353results about "Actuated automatically" patented technology

An unmanned aerial vehicle that transports harvested crops harvested from a field, includes a flight device to cause the unmanned aerial vehicle to fly, a controller configured or programmed to control operation of the flight device, a communication device to receive package position information indicating a first position where a target package for transport containing the harvested crops is located, and package weight information, and a support device to support the target package. The controller is configured or programmed to determine, based on the package weight information, whether the target package can be transported to a second position different from the first position, and when doing so, control the flight device to cause the unmanned aerial vehicle to fly to the first position, cause the support device to support the target package, and control the flight device to cause the unmanned aerial vehicle to fly to the second position.

Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45′ diameter) footprint.

A flight path generation system for generating a three-dimensional flight path for an unmanned aerial vehicle includes an acquisition device to acquire route data including information of a two-dimensional flight path of the unmanned aerial vehicle and map data including information of elevation at each point on the two-dimensional flight path, and a processor configured or programmed to generate the three-dimensional flight path by determining a flight altitude of the unmanned aerial vehicle from a ground on the two-dimensional flight path based on the two-dimensional flight path and the elevation. The processor is configured or programmed to determine the flight altitude in an excess region with an altitude not exceeding a first altitude and a first region with an altitude not exceeding the first altitude, such that a maximum value of the flight altitude of the unmanned aerial vehicle in the excess region does not exceed the first altitude.

Systems, methods, and devices include an aerial vehicle (AV) with a plurality of coaxially aligned vertical ducts. The lower vertical duct has a larger diameter than the upper vertical duct. Furthermore, the upper vertical duct at least partially contains a first propulsion component and the lower vertical duct at least partially contains a second propulsion component. The lower vertical duct can be coupled to the upper vertical duct by duct couplers which forms an air intake gap between the upper vertical duct and the lower vertical duct. The AV also includes one or more steering flaps disposed on the lower vertical duct, configured to manipulate an air flow out the bottom of the lower duct, thus controlling navigation and stability of the AV.

Aspects of the present disclosure generally relate to systems and methods for flight control of aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, a flight control system of an aircraft is disclosed, configured to receive one or more signals to control movement of the aircraft, determine at least one flight condition of the aircraft, calculate at least one or more loads associated with the aircraft based on the determined at least one flight condition; determine a flight configuration to alleviate loads on one or more components of the aircraft based on the received one or more signals and the calculated one or more loads by predicting a distribution of loads associated with the aircraft, generate one or more effector commands based on the flight configuration; and actuate one or more aircraft effectors based on the one or more effector commands.

This disclosure relates to systems and methods for providing a copilot replacement system (CPRS) that enables dual-pilot or multi-pilot aircraft to be operated by a single onboard pilot. This disclosure also relates to systems and method for integrating an artificial intelligence (AI) controller into the aircraft, which autonomously provides assistance with controlling operation of the aircraft. Amongst other things, the solutions described herein can autonomously execute various functions for controlling the aircraft and / or can establish connections with one or more copilot ground base stations (GBSs) that enable ground-based copilots to remotely provide assistance with operating the aircraft. Both onboard pilots and remote pilots can be provided with override controls that enable the pilots to override, cancel, and / or modify actions undertaken by the AI controller.

[Problem] To provide an unmanned aerial vehicle, a method for controlling an unmanned aerial vehicle, a program, a control system, and a control device with which it is possible to detect an unexpected object during flight and perform appropriate emergency control. [Solution] An unmanned aerial vehicle according to one embodiment of the present invention comprises: an imaging device that is provided to the unmanned aerial vehicle and generates a captured image; an object detection unit that detects an object from the captured image; a determination unit that determines whether the object detected by the object detection unit satisfies a predetermined condition; and a flight control unit that, when the determination unit determines that the condition is satisfied, causes the own vehicle body to execute emergency control.

An automated control system for a glider towed by a tug employs a sensor system (e.g., cameras mounted on at least one of the aircraft) to determine the relative position and velocity of the glider. A controller determines corrections to the flight characteristics of the glider in response to this data from the sensor system to maintain the glider on the surface of a limit sphere extending behind the tug with a predetermined radius based on the length of the tow cable. An interface to the flight controls of the glider maintains the desired flight characteristics of the glider provided by the controller.

An aircraft wing is disclosed having a fixed wing with a tip, and a wing tip device rotatably mounted on a hinge at the tip of the fixed wing, such that the wing tip device is rotatable about the hinge, and an actuation system for rotating the wing tip device about the hinge. The actuation system includes a motor, at least one geared rotary actuator, a reduction gearbox, a clutch for selectively decoupling rotation of the motor from rotation of the geared rotary actuator, the geared rotary actuator is driveable by the motor and arranged to convert rotary motion into a different rotary motion and is arranged to rotate the wing tip device relative to the tip of the fixed wing. The clutch is coupled to the geared rotary actuator by a shaft and the shaft is fixed in rotation to a mass disposed radially outwardly from the shaft.

Examples relate to uncrewed aerial vehicles (UAVs) and methods for controlled descent during control tier failures. A computing device may initially detect a control tier failure at an UAV. In some examples, the UAV includes a fuselage, a pair of wings extending outwardly from the fuselage, and a pair of stabilizers arranged in a V-shape configuration. Each stabilizer has a control surface that is adjustable relative to a fixed portion of the stabilizer. Based on detecting the control tier failure at the UAV, the computing device may adjust the control surface of each stabilizer from a first angle to a second angle relative to the fixed portion of the stabilizer. By adjusting the angle between the control surfaces and fixed portions of one or both stabilizers, the UAV may induce a deep stall maneuver that can enable a controlled descent of the UAV.

A craft comprises a hull, a wing, a hydrofoil, and a control system. The wing is configured to generate upwards aero lift as air flows past the wing to facilitate wing-borne flight of the craft. The hydrofoil is configured to generate upwards hydrofoil lift during a first mode of operation as water flows past the hydrofoil to facilitate hydrofoil-borne movement of the craft through the water. While the craft is hydrofoil-borne, the control system is configured to determine the upwards aero lift generated by the wing. The control system is further configured to control the hydrofoil to generate downwards hydrofoil lift to counteract the upwards aero lift generated by the wing that maintains the hydrofoil at least partially submerged in the water while the determined upwards aero lift is below a threshold lift.

Provided are a method and a system for cooperative airborne meteorological perception with multiple aircraft. The method includes: determining a training set based on a spatial position, motion data, weather, an observation image, and static information of each of multiple aircraft; determining a fusion performance function based on an objective of a cooperative perception network; generating a fusion model based on the training set and the fusion performance function; generating a perception result image based on the fusion model; determining flight risk information based on the perception result image; determining a route alarm command and sending the route alarm command to a management user interface and an interactive device of a target aircraft; after receiving the route alarm command, generating, by the management user interface, a route adjustment parameter; in response to obtaining the route adjustment parameter, performing at least one of the following operations: adjusting an engine velocity, adjusting an aileron pressure, adjusting an elevator deflection, and adjusting a rudder deflection.

An electric vertical take-off and landing aircraft comprises a fuselage and a tilt wing. The tilt wing is tiltable relative to the fuselage in a range of tilt wing angles. Control surfaces are arranged at the tilt wings. The aircraft comprises a horizontal stabilizer with an elevator, in particular a stabilator, a vertical stabilizer with a rudder, in particular a fully movable stabilizer, at least one electric engine for powering main propellers arranged at the tilt wing and at least one software control device. The control device is configured to control at least the control surfaces , the main propellers and the tilt wing angle during hover and transition between hover and cruise flight.

According to an embodiment, a control device controls a user-wearable flight device and includes a processing unit configured to acquire state data related to a state of the flight device and manipulation data related to a manipulation of the flight device, input the acquired state data and the acquired manipulation data to a model trained using deep reinforcement learning, and control the flight device on the basis of an output result of the model to which the state data and the manipulation data are input.

A vertical take-off and landing aircraft and a control method for a vertical take-off and landing aircraft. The vertical take-off and landing aircraft includes a fuselage (10), four tilting rotors and four fixed rotors. Wings (20) are symmetrically provided at both sides of the fuselage (10); four tilting rotors are respectively installed at the front and rear sides of the wings (20) on both sides, and are pairwise correspondence and symmetrical about the longitudinal symmetry plane (11) of the fuselage (10). A spacing of the tilting rotors at the front side of the wing (20) is A, a spacing of the tilting rotors at the rear side of the wing (20) is B, and a deviation between A and B is less than or equal to 0.2*(A+B) / 2. Four fixed rotors are respectively provided at outer sides of the tilting rotors at both sides of the fuselage, and provided at the front sides and the rear sides of the wings (20), and are pairwise correspondence and symmetrical about the longitudinal symmetry plane (11). A spacing between two fixed rotors at the front sides of the wings (20) is C, a spacing between two fixed rotors on the rear sides of the wings (20) is D, and a deviation between C and D is less than or equal to 0.05*(C+D) / 2.

Aspects of the present disclosure generally relate to systems and methods for flight control of aircraft driven by an electric propulsion system and in other types of vehicles. In some embodiments, an aircraft is disclosed, the aircraft comprising: at least one electric propulsion unit; at least one sensor configured to measure at least one aircraft condition; and at least one flight control computer configured to dynamically vary at least one torque command for the at least one electric propulsion unit based at least on the at least one aircraft condition; wherein the at least one electric propulsion unit is configured to generate thrust based on at least one dynamically changed torque command.

To properly and surely monitor a lighting state of an outdoor lamp and properly perform a notification in a case where abnormality is found.SOLUTION: An outdoor lamp monitoring system comprises: a camera 3 which is mounted on a flying drone 2; and a monitoring server 4 which determines the presence / absence of abnormality in a lighting state of an outdoor lamp L based on an image of the outdoor lamp L captured by the camera 3 and, when the presence of abnormality is determined, performs a notification to a previously stored notification destination 5.SELECTED DRAWING: Figure 1

Operation control unit controls flight driving mechanism such that drone performs an operation by which detection values of sensors included in sensors included in drone match a target value. Detection unit detects, when a plurality of drones perform an operation by which detection values of the sensors included in sensors included in the plurality of drones match a target value, a difference in an operation result of each of drones. Clustering unit classifies a plurality of drones, including drone in which clustering unit is included, into at least one cluster based on differences in operation results detected by detection unit. Correction unit corrects the detection values of the sensors based on the operation results of drones included in a maximum cluster of the classified clusters.

An active side lever controller for controlling pitching and rolling motions of an aircraft, having a mechanical backup, comprising: a cross-shaped hinge assembly connected to an operating handle and implementing a two-degree-of-freedom rotation of a side lever in pitching and rolling directions through a pitching hinge shaft and a rolling hinge shaft arranged perpendicularly crossing each other; the multiple spring damping assemblies are coaxially arranged with the pitching hinge shaft and the rolling hinge shaft respectively, and can provide reverse damping force in the rotation process of the pitching hinge shaft and the rolling hinge shaft; and the multiple motor assemblies are coaxially arranged with the pitching hinge shaft and the rolling hinge shaft correspondingly, reverse driving force is provided during normal work, and rotors of the motor assemblies freely rotate in the mode of being disengaged from a transmission system after power failure. According to the active side lever controller, the problems that the fault risk of an electromechanical assembly is high in the past, and a traditional mechanical backup scheme is complex in structure and large in occupied space can be solved.

The present invention relates to an electric flight control system (5) for controlling an aircraft (1).The flight control system (5) comprises a plurality of functional subsets (95), each having at least one dissimilar primary computer (35) and at least one dissimilar secondary computer (36), at least one functional subset (95) being a simplex / duplex subset (96) comprising at least three identical simplex primary computers (41, 42, 43) and at least one duplex secondary computer (44, 45), each duplex secondary computer (44, 45) of a simplex / duplex subset (96) comprising an independent and synchronized control computing channel (46) and a monitoring computing channel (47), each simplex primary computer (41, 42, 43) of a simplex / duplex subset (96) having a single computing channel, and in that, barring failure, the three primary computers (41, 42, 43) of a subset simplex / duplex (96) form two virtual pseudo-duplex computers. Abbreviation figure: figure 1.

To improve maneuvering easiness when executing a maneuver involving backward movement of a maneuvering object body.SOLUTION: A gyro unit to be mounted on a maneuvering object body maneuvered based on a maneuvering signal received from the outside, the gyro unit includes: a gyro sensor; a calculation part for executing calculation for attitude control of the maneuvering object body based on a maneuvering signal and a detection signal of the gyro sensor, and a control part for executing control such that a control direction of the attitude control is switched between when the maneuvering object body moves forward and backward.SELECTED DRAWING: Figure 3

This invention provides a method for using a weed-removing drone and a flight route information acquisition device for use therein, which can accurately and appropriately acquire the flight route of the weed-removing drone. [Solution] In a method of using a weed-killing drone device equipped with a herbicide liquid application device 20 that can apply herbicide liquid to a target location, the method involves flying the drone along a pre-set flight route, and the pre-acquisition step of flight route information, which uses a satellite positioning system to obtain three-dimensional position information, includes obtaining flight route position information by having a positioning unit 82 having the same or equivalent functions as the positioning unit mounted on the weed-killing drone device use a flight route information acquisition device 80 attached to a long member 81 to sequentially acquire three-dimensional position point information along the flight route, and then inputting the flight route position information to the weed-killing drone device to control it to fly along the flight route.

An unmanned aircraft according to an embodiment is an unmanned aircraft that transports harvested produce that is harvested at a farm, wherein the unmanned aircraft includes: a flight device that causes the unmanned aircraft to fly; a control device that controls operations of the flight device; a communication device that receives package position information indicating a first position of a target package that is an object of transportation, including the harvested produce, and package weight information indicating weight of the target package; and a supporting device that is capable of supporting the target package. The control device judges whether or not the target package can be transported to a second position that differs from the first position on the basis of the package weight information, and in a case of judging that the target package can be transported, controls the flight device to cause the unmanned aircraft to fly to the first position, causes the supporting device to support the target package, and controls the flight device to cause the unmanned aircraft to fly to the second position.

A system comprising an unmanned aerial vehicle (UAV) (100) configured to transition (520) from a terminal homing mode (510) to a target search mode (530), responsive to an uplink signal (451) and / or an autonomous determination of scene change.

A jet aircraft maneuvering characteristic simulation system for a single propeller aircraft includes a power lever, speed brakes, and a controller. The power lever is configured to change a thrust of the single propeller aircraft. The speed brakes are provided on respective right and left sides of the single propeller aircraft. The controller is configured to, in response to an operation of the power lever to raise the thrust of the single propeller aircraft, deploy both the right and the left speed brakes to cause an increase in speed of the single propeller aircraft to be moderate, and control the speed brakes to cause a force in a yaw direction and a force in a roll direction to be generated that act against a turning tendency of the single propeller aircraft by making amounts of the deployment of the right and the left speed brakes different from each other.

Electromechanical drive system (1) to control a transmission shaft (2) connected to the mechanical operating systems of an aircraft, comprising an electric machine (3), a two-way transmission rotation (8) and a clutch assembly (9) wherein the two-way transmission rotation (8) is configured, in any direction of rotation of the transmission shaft (2), to selectively allow the passage of torque either only between the electric machine (3) and the transmission shaft (2) when the torque is supplied by the electric machine (3) to the transmission shaft (2) or between the transmission shaft (2), the clutch assembly (9) and the electric machine (3) when the torque is supplied by the transmission shaft (2) to the electric machine (3).

To allow an operator to undergo training, evaluation, and certification of operating skills more effectively and appropriately.SOLUTION: An information control system available for supporting the training, evaluation, or certification of operating skills of an operator who operates an object to be operated, including a flight vehicle or another mobile body, comprises: an information import part that acquires first video data recorded on the state of the object to be operated that is operated by the operator and also acquires second video data recorded by an operating device on the state of the operation inputted by the operator; an integrated data generation part that generates or records integrated video data obtained by integrating the first and second video data; and a display output part that outputs the integrated video data during or after operation of the object to be operated.SELECTED DRAWING: Figure 1

The present disclosure relates to a an aircraft assistance system measuring a wind speed and direction in a vicinity of an aerodrome (10) and calculating a wind speed and direction in a path (112), along which the aircraft (100) approaches or departs, and predict wind data representing a wind speed and direction in the path (112) for a predetermined future time period. The present disclosure further relates to an aircraft that receives the predicted wind data transmitted by the aircraft assistance system and determines the predicted wind speed and direction along the path (112), and displays a visualisation about the predicted wind speed and direction or provides an autopilot system adapting a flight path accordingly.

A control device (60) controls a flight of an eVTOL including a rotary wing (13) which is driven by a driving device (15) to generate a rotational lift, a fixed wing which generates a gliding lift, and a lift adjustment mechanism which adjusts the gliding lift. The control device (60) includes a rotary wing control unit (621) which adjusts the rotational lift by controlling driving of the rotary wing (13), and a fixed wing control unit (622) which adjusts the gliding lift by controlling driving of the lift adjustment mechanism. When an abnormality of the driving device (15) is predicted or detected in a flight time of an electric flight vehicle, the rotary wing control unit (621) and the fixed wing control unit (622) perform lift adjustment control such that the rotary wing control unit reduces the rotational lift and the fixed wing control unit increases the gliding lift.