied with the actuator between the load attachment point and the lifting gear as a function of the phase and of the amplitude of the sensed excitations. | 04-07-2011 |
20110121126 | EMERGENCY COLLECTIVE ACTUATOR AND METHOD FOR A HELICOPTER - A helicopter includes a rotor system having a rotor with an adjustable pitch that is controlled at least in part by a pilot using a collective control and which helicopter generates a Low RPM signal that is indicative of a threshold low rotational speed of the rotor. An actuator arrangement configured to move the collective control by exerting a force on the collective control such that the pilot is able to overcome the force but which otherwise moves the collective control from a current operational position toward a minimum pitch position. A control arrangement is configured for receiving the Low RPM signal and for responding to the Low RPM signal by activating the actuator arrangement for at least a predetermined period of time to apply the force to move the collective control from the current operational position to the minimum pitch position. | 05-26-2011 |
20110133022 | HELICOPTER WITH COUNTER-ROTATING COAXIAL ROTORS WITHOUT CYCLIC VARIATION OF PITCH, EQUIPPED WITH MEANS FOR AERODYNAMIC CONTROL OF ATTITUDE AND FLIGHT PATH - An aircraft with preferably coaxial counter-rotating sustaining rotors includes in combination: elements for variation of the collective pitch, i.e., for applying simultaneously one and the same variation to the incidence of all the blades of the rotors; and elements for controlling the attitude and direction of flight, which by generating appropriate aerodynamic forces via the sustaining rotor wind eliminate the need for the presence of elements for variation of the cyclic pitch of the blades of the rotors themselves. | 06-09-2011 |
20110155842 | Velocity Feedback Control System for a Rotor of a Toy Helicopter - There is provided a method and apparatus for controlling a toy helicopter in flight. The toy helicopter is powered by a first rotor and a second rotor. A target speed ratio is determined for the speed of the first rotor and the speed of the second rotor. The speed of the rotors is adjusted incrementally until the target ratio is achieved. | 06-30-2011 |
20110155843 | Velocity Feedback Control System for a Rotor of a Toy Helicopter - There is provided a method and apparatus for controlling a toy helicopter in flight. The toy helicopter is powered by a first rotor and a second rotor. A target speed ratio is determined for the speed of the first rotor and the speed of the second rotor. The speed of the rotors is adjusted incrementally until the target ratio is achieved | 06-30-2011 |
20110155844 | Velocity Feedback Control System for a Rotor of a Toy Helicopter - There is provided a method and apparatus for controlling a toy helicopter in flight. The toy helicopter is powered by a first rotor and a second rotor. A target speed ratio is determined for the speed of the first rotor and the speed of the second rotor. The speed of the rotors is adjusted incrementally until the target ratio is achieved | 06-30-2011 |
20110163199 | A FLYING MACHINE COMPRISING TWIN CONTRA-ROTATING VERTICAL AXIS PROPELLERS - A flying machine comprises a chassis on the underside of which is mounted two vertical axis contra-rotating propellers, which share a common rotational axis. The propellers are driven by two motors through a common drive mechanism, the motors being mounted on the chassis above the propellers and being longitudinally spaced apart along the chassis. Handlebars are movably mounted on the chassis between a seat and a nose piece. A user of the machine thus sits substantially centrally on top of the propellers with their legs straddling the motors and drive mechanism, the riding position thus being closely similar to that of a motorbike. Various collective and cyclic blade pitch control mechanisms are also disclosed. The handlebars and seat in some embodiments are replaced by a load carrying region. | 07-07-2011 |
20110180656 | Method and Apparatus for Aircraft Sensor and Actuator Failure Protection Using Reconfigurable Flight Control Laws - A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix and a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. A sensor management tool is provided for input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators. | 07-28-2011 |
20110192932 | Regulator Device for Helicopters - A regulator device used on helicopters carrying an external load suspended from the helicopter by a supporting cable aids in controlling the flight of the helicopter by measuring the oscillating the movement of the external load, converting the detected variables for the oscillating movement to a geodetic coordinate system, generating a closed loop control signals as a function of the variables, and applying the closed loop control signals to open loop control signals which control the flight of the helicopter. | 08-11-2011 |
20110259994 | HELICOPTER VIBRATION CONTROL SYSTEM AND ROTATING ASSEMBLY ROTARY FORCES GENERATORS FOR CANCELING VIBRATIONS - A rotary blade rotating hub mounted rotating assembly vibration control system ( | 10-27-2011 |
20110303783 | Stabilizer - The invention relates to a stabilizer for rotary wing aircraft | 12-15-2011 |
20110303784 | System and Method for Vibration Control in a Rotorcraft Using an Adaptive Reference Model Algorithm - The adaptive reference model algorithm uses a gain scheduling feature combined with a customized Least-Squares routine as an adaptive method for adjusting feedback control so as to account for variations in Transfer Function (G), thereby optimizing the effectiveness of the Active Vibration Control (AVC) System. The Least-Squares routine identifies the transfer function in a background process without interruption of closed loop vibration control. This identification approach is accomplished without intentional interrogation of the AVC actuators and without intentional vibration level changes. For this adaptive control logic, the dynamic relationship between AVC actuators and AVC sensors is represented by a mathematical model of Transfer Function (G). The mathematical model of Transfer Function (G) is continuously updated by the Least-Squares routine. A feedback gain (H) is computed from the mathematical model of Transfer Function (G), and the feedback gain (H) is updated each time the mathematical model of Transfer Function (G) is updated. | 12-15-2011 |
20120018570 | METHOD OF MINIMIZING THE ATTITUDE HUMP PHENOMENON AND A ROTARY WING AIRCRAFT PROVIDED WITH STABILIZER MEANS THEREFOR - A method of minimizing the attitude hump phenomenon relating to a rotary wing aircraft ( | 01-26-2012 |
20120025012 | ROTARY WING VEHICLE - 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. | 02-02-2012 |
20120043414 | CONTROL OPTIMIZATION METHOD FOR HELICOPTERS CARRYING SUSPENDED LOADS - The control optimization method for helicopters carrying suspended loads during hover flight utilizes a controller based on time-delayed feedback of the load swing angles. The controller outputs include additional displacements, which are added to the helicopter trajectory in the longitudinal and lateral directions. This simple implementation requires only a small modification to the software of the helicopter position controller. Moreover, the implementation of this controller does not need rates of the swing angles. The parameters of the controllers are optimized using the method of particle swarms by minimizing an index that is a function of the history of the load swing. Simulation results show the effectiveness of the controller in suppressing the swing of the slung load while stabilizing the helicopter. | 02-23-2012 |
20120068004 | Auto-hover and auto-pilot helicopter - A helicopter gyroscope mounted on the moving swash plate rather than in or on the body of the helicopter will improve the helicopters hovering capability and auto-pilot performance. | 03-22-2012 |
20120068005 | HELICOPTER ROTOR CONTROL SYSTEM WITH INDIVIDUAL BLADE CONTROL - A method of controlling rotor pitch in a helicopter comprising the steps of: generating at least one blade dynamics signal representing at least one dynamic force acting on at least one of a rotor blade rotating assembly and a helicopter non-rotating assembly, the rotor blade rotating assembly including a plurality of rotor blades and a pitch actuator for each rotor blade; extracting information representing the at least one dynamic force; generating a dynamic force compensation output representing a compensation for at least a portion of the at least one dynamic force; receiving flight control signals directing flight of the helicopter from flight controls of the helicopter; generating from the flight control signals and the dynamic force compensation output a compensated pitch control signal for each blade of the rotor blade rotating assembly, and providing a compensated pitch control signal to compensate for a portion of the at least one dynamic force. | 03-22-2012 |
20120091259 | TOWABLE AIR VEHICLE - An unmanned, towable air vehicle is described and includes electronic sensors to increase the detection range relative to the horizon detection limitations of a surface craft, an autogyro assembly to provide lift, and a controller to control operation the autogyro assembly for unmanned flight. A forward motive force powers the autogyro assembly to provide lift. 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 in an example. | 04-19-2012 |
20120091260 | METHOD OF PILOTING A ROTARY WING DRONE HAVING MULTIPLE ROTORS - This method implements a transition from i) moving state in which the drone is flying at speed and tilt angle that are not zero to ii) hovering state in which the drone has speed and tilt angle that are both zero. The method comprises: a) measuring horizontal linear speed, tilt angles, and angular speeds at the initial instant; b) setting stopping time value; c) on the basis of initial measurements and set stopping time, parameterizing a predetermined predictive function that models optimum continuous decreasing variation of horizontal linear speed as a function of time; d) applying setpoint values to a loop for controlling motors of the drone, which values correspond to target horizontal linear speed precalculated from said parameterized predictive function; and e) once hovering state has been reached, activating a hovering flight control loop for maintaining drone at speed and tilt angle that are zero relative to the ground. | 04-19-2012 |
20120104154 | TAIL FAN APPARATUS AND METHODS FOR LOW SPEED YAW CONTROL OF A ROTORCRAFT - Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use. | 05-03-2012 |
20120104155 | TAIL JET APPARATUS AND METHOD FOR LOW SPEED YAW CONTROL OF A ROTORCRAFT - Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use. | 05-03-2012 |
20120138730 | STABILIZED SAFETY GYROPLANE - The rotary wing aircraft is based on the principle of the gyroplane, and includes a double wing rotating in opposite directions, coupled to a power converter which transfers the power of the gyroplane engine for launching by a mechanical converter which provides the lift energy and which, under command from the airframe, transposes the power to the horizontal thrust propeller. The aircraft is put into natural lift mode by its translational speed, this operating principle allowing take-off at low wind speeds which do not allow auto-rotation to be established. | 06-07-2012 |
20120153072 | METHOD OF CONTROLLING AND REGULATING THE DEFLECTION ANGLE OF A TAILPLANE IN A HYBRID HELICOPTER - A method of controlling and regulating a rotorcraft presenting a speed of advance that is high and stabilized, the rotorcraft including at least a main lift rotor ( | 06-21-2012 |
20120153073 | MISSION-ADAPTIVE ROTOR BLADE - A rotorcraft may include an airframe and a rotor connected to the airframe. The rotor may include a hub and a rotor blade connected to the hub to extend radially away therefrom. The rotor blade may include biasing fibers, oriented to increase the twist of the rotor blade in response to an increase in the speed of rotation of the rotor corresponding to a mission, task, or maneuver. | 06-21-2012 |
20120153074 | ELECTRONIC FLIGHT CONTROL SYSTEM FOR AN AIRCRAFT CAPABLE OF HOVERING - An electronic flight control system for an aircraft capable of hovering and having at least one rotor. The flight control system is configured to operate in a manual flight control mode, in which the flight control system controls rotor speed in response to direct commands from the pilot; and in at least two automatic flight control modes corresponding to respective flight modes of the aircraft, and in which the flight control system controls rotor speed automatically on the basis of flight conditions. The flight control system is also configured to memorize, for each automatic flight control mode, a respective flight table relating different speed values of the rotor to different values of at least one flight quantity; and to automatically control rotor speed in the automatic flight control modes on the basis of the respective flight tables. | 06-21-2012 |
20120160954 | AIRCRAFT PROVIDED WITH A SWIVELING TAIL ROTOR, AND AN ASSOCIATED METHOD - An aircraft ( | 06-28-2012 |
20120181379 | MOMENT LIMITING CONTROL LAWS FOR DUAL RIGID ROTOR HELICOPTERS - A method of counteracting a rotor moment of one or more rotors of a concentric dual-rotor helicopter includes sensing angular velocity and angular acceleration of a helicopter during a flight maneuver. The angular velocity and angular acceleration are compared to a set of control parameters and one or more control servos change the cyclic pitch of the one or more rotors to counteract the rotor moment. A control system for counteracting a rotor moment of one or more rotors of a concentric dual-rotor helicopter includes one or more sensors configured to sense angular velocity and angular acceleration of a helicopter during a flight maneuver. A computer is operably connected to the one or more sensors and configured to compare sensor data to a set of control parameters. A plurality of control servos change the cyclic pitch of the one or more rotors to counteract the rotor moment. | 07-19-2012 |
20120187237 | DIRECTIONAL CONTROL FOR A HELICOPTER - The present document describes a yaw control system for a helicopter having a controllable aft rudder. The system comprises a fan for blowing low pressure air impinging upon the controllable aft rudder. During flight, the main rotor assembly drives the fan and the air flow impinging upon the controllable aft rudder creates a side force which enables yaw control. | 07-26-2012 |
20120234969 | NAVIGATION ELECTRONIC CARD SUPPORT FOR A ROTARY WING DRONE - The support ( | 09-20-2012 |
20120241553 | HELICOPTER WITH TWO OR MORE ROTOR HEADS - A helicopter with two or more rotor heads with full swash plate control and a novel control scheme to allow for propulsion in the horizontal plane in all directions, allowing the aircraft to fly in all directions in a truly horizontal fashion. Furthermore, a manual input device to control the additional control freedoms thus gained, and an electronic control system that combines manual inputs with inputs from sensors and translates these inputs into directions for the actuators of the two or more swash plates in order to control the aircraft, taking into account the novel control scheme. | 09-27-2012 |
20120261508 | ACTIVE GURNEY FLAP - According to an embodiment disclosed herein, a gurney flap assembly includes an actuator, and a flexible body attaching to the actuator, the body having a downwardly depending flap for moving into and out of an airstream in a pressure side of a wing, wherein the flexible body flexes in reaction to motion of the actuator. This increases the lift force of the rotor blade, wing or aerofoil blade. | 10-18-2012 |
20120286088 | EMERGENCY COLLECTIVE ACTUATOR AND METHOD FOR A HELICOPTER - A helicopter includes a rotor system having a rotor with an adjustable pitch that is controlled at least in part by a pilot using a collective control and which helicopter generates a Low RPM signal that is indicative of a threshold low rotational speed of the rotor. An actuator arrangement can move the collective control by exerting a force on the collective control such that the pilot is able to overcome the actuator force but which otherwise can move the collective control from a current operational position toward a minimum pitch position. A clutch can co-rotate with a motor to serve in transferring the actuation force to reduce the adjustable pitch and can slip relative to the actuator shaft assembly responsive to an application of a counterforce applied by the pilot to the collective control such that the counterforce overcomes the actuation force. | 11-15-2012 |
20120298791 | DRIVING CONTROLLER OF REMOTE CONTROL EQUIPMENT - A driving controller of remote control equipment includes a yaw axis angular velocity detecting unit for outputting a yaw axis angular velocity as a yaw axis angular velocity signal; a main rotor RPM detecting unit for outputting a main rotor RPM as a main rotor RPM signal; and a phase control unit for detecting a phase deviation in a roll axis and a pitch axis based on the yaw axis angular velocity signal and the main rotor RPM signal, and generating a roll and a pitch control signal by correcting a roll and a pitch operation signal by the phase deviation. The driving controller further includes an actuator control unit for generating a roll and a pitch actuator driving signal respectively based on the roll and the pitch control signal, and outputting the generated roll and pitch actuator driving signals to a roll and a pitch control actuator, respectively. | 11-29-2012 |
20130015289 | System and Method for Limiting Cyclic Control Inputs - A control system having a first loop configured to provide a longitudinal blowback value of a rotor blade during flight and a second loop associated with the first loop, the second loop being configured to provide a design maximum total flapping value and a lateral flapping value. A method includes calculating a flight control limit from the design maximum total flapping value and the lateral flapping value. An upper longitudinal cyclic control limit is calculated by adding the flight control limit to the longitudinal blowback value. A lower longitudinal cyclic control limit is calculated by subtracting the flight control limit from the longitudinal blowback value. | 01-17-2013 |
20130105620 | SIDED PERFORMANCE COAXIAL VERTICAL TAKEOFF AND LANDING (VTOL) UAV AND PITCH STABILITY TECHNIQUE USING OBLIQUE ACTIVE TILTING (OAT) | 05-02-2013 |
20130134255 | PILOT CYCLIC CONTROL MARGIN DISPLAY - A system to control flight of an aircraft includes a rotor blade, an actuator operably associated with the rotor blade, a controller operably associated with the actuator, and a flight control system. The flight control system having a subsystem adapted to modify a flight control limit of the aircraft based upon detection of an impending hazardous flight condition and a display showing available flight control limits provided by modification of design control limits based upon the detection of the impending hazardous flight condition. The method includes generating the control limits, modifying the control limits based upon the impending hazardous flight condition, and displaying the displacement of actuator position relative to the displayed control limits thus cueing the pilot as to the cyclic stick or pedal inputs required to increase the control margin from the impending hazardous condition | 05-30-2013 |
20130175385 | METHOD OF AUTOMATICALLY CONTROLLING A ROTARY WING AIRCRAFT HAVING AT LEAST ONE PROPULSION PROPELLER, AN AUTOPILOT DEVICE, AND AN AIRCRAFT - An autopilot device ( | 07-11-2013 |
20130181087 | CLUTCH SYSTEM FOR ROTARY-WING AIRCRAFT WITH SECONDARY THRUST SYSTEM - An aircraft includes a powerplant system operable to power a main rotor system and a secondary thrust system, the secondary thrust system is selectively driven through operation of a clutch system, and a clutch system synchronization time corresponds to a response time of the powerplant system. | 07-18-2013 |
20130206899 | Control System For Reconfigurable Rotary Wing Aircraft - A control system for a rotary wing aircraft having a reconfigurable element. The control system includes a model predictive control module receiving operator commands, objectives and constraints; and a dynamic inversion module receiving an output of the model predictive control module, the dynamic inversion module providing control commands to reconfigure the reconfigurable element of the rotary wing aircraft. | 08-15-2013 |
20130214087 | Coaxial Counter-Rotating Rotor System - A system and method to tilt coaxial counter-rotating rotor hub assemblies relative to a fuselage. The system includes a first rotor hub assembly and a second rotor hub assembly spaced apart from the first hub assembly and carried by the fuselage. The method includes pivotally attaching the first rotor hub assembly and the second rotor hub assembly to a pivot joint and thereafter tilting the first rotor hub assembly and the second rotor hub assembly about the pivot joint with a driver. | 08-22-2013 |
20130221153 | SYSTEM AND METHOD FOR AUTOMATION OF ROTORCRAFT ENTRY INTO AUTOROTATION AND MAINTENANCE OF STABILIZED AUTOROTATION - The system is configured for automation of rotorcraft entry into autorotation. The system can provide a means to assist the flight crew of a rotorcraft in maintaining rotor speed following loss of engine power. The system can automatically adjust control positions, actuator positions or both to prevent excessive loss of rotor speed upon initial loss of engine power before the flight crew is able to react. The system uses model matching to provide axis decoupling and yaw anticipation; it includes pitch control initially to assist in preventing rotor deceleration; and it makes use of collective, pitch, roll and yaw trim functions to provide tactile cueing to the pilot to assist when the pilot is in the loop. The system can reduce workload by assisting the crew with controlling rotor speed and forward speed during stabilized autorotation. | 08-29-2013 |
20130233965 | HELICOPTER TORQUE COUNTERACTION DEVICE - The torque resisting system for a helicopter which includes a body. Main rotor and a tail rotor, the system includes a deflector connected to an actuator for moving the deflector relative to the body. The system further includes a sensor that is operationally associated with the tail rotor and the actuator, such that the actuator moves the deflector upon: receiving a signal indicating that the tail rotor is operating below a predetermined rotation or a determination that the sensor is inoperable or absent. | 09-12-2013 |
20130248648 | Portable Control System For Rotary-Wing Aircraft Load Management - A control system for portable control of a rotary-wing aircraft includes a portable, hand-held, control device executing a control application, the control device operating in a loaded mode when a load is attached to the rotary-wing aircraft and an unloaded mode when no load is attached to the rotary-wing aircraft, the control device presenting command icons in response to being in loaded mode and unloaded mode; a vehicle management system in the rotary-wing aircraft; a sensor package on the rotary-wing aircraft; and a communication system providing communications between the control device and the rotary-wing aircraft, vehicle management system and sensor package; wherein the control device communicates commands to the vehicle management system to implement loading and unloading of the rotary-wing aircraft. | 09-26-2013 |
20130264412 | ROTARY WING AIRCRAFT HAVING A TAIL ROTOR, AND A METHOD OF OPTIMIZING THE OPERATION OF A TAIL ROTOR - A rotary wing aircraft ( | 10-10-2013 |
20130306787 | AUTOMATIC ATTITUDE CONTROL OF ROTARY WING AIRCRAFTS - A method and device for precise control of and controller design for aircrafts consisting of at least one spinning part and at least one non spinning part is provided. The required torques for control of the spinning parts and for the non-spinning parts are continuously and individually calculated. All torques are combined to get the correct torque for the complete aircraft. Doing this, it's possible to continuously apply the correct torque, both correctly distributed among the roll and pitch axes (correct angle), and correct magnitude. The result is a decoupling of the roll and pitch axes, simplifying controller design to a design of two single input single output controllers, one for each axe. | 11-21-2013 |
20130313355 | PITCHING STABILIZATION MEANS AND A ROTARY WING AIRCRAFT INCLUDING SUCH MEANS - A pitching stabilization means ( | 11-28-2013 |
20130327879 | HIGH SPEED COMPOUND ROTARY WING AIRCRAFT - A rotary wing aircraft includes an airfame and an extending tail extending from the airframe. A main rotor assembly is operably connected to the airframe and includes a plurality of rotor blades operably connected to a rotor shaft, and one or more active adaptive devices located at one or more rotor blades of the plurality of rotor blades. The one or more active adaptive devices are operably connected to an aircraft flight control system such that, when activated, the one or more active adaptive devices change one or more operational characteristics of the rotor assembly. A tail rotor is operably connected to the extending tail. The tail rotor is rotatable about a tail rotor axis and the tail rotor axis movable from laterally-extending to rearward-extending. | 12-12-2013 |
20130327880 | AUTOMATIC FLIGHT CONTROL METHOD FOR A ROTORCRAFT ENABLING THE ROTOCRAFT TO MAINTAIN A PATH BY TRACKING MANUAL FLIGHT CONTROLS - A method of enabling an autopilot ( | 12-12-2013 |
20130334361 | SYSTEM AND METHOD FOR LIMITING CYCLIC CONTROL INPUTS - A control system having a first loop configured to provide a longitudinal blowback value of a rotor blade during flight and a second loop associated with the first loop, the second loop being configured to provide a design maximum total flapping value and a lateral flapping value. A method includes calculating a flight control limit from the design maximum total flapping value and the lateral flapping value. An upper longitudinal cyclic control limit is calculated by adding the flight control limit to the longitudinal blowback value. A lower longitudinal cyclic control limit is calculated by subtracting the flight control limit from the longitudinal blowback value. | 12-19-2013 |
20140027564 | ROTORCRAFT AUTOPILOT AND METHODS - A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes. | 01-30-2014 |
20140027565 | ROTORCRAFT ADVANCED AUTOPILOT CONTROL ARRANGEMENT AND METHODS - An autopilot system includes an actuator arrangement that receives control signals to influence the flight of the helicopter in a selected one of a plurality of different flight modes. A control stick input arrangement allows flight mode selection and control with no more than a particular one of the pilot's hands in the engaged position on the stick and without moving the hand away from the engaged position. A slaved gyro output signal is based on no more than the set of sensor outputs used by the autopilot such that an autopilot display presents autopilot flight mode information while displaying a slaved gyro output. The autopilot provides for pilot selection of one of a subset of the plurality of flight modes which is customized based on a current flight status of the helicopter. An automatic autorotation mode is provided. | 01-30-2014 |
20140027566 | ROTORCRAFT AUTOPILOT SYSTEM, COMPONENTS AND METHODS - An autopilot actuator includes first and second motors each including a rotatable motor output shaft such that either one or both of the motors can drive an actuator output shaft. An autopilot main unit enclosure is removably mounted to the helicopter proximate to a cyclic control and commonly houses autopilot actuators as well as main autopilot electronics. A cyclic vibration isolator is removably supported by an actuator shaft for co-rotation and coupled to the cyclic control to attenuate a cyclic vibration frequency at the actuator shaft while output rotations of the actuator shaft below a resonant frequency are coupled to the cyclic control. A force limited link includes first and second ends and a variable length between. The force limited link having a relaxed length when less than an unseating force is applied and the variable length changes when an applied force exceeds the unseating force to permit pilot override. | 01-30-2014 |
20140054411 | METHOD OF ASSISTING A PILOT OF A SINGLE-ENGINED ROTARY WING AIRCRAFT DURING A STAGE OF FLIGHT IN AUTOROTATION - A method of assisting a pilot of a single-engined rotary wing aircraft ( | 02-27-2014 |
20140061369 | Rotor Position Determination System with Hall-Effect Sensors - According to one embodiment, a rotor system, includes a position determination system disposed between a blade and at least part of a hub. A grip couples the rotor blade to the hub. The position determination system comprises at least one magnet and a plurality of magnet sensors proximate to the at least one magnet. | 03-06-2014 |
20140070048 | METHOD AND AN AIRCRAFT FOR MINIMIZING THE RISKS OF THE AIRCRAFT TOPPLING ON THE GROUND - A method of assisting a pilot in order to minimize the risks of an aircraft rolling over on the ground, the aircraft having a main rotor and a yaw movement control rotor ( | 03-13-2014 |
20140077025 | Pilot Control System with Adjustable Pedals - According to one embodiment, a method of adjusting an aircraft pedal assembly includes providing a pedal linkage coupled between a pedal and an attachment assembly situated proximate to an aircraft instrument panel. A brake cylinder is provided coupled between the pedal and the attachment assembly. The pedal linkage is rotated in response to an adjustment input. The pedal linkage is maintained approximately parallel to the brake cylinder during rotation of the pedal linkage. | 03-20-2014 |
20140077026 | PITCH STABILIZER AND ROTARY-WING AIRCRAFT EQUIPPED WITH SUCH STABILIZER - A pitch stabilizer [ | 03-20-2014 |
20140097291 | HOVER HOLD AID SYSTEM FOR A HELICOPTER - The general area of the invention is that of hover hold aid systems for helicopters. The system comprises navigation means; a helmet-mounted visualization system containing a helmet-mounted display incorporated in the pilot's helmet and means for generating symbols in said helmet-mounted display at fixed positions in relation to a terrestrial frame of reference, said symbols being displayed in the angular field of display of the helmet-mounted display. When the helicopter has to home or stay in the vicinity of a predetermined position, the symbol generation means calculate a first and a second representation containing a first target and a second target referenced in said terrestrial frame of reference, the first target located in the direction of the homing course to the predetermined position, the second target located in a direction perpendicular to this same course. | 04-10-2014 |
20140117148 | METHOD OF MANAGING AN ENGINE FAILURE ON A MULTI-ENGINED AIRCRAFT HAVING A HYBRID POWER PLANT - A method of managing an engine failure on a rotary wing aircraft ( | 05-01-2014 |
20140138476 | METHOD AND MEANS TO CONTROL THE POSITION AND ATTITUDE OF AN AIRBORNE VEHICLE AT VERY LOW VELOCITY - A vehicle equipped with two or more propulsion units, each, for example, consisting of engine with propeller, with their thrust principally directed vertically along a z-axis, such vehicle characterized by that each propulsion unit can be controlled by rotation around two axes mainly perpendicular to the z-axis and that the propulsion units are positioned some distance apart in the z-direction enabling such control of the attitude of the propulsion units to obtain:
| 05-22-2014 |
20140191079 | Disconnecting a Rotor - According to one embodiment, a clutch may be coupled between a rotor system and a power train of a rotorcraft. The clutch may be operable to disengage the rotor system from the power train during operation of the power train. A clutch control system in communication with the clutch and include a rotorcraft condition sensor operable to sense an operating condition of the rotorcraft and a control unit operable to prevent the clutch from disengaging the rotor system from the power train if the operating condition of the rotorcraft fails to satisfy a predetermined criterion. | 07-10-2014 |
20140246538 | TOWABLE AIR VEHICLE - An unmanned, towable air vehicle is described and includes electronic sensors to increase the detection range relative to the horizon detection limitations of a surface craft, an autogyro assembly to provide lift, and a controller to control operation the autogyro assembly for unmanned flight. A forward motive force powers the autogyro assembly to provide lift. 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 in an example. | 09-04-2014 |
20140252158 | SYSTEM AND METHOD OF ADAPTIVELY GOVERNING ROTOR SPEED FOR OPTIMAL PERFORMANCE - The system for adaptively governing a speed of a rotor assembly in an aircraft can include a processor configured for comparing receivable data to limit data in an algorithm and subsequently making one or more commands that affect the speed of the rotor assembly, the algorithm being configured for analyzing power available during operation of the aircraft. The method can include calculating a first power available by comparing an actual transmission torque to a transmission torque limit; calculating a second power available by comparing an actual engine exhaust temperature to an engine exhaust temperature limit; and comparing the first power available to the second power available. | 09-11-2014 |
20140263820 | Autorotative Enhancement System - Embodiments refer generally to systems and methods for providing autorotative enhancement for helicopters using an autorotative assist unit coupled to the transmission of the helicopter. Methods of utilizing an autorotative assist unit as well as retrofitting an autorotative assist unit to an existing helicopter are also disclosed. By employing an autorotative assist unit, improved autorotation may be achieved without the need to increase the weight of the rotor. | 09-18-2014 |
20140263821 | AUTOMATIC PITCH CHANGE ROTARY WING ROTOR SYSTEM AND METHOD OF ROTOR CONTROL - A helicopter main rotor control system includes a trunnion head mountable to a rotatable helicopter mast wherein the trunnion head has a control bar pivot supported by the trunnion head and pivotal about an axis substantially at a right angle to the helicopter mast. A control bar extends through the control bar pivot at a right angle thereto, and a pair of opposing leaf hinges are pivotal about the control bar and centered about said trunnion head. Each leaf hinge has a hinge plate extending from the control bar and defines a rotor blade mount hole therethrough. | 09-18-2014 |
20140326825 | SYSTEM AND A METHOD FOR CONTROLLING PITCHING STABILIZER MEANS OF AN AIRCRAFT - A control system ( | 11-06-2014 |
20140332621 | VARIABLE LOWER LIMIT COLLECTIVE GOVERNOR TO IMPROVE RECOVERY - A flight control system uses a governor configured to regulate the speed of a rotor in the aircraft through collective pitch control of a rotor blade, and a limiter configured to selectively remove the threshold limit of the governor when the collective pitch control exceeds a threshold limit, so as to permit a pilot full command of the collective above the threshold limit. The threshold limit is selectively removed and phased back in to provide temporary pilot control to “cushion” landing of an aircraft when an engine has failed. | 11-13-2014 |
20140361118 | TORQUE BASED METHOD OF LIMITING VERTICAL AXIS AUGMENTATION - A method of limiting vertical axis augmentation in a rotorcraft, the method comprising: measuring a torque with a sensor; deriving a comparison of the torque to a lower torque limit, using a computer processor; and adjusting a vertical axis control command based upon the comparison of the torque to the lower torque limit. | 12-11-2014 |
20150028152 | HELICOPTER ROTOR LOAD REDUCTION AND TIP CLEARANCE CONTROL - A method of controlling a helicopter having a rotor with blades is provided. The method includes receiving, by a computing device comprising a processor, at least one input associated with the helicopter; generating, by the computing device, control signals configured to counteract blade bending associated with the rotors based on the received at least one input; measuring, by the computing device, blade signals using sensors for the blades; extracting, by the computing device, harmonic loads from the measured blade signals; adapting, by the computing device, the control signals based on the harmonic loads; and controlling, by the computing device, servos connected to the blades to adjust the blades according to the adapted control signals to reduce vibratory loads on the blades. | 01-29-2015 |
20150028153 | REGULATED THREE-ENGINED POWER PLANT FOR A ROTARY WING AIRCRAFT - A power plant ( | 01-29-2015 |
20150053815 | AUTOMATED ROTATING TAIL ROTOR CONTROL - Embodiments are directed to causing, by a computing device comprising a processor, a rotating tail rotor to operate in a tail rotor mode when an aircraft is operating at a speed less than a rudder control power threshold, receiving, by the computing device, a command that indicates a request to transition the aircraft, determining, by the computing device, that a rudder of the aircraft has control power in an amount greater than a second threshold based on receiving the command, and causing, by the computing device, the rotating tail rotor to operate in a pusher propeller mode based on determining that the rudder has control power in the amount greater than the second threshold. | 02-26-2015 |
20150097074 | DUAL-FREQUENCY ACTIVE VIBRATION CONTROL - A system for active vibration control includes an actuator configured to reduce the impact of a vibratory load imposed on an airframe of a rotorcraft to an amount that is less than a threshold; and a controller configured to determine the vibratory load based on the data, and set an eccentric rotational speed of an actuator at a first frequency and modulate the eccentric rotational speed by a second frequency based on the vibratory load. Also a method includes obtaining, by the controller, data; determining, by the controller, a vibratory load based on the data; and setting, by the controller, an eccentric rotational speed of an actuator at a first frequency and modulating the eccentric rotational speed by a second frequency based on the vibratory load. | 04-09-2015 |
20150097075 | YAW CONTROL OF CO-AXIAL ROTOR - A method for controlling rotor blades of a co-axial rotor assembly of an aircraft including a first rotor co-axial with a second rotor includes identifying a first zone of rotor rotation angles of the co-axial rotor assembly. The first zone defines a range of rotor rotation angles corresponding to an up-flow of air to the coaxial rotor assembly, and the remainder of the rotor rotation angles other than the first zone of rotation angles is defined as a second zone. The method includes receiving a yaw command to adjust a yaw moment of the aircraft and applying a different rotor blade angle change to rotor blades in the first zone than a rotor blade angle change applied to rotor blades in the second zone to adjust the yaw moment of the aircraft according to the yaw command. | 04-09-2015 |
20150102158 | Coaxial Rotor Yaw Control - A method includes determining, by a computing device comprising a processor, a value for at least one parameter related to an operation of a coaxial rotary wing aircraft; processing, by the computing device, the at least one parameter to determine control power available from one or more flight controls comprising a differential cyclic; and establishing, by the computing device, a value for the differential cyclic to create a net yaw moment for the rotary wing aircraft based on the determination of the available control power. | 04-16-2015 |
20150307182 | ADVANCED PITCH STABILIZER - A pitch stabilizer with box configuration suitable for providing stability to a rotorcraft comprising a vertical mid-plane and a fuselage; the pitch stabilizer comprising one or two pitch stabilizing assemblies, with no more than one pitch stabilizing assembly on each side of the vertical mid-plane, wherein each pitch stabilizing assembly comprises upper pitch stabilizing means, lower pitch stabilizing means and a wing tip element. | 10-29-2015 |
20150314866 | ACCELERATION SMOOTHING HOLDING OVERALL KINETIC ENERGY CONTROL - A method and system for controlling maneuverability of an aircraft includes receiving one or more signals indicative of commanded peak rotary acceleration at a first timeperiod; determining a signal indicative of an actual peak rotary acceleration for the first timeperiod in response to the receiving of the one or more signals for commanded pilot acceleration; and determining signals indicative of actual rotary acceleration for a second timeperiod. | 11-05-2015 |
20150331427 | Control Method to Damp Quadrotor Slung Payload Mode - A quadrotor or other vertical lift aerial vehicle measures an angle of a payload slung from the quadrotor relative to a body of the quadrotor. Using this measurement a signal may be generated that adjusts a flight characteristic of the quadrotor to counteract swing in the payload. A feedback function for generating the feedback signal may include proportional and derivative gain functions as well as non-linear signal processing functions. The feedback signal may be added to normal input control signals to cause acceleration in the direction of the payload angle that damp oscillation of the slung payload caused by wind or movements of the quadrotor. | 11-19-2015 |
20150375849 | FLIGHT CONTROL SYSTEM AND METHOD WITH TRACK MAINTENANCE FOR A ROTARY WING AIRCRAFT - A flight control system for a rotary wing aircraft, the aircraft following a track T | 12-31-2015 |
20150375850 | FLIGHT CONTROL SYSTEM AND METHOD FOR A ROTARY WING AIRCRAFT, ENABLING IT TO MAINTAIN EITHER TRACK OR HEADING DEPENDING ON ITS FORWARD SPEED - A flight control method and system for a rotary wing aircraft. When the longitudinal speed U | 12-31-2015 |
20150375851 | METHOD AND SYSTEM FOR ENGAGING HOVERING FLIGHT FOR A ROTARY WING AIRCRAFT, ENABLING IT TO MAINTAIN EITHER TRACK OR HEADING DEPENDING ON ITS FORWARD SPEED - A method and a system for engaging hovering flight for a rotary wing aircraft. A first mode of operation makes it possible, while the longitudinal speed U | 12-31-2015 |
20160009388 | Electric VTOL Aircraft | 01-14-2016 |
20160016664 | UNMANNED AERIAL DELIVERY DEVICE - An unmanned aerial delivery device has a plurality of rotors for propulsion and control, including redundant rotors in case of failure of a primary rotor, and uses a Laser Rangefinder system to guide the delivery device around an obstacle in its path until an acceptable straight-line path to a recipient is found, detect when a rotor is inoperable, and detect the distance from a take-off or landing surface to retract or extend support legs. The device has an insulated payload chamber that can only be opened by entering an unlock code on a touchscreen | 01-21-2016 |
20160023755 | SYSTEM AND METHOD FOR CONTROL OF QUADROTOR AIR VEHICLES WITH TILTABLE ROTORS - A system and method of controlling quadrotor air vehicles (QRAV) that may include an additional two degrees of freedom for each of the four propellers of the QRAV. Each of the four rotors may be allowed to rotate (tilt) around two local axes selected from the x-axis (roll), y-axis (pitch), and z-axis (yaw). Control of the quadrotor including the additional two degrees of freedom allows thrust of each rotor to be direct in any direction of a semi-sphere. As a result, total control inputs of the QRAV may be increased to twelve, enabling smooth control to achieve superior and precise maneuverability. Additionally, the system and method is fault tolerant and capable of handling failures of any of the rotors. Commands to the propellers may be fully decoupled and achieved independently thereby giving pilots better control to execute difficult maneuvers. | 01-28-2016 |
20160031558 | UNMANNED AERIAL VEHICLE AND OPERATIONS THEREOF - 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. | 02-04-2016 |
20160075431 | UNMANNED AERIAL VEHICLE AND OPERATIONS THEREOF - 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. | 03-17-2016 |
20160083076 | AUTOMATIC PROPELLER TORQUE PROTECTION SYSTEM - An aircraft is provided and includes one or more main rotors, one or more and propellers including blades that are rotatable about a rotational axis, a pitch of each of the blades being controllable, and a flight control computer disposed to control the pitch of each of the blades to reduce propeller blade pitch angles in an event of an engine failure. | 03-24-2016 |
20160101856 | WEARABLE UNMANNED AERIAL VEHICLES, AND ASSOCIATED SYSTEMS AND METHODS - Wearable unmanned aerial vehicles and associated systems and methods are disclosed. A representative unmanned aerial vehicle includes a wearable, flyable support structure, and a propulsion system carried by the support structure. The propulsion system can include a power source and a plurality of propellers. In particular embodiments, the support structure can include a wrist band. | 04-14-2016 |
20160121997 | ROTORCRAFT TOP FAIRING FITTED WITH A MOVABLE MEMBER FOR GUIDING A STREAM OF AIR FLOWING TOWARDS THE REAR OF THE ROTORCRAFT - A rotorcraft provided on top with a waterdrop-shaped fairing arranged below the rotary wing of a main rotor of the rotorcraft and overlying a cover covering a power plant of the rotorcraft. The trailing edge(s) of the fairing is/are provided with a respective movable member guiding a first stream of air flowing along the fairing and escaping from the trailing edge towards the rear of the rotorcraft in flight. By way of example, the movable member is arranged as a flap or as a bladed roller that may potentially be motor-driven as a function of the effects of the first stream of air on the behavior of the rotorcraft in flight. | 05-05-2016 |
20160122018 | Observation Device - A observation device includes an aircraft and an observation unit attached to the aircraft that observes a target within a predetermined view angle. The aircraft includes a base, at least two thrusters that generate a propulsion force including lift, actuators that change a direction of the propulsion force generated by the thrusters with respect to the base, an inertial measurement unit (IMU) that detects an orientation of the base with respect to a ground surface, and a controller that controls the thrusters and the actuators based on the orientation of the base detected by the IMU. The observation unit is fixedly attached to the base and the aircraft is configured to fly in any arbitrary orientation with respect to the ground surface through a combination of a magnitude of the propulsion force and the direction of the propulsion force of each of the thrusters. | 05-05-2016 |
20160130010 | INVERTIBLE AIRCRAFT - A rotorcraft including a fuselage, one or more motor-driven rotors for vertical flight, and a control system. The motors drive the one or more rotors in either of two directions of rotation to provide for flight in either an upright or an inverted orientation. An orientation sensor is used to control the primary direction of thrust, and operational instructions and gathered information are automatically adapted based on the orientation of the fuselage with respect to gravity. The rotors are configured with blades that invert to conform to the direction of rotation. | 05-12-2016 |