Abstract: A system and method for operating an indoor/outdoor drone in a training mode that limits the maximum altitude during flight, restricts the ability to perform rapid maneuvers, and also may disable the ability to conduct aerial stunts. The system includes a flight controller that may select between the training mode, a normal mode, and a stunt mode. In the training mode, the flight controller restricts an increase in altitude of the drone beyond an altitude threshold, and also restricts an increase in one or more movement parameters of the drone beyond respective movement parameter thresholds. The selection of the training mode may disable the ability for the user to select the stunt mode.

Abstract: A method and a system for establishing an approach to hover path for a rotorcraft enabling it to approach a mobile target and to hover relative to the target. An initial approach to hover path is firstly defined from measurements of the characteristics of the respective routes of the target and of the rotorcraft and also of the wind conditions to which the rotorcraft is subjected. During the flight of the rotorcraft, a required approach to hover path is determined in real time as a function of potential variations in the characteristics of the target, of the rotorcraft, and of the wind. Thereafter, the initial path is updated by the required path where necessary in order to guarantee safety of the approach to hover path for the rotorcraft relative to the target.

Abstract: A combined active stick and control boost actuator system for a control surface has a control stick engaged to a mechanical flight control structure with a linkage configured to move a control surface. A mechanical interconnect engages the linkage and has a control stick connection. An integrated actuator is separably connected to the mechanical interconnect intermediate the control stick connection and the linkage. A stick force sensor is configured to provide a stick force signal. A flight control system receives the stick force signal and provides an actuator position control signal to the integrated actuator. The integrated actuator moves to a prescribed position in accordance with a force feel profile providing pilot variable tactile cueing and power boost to reduce both fatigue and workload.

Abstract: 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.

Abstract: A control system for a machine having variable rate damping based control (VRDC) is disclosed, and includes one or more processors and a memory coupled to the processors storing data comprising a database and program code that, when executed by the processors, causes the control system to receive an inceptor position from one or more active inceptors and calculate an operator command based on at least the inceptor position. The control system is caused to determine an amplitude of the operator command. The control system is caused to determine a variable gain based on the amplitude of the operator command and determines an actuation command based on the variable gain. The control system sends the inline actuators the actuation command. The inline actuators actuate into a total actuator position to variably damp movement of the machine as a function of the magnitude of the operator command.

Abstract: An apparatus, system and method is described for controlling one or more consumer electronic devices that is performed by a smart device. The smart device causes one or more graphical elements, each for performing a particular operation to be displayed. The smart device then causes an action to be performed when the user selects one of the graphical elements, for example by pressing one of the keys on the universal controlling device or by speaking a command.

Abstract: A rotorcraft includes a flight control computer (FCC), a GPS receiver configured to calculate a groundspeed based on a first carrier signal, and an attitude and heading reference system (AHRS) configured to determine an acceleration of the rotorcraft. The AHRS is operable to receive an indication of the groundspeed from the GPS receiver and to calculate a velocity of the rotorcraft based on the indication of the groundspeed and the acceleration. The FCC is operable to receive an indication of the velocity from the AHRS, to generate the flight control device control signal according to the indication of velocity, and to send a flight control device control signal to one or more flight control devices.

Abstract: An embodiment rotorcraft includes a rotor system including a plurality of blades; a control assembly operable to receive commands from a pilot; a flight control system (FCS), the flight control system operable to control flight of the rotorcraft by changing an operating condition of the rotor system; and a flight management system (FMS) in signal communication with the control assembly and the FCS. The FMS is operable to receive a target location and a plurality of approach parameters from the control assembly; generate a plurality waypoints between a current location of the rotorcraft and a missed approach point (MAP) based on the target location and the plurality of approach parameters; receive a command to engage in an approach maneuver from the control assembly; and in response to the command to engage in the approach maneuver, instruct the FCS to fly to the MAP.

Abstract: The present disclosure provides methods and system for providing takeoff pitch guidance for an aircraft. Takeoff pitch guidance for the aircraft is provided in a pitch target mode at a time of takeoff. The pitch target mode corresponds to determining pitch as a function of a target pitch based on aircraft operating parameters. A transition event is detected while in the pitch target mode. The takeoff pitch guidance for the aircraft is transitioned from the pitch target mode to an airspeed error mode after the transition event is detected and the takeoff pitch guidance is provided in the airspeed error mode. The airspeed error mode corresponds to determining pitch based on a difference between an actual speed and a target speed of the aircraft.

Abstract: A drive machine coupling device for a motor vehicle with a hybrid drive is provided. The device includes an input shaft designed to receive the drive power provided by a first drive machine, an output shaft designed to output the drive power, and a first coupling device arranged between the input shaft and the output shaft. By way of the first coupling device, a torque can selectively be transmitted from the input shaft to the output shaft. The coupling device can be directly coupled to the output shaft. An additional coupling device is arranged between the input shaft and the output shaft, and can be directly coupled to the output shaft, such that a torque can selectively be transmitted from the input shaft to the output shaft. The additional coupling device is arranged parallel to the first coupling device with respect to the torque transmission.

Abstract: 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.

Abstract: In an embodiment, a rotorcraft includes: a rotor system; a sensor; a flight control device; and a flight control computer (FCC) coupled to the rotor system, the sensor, and the flight control device, the FCC configured to: determine a rotation speed of the rotor system; select a first aeroservoelasticity filter configuration from a plurality of aeroservoelasticity filter configurations according to the rotation speed of the rotor system, the aeroservoelasticity filter configurations being predetermined configurations corresponding to different rotation speeds of the rotor system; receive a signal from the sensor; filter the signal according to the first aeroservoelasticity filter configuration; and adjust the flight control device according to the filtered signal.

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

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

Abstract: In an embodiment, a rotorcraft includes: a flight control computer configured to: receive a first sensor signal from a first aircraft sensor of the rotorcraft; receive a second sensor signal from a second aircraft sensor of the rotorcraft, the second aircraft sensor being different from the first aircraft sensor; combine the first sensor signal and the second sensor signal with a complementary filter to determine an estimated vertical speed of the rotorcraft; adjust flight control devices of the rotorcraft according to the estimated vertical speed of the rotorcraft, thereby changing flight characteristics of the rotorcraft; and reset the complementary filter in response to detecting the rotorcraft is grounded.

Abstract: A method of controlling rotor moments includes receiving, in a flight control computer (FCC) a rotor moment reference value based on pilot inceptor inputs, sensing rotor moment from one or more sensors, receiving, in the FCC, a rotary wing aircraft condition parameter, and establishing, through the FCC, a rotor blade pitch angle for one or more of a plurality of rotor blades that counteracts external forces acting upon the rotary wing aircraft.

Abstract: Systems and methods include UAVs that serve to assist carrier personnel by reducing the physical demands of the transportation and delivery process. A UAV generally includes a UAV chassis including an upper portion, a plurality of propulsion members configured to provide lift to the UAV chassis, and a parcel carrier configured for being selectively coupled to and removed from the UAV chassis. UAV support mechanisms are utilized to load and unload parcel carriers to the UAV chassis, and the UAV lands on and takes off from the UAV support mechanism to deliver parcels to a serviceable point. The UAV includes computing entities that interface with different systems and computing entities to send and receive various types of information.

Abstract: An unmanned aerial vehicle subsystem includes a vehicle-mountable light bar. The light bar includes a periphery and a plurality of lights configured to illuminate through at least a portion of the periphery. The light bar further defines a volume within which is positioned an unmanned aerial vehicle pad and a tether extension and retraction mechanism. The subsystem further includes an unmanned aerial vehicle having at least one camera. A tether is operable with the tether extension and retraction mechanism and extendable from the tether extension and retraction mechanism to the unmanned aerial vehicle. The tether is configured to, during flight of the unmanned aerial vehicle, transmit power to the unmanned aerial vehicle and transmit data signals to and from the unmanned aerial vehicle.

Abstract: Methods, systems, and apparatus for an intelligent protective drone are described. The intelligent protective drone comprises an environmental protective shield that provides protection from environmental elements. An image of an environment near the aeronautical drone is captured and processed to identify a target entity. A geographical location of an effective protective area provided by the environmental protective shield is identified and a location for the aeronautical drone is determined that places the target entity within the effective protective area.

Abstract: An aerial vehicle includes a hull containing the main processor, energy storage, support components such as sensors, wireless communication, and landing gear. Attached to the hull are at least three thrust or propulsion units each with two degrees of freedom from the hull allowing them to orient independently in any direction and apply thrust independently from the hull or any other thrust or propulsion unit. In some embodiments, a mount for auxiliary attachments is included or the auxiliary system is built into the hull. Components like the energy storage, auxiliary attachments, and/or propulsion units may also be replaceable as required.

Abstract: An unmanned aerial vehicle system includes a ground station including a case, a power supply housed in the case, and a tether having a first end and a second end opposite to the first end. The first end of the tether is coupled to the case. The unmanned aerial vehicle system also includes a module including smart battery authentication circuitry configured to be coupled to the second end of the tether. The module is configured to be connected to an unmanned aerial vehicle. The smart battery authentication circuitry enables the unmanned aerial vehicle to receive power from the power supply housed in the case when the module is connected to the unmanned aerial vehicle.

Abstract: A rotorcraft including a main rotor, flight controls connected to the main rotor, a plurality of engines connected to the main rotor and operable to drive the main rotor, a main rotor revolutions per minute (RPM) sensor, and a monitoring system operable to determine an engine failure of the plurality of engines. The monitoring system is further operable to engage an automated autorotation entry assist process in response to at least determining the engine failure and according to the measured main rotor RPM, where the automated autorotation entry assist process comprises the monitoring system generating one or more rotor RPM related commands according to at least a target main rotor RPM and the measured main rotor RPM, where the automated autorotation entry assist process further comprises controlling the one or more flight controls according to the one or more rotor RPM related commands.

Abstract: A fly-by-wire system for a rotorcraft includes a computing device having control laws. The control laws are operable to engage a level-and-climb command in response to a switch of a pilot control assembly being selected. The level-and-climb command establishes a roll-neutral (“wings level”) attitude with the rotorcraft increasing altitude. The switch may be disposed on a collective control of the pilot control assembly (e.g., a button on a grip of the collective control). Selection of the switch may correspond to a button depress. The level-and-climb command may include a roll command and a collective pitch command. One or more control laws may be further operable to increase or decrease forward airspeed in response to pilot engagement of the level-and-climb command. The level-and-climb command may correspond to a go-around maneuver, an abort maneuver, or an extreme-attitude-recovery maneuver to be performed by the rotorcraft.

Abstract: A system and method of controlling flight of an aircraft is disclosed. The system includes a first inceptor that provides a direct mode command for controlling a control axis of the aircraft according to a direct mode and a second inceptor that provides a stable mode command for controlling the control axis of the aircraft according to a stable mode. A processor receives the direct mode command and the stable mode command, forms a combined command for controlling the control axis of the aircraft based on a combination of the direct mode command and the stable mode command, and controls the control axis of the aircraft according to the combined command.

Abstract: An aircraft and method of flying an aircraft are disclosed. The aircraft includes a cross-feed unit that receives a flight command for the aircraft and determines an amount of fuel for a motor of the aircraft in order to reduce a droop in the aircraft when executing the flight command at the aircraft. A fuel injector or fuel supplier provides the determined amount of fuel to the motor when the flight command is executed at the aircraft.

Abstract: A ganged servo flight control system for an unmanned aerial vehicle is provided. The flight control system may include a swashplate having first, second, and third connection portions; a first control assembly connected to the first connection portion of the swashplate; a second control assembly connected to the second connection portion of the swashplate; and a third control assembly connected to the third connection portion of the swashplate. The first control assembly may include two or more servo-actuators connected to operate in cooperation with each other.

Abstract: An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly composed of a plurality of blades and a lower rotor assembly composed of a plurality of blades. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. A flight control system to control the upper rotor assembly and the lower rotor assembly, wherein the flight control system is configured to control lift offset of the upper rotor assembly and the lower rotor assembly.

Abstract: A variable pitch mechanism for a helicopter is configured to have a simple configuration with a small number of members, and to be capable of precisely controlling a pitch angle of blades without accurate adjustment. A pitch plate 16 and a pitch plate boss 17 are slidably mounted on an outer periphery of a main mast 61, and an output shaft of a servomotor 19 is directly connected to a pitch lever 18 that vertically moves the pitch plate boss 17. By actuating the servomotor 19 and rotating the pitch lever 18, the pitch plate boss 17 and the pitch plate 16 are displaced upward or downward along the main mast 61, thereby tilting blade holders 13, 13 connected to the pitch plate 16 and changing a pitch angle of the blades 14.

Abstract: A fly-by-wire aircraft and method of flying a fly-by-wire aircraft is disclosed. The aircraft includes a control system for flying the aircraft in one of a proportional ground control mode and a model following controls mode. A control device at a control interface of the aircraft selectively activates a trim follow up function in the control system. When flying the aircraft in a proportional ground control mode, trim follow up function can be activated. The control system can then transition into the model following controls mode with the trim follow up function activated to reduce transient behavior.

Abstract: 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.

Abstract: The aircraft includes a rotor. The rotor includes a plurality of rotor blades. The aircraft further includes a non-rotating aircraft component. A proximity sensor is disposed with at least one of the non-rotating aircraft component and the rotor blades. A flight control computer is electrically coupled to the proximity sensor.

Abstract: The invention relates to a method for destination approach control of unmanned aerial vehicles, in particular delivery drones, to an arbitrary location defined by the recipient.

Abstract: The aircraft includes a rotor. The rotor includes a plurality of rotor blades. The aircraft further includes a non-rotating aircraft component. A proximity sensor is disposed with at least one of the non-rotating aircraft component and the rotor blades. A flight control computer is electrically coupled to the proximity sensor.

Abstract: A wireless transmitter includes a pair of control sticks, circuitry coupled to control sticks, and an antenna coupled to the circuitry. The circuitry is configured to process signals produced by the control sticks to provide control inputs for the speed, direction, and other flight characteristics of the model aircraft being controlled by the transmitter. The transmitter is configured for multiple operational modes in which the pair of control sticks engage or disengage functionality, such as return-to-center functionality, vertical or horizontal position limiting functionality, or position select functionality.

Abstract: In some embodiments, methods and systems of facilitating movement of product-containing pallets include at least one forklift unit configured to lift and move the product-containing pallets, at least one motorized transport unit configured to mechanically engage and disengage a respective forklift unit, and a central computer system in communication with the at least one motorized transport unit. The central computer system is configured to transmit at least one signal to the at least one motorized transport unit. The signal is configured to cause the at least one motorized transport unit to control the at least one forklift unit to move at least one of the product-containing pallets.

Abstract: Methods for interactive communication between an object and a smart device are provided. Signals can be transmitted from the smart device to the object to control movement of a movable part at the object. Signals can also be transmitted from the smart device to the object to broadcast words and/or songs at a speaker at the object. In addition, in response to a user's touching the object, the object's speaker can broadcast words and/or songs. The signals transmitted from the smart device to the object transceiver can be audio signals so as to create a two-way interactive and live communication. In addition, voice instructions can be spoken into the microphone of the object, and then transmitted from the object to the smart device to initiate an activity at the smart device.

Abstract: An aircraft defining an upright orientation and an inverted orientation, a ground station; and a control system for remotely controlling the flight of the aircraft. The ground station has an auto-land function that causes the aircraft to invert, stall, and controllably land in the inverted orientation to protect a payload and a rudder extending down from the aircraft. In the upright orientation, the ground station depicts the view from a first aircraft camera. When switching to the inverted orientation: (1) the ground station depicts the view from a second aircraft camera, (2) the aircraft switches the colors of red and green wing lights, extends the ailerons to act as inverted flaps, and (3) the control system adapts a ground station controller for the inverted orientation. The aircraft landing gear is an expanded polypropylene pad located above the wing when the aircraft is in the upright orientation.

Abstract: In one embodiment, a horizontal stabilizer comprises an airfoil structure configured to be mounted to an aircraft at a horizontal orientation. The airfoil structure comprises a leading edge, a trailing edge, a top surface, and a bottom surface. Moreover, the airfoil structure is cambered, wherein a camber of the airfoil structure forms a concave slope on the top surface and a convex slope on the bottom surface.

Abstract: In one aspect, an example system includes: (i) a base including a bottom surface and a first coupling-point; (ii) a vertically-oriented elongate structure comprising a lower end, an upper end, and an inner channel, wherein the inner channel comprises an upper access-point disposed proximate the upper end, wherein the base is coupled to the elongate structure proximate the lower end; (iii) a deployable cushioning-device coupled to the elongate structure; and (iv) a tether comprising a first portion, a second portion, a third portion, and a fourth portion, wherein the first portion is coupled to the first coupling-point, the second portion is coupled to a second coupling-point of the UAV, the third portion extends through the inner channel, the fourth portion extends from the upper access-point to the second coupling-point, and the fourth portion has a length that is less than a distance between the upper access-point and the bottom surface.

Abstract: A system for video imaging and photographing using an autonomous aerial platform. The system may be a quad rotor system using electrically powered propellers. The aerial platform may be commanded by the user to follow an object of interest. The aerial platform may have multiple configurations for its thrust units such that they are clear of the field of view of the imaging device in a first configuration, such that they protect the imaging device during landing in a second configuration, and that allows for efficient storage in a stowed configuration.

Abstract: A method of operating a rotorcraft includes transitioning from a first mode to a second mode when a velocity of the rotorcraft exceeds a first velocity threshold. Transitioning between the first and second modes includes fading out a gain of a dynamic controller over a first period of time, and decreasing a value of an integrator of the dynamic controller over a second period of time. In the first mode, the translational speed of the rotorcraft is determined based on a pilot stick signal, and in the second mode, an output of an attitude rate controller is proportional to an amplitude of the pilot stick signal.

Abstract: A method for providing haptic feedback to a user of a rotary wing aircraft that includes receiving, by a computing device, a signal indicative of a user input selecting a control system state for a rotary wing aircraft, where, upon selection, the control system state modifies one or more operational parameters of the rotary wing aircraft, and in response to receiving the signal, outputting, by the computing device, a signal to a shaker system coupled to a collective stick, where the signal is configured to cause the shaker system to provide a haptic feedback via the collective stick, and where the haptic feedback includes a signature that indicates that the control system state has been activated.

Abstract: A vertical takeoff and landing (VTOL) fixed-wing aircraft having overlapping propellers and low handing vertical stabilizers disposed on the rear end of the aircraft.

Abstract: An automatic piloting system intended for an aircraft comprising an aircraft signals acquisition module, a module for interfacing with the crew, and a module for processing the output signals, comprises: a generic software kernel for automatic piloting aboard the aircraft, comprising several parameterizable elementary cells, a parameterization tool for the generic software kernel, able to transform an operational need of the automatic piloting system, expressed by means of a configuration file in accordance with a predetermined configuration domain DC, into a database of binary parameters DB able to parameterize the generic software kernel; each cell being parameterized by the database DB, and means for loading and storage aboard the aircraft of the database DB.

Abstract: An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly with an upper blade and a lower rotor assembly with a lower blade. A first antenna in one of upper blade and the lower blade, and a second antenna in the other of the upper blade and the lower blade. An oscillator to apply an excitation signal to the first antenna. A blade proximity monitor to monitor a magnitude of the excitation signal and an output signal from the second antenna to determine a distance between the upper blade and the lower blade.

Abstract: A rotary wing aircraft including a vehicle vibration control system.

Abstract: A method of assisting in rotor speed control in a rotorcraft can include measuring a rotor speed with a sensor; detecting a droop in the rotor speed beyond a lower droop limit; and commanding a decrease in collective in response to the rotor speed drooping beyond the lower droop limit. A system of assisting in rotor speed control in a rotorcraft, the system can include: a computer having a control law, the control law operable to generate a decrease collective command to an actuator in response to a rotor speed decreasing below a lower droop limit; wherein the lower droop limit is below a normal lower rotor speed range.

Abstract: In accordance with an embodiment, a method of operating a rotorcraft includes operating the rotorcraft in a position hold mode by determining whether GPS position data is usable, receiving a position of the rotorcraft from a GPS sensor, determining a position error based on received GPS position data and a held position when the GPS position data is usable, determining the position error based on a rotorcraft velocity when the GPS position data is not usable, and transmitting an actuator command based on the determined position error.

Abstract: In one aspect, an example system includes: (i) a base including a bottom surface and a first coupling-point; (ii) a vertically-oriented elongate structure comprising a lower end, an upper end, and an inner channel, wherein the inner channel comprises an upper access-point disposed proximate the upper end, wherein the base is coupled to the elongate structure proximate the lower end; (iii) a deployable cushioning-device coupled to the elongate structure; and (iv) a tether comprising a first portion, a second portion, a third portion, and a fourth portion, wherein the first portion is coupled to the first coupling-point, the second portion is coupled to a second coupling-point of the UAV, the third portion extends through the inner channel, the fourth portion extends from the upper access-point to the second coupling-point, and the fourth portion has a length that is less than a distance between the upper access-point and the bottom surface.

Abstract: Techniques for calculating a sound received at a plurality of distances from an unmanned aerial vehicle (UAV) may be provided. For example, during delivery, the UAV may be associated with a sensor to obtain first sound information that corresponds to the sound generated by the UAV. A sensor associated with a landing marker may obtain second sound information about the sound generated by the UAV during flight and delivery of a payload to a location associated with the landing marker. In embodiments, the first sound information and the second sound information may be utilized to calculate sound metrics for the sound generated by the UAV and determine the sound received at a plurality of distances from the UAV during flight.