28 results about "Flight controller" patented technology

The application discloses a kind of unmanned aerial vehicle direct transmission and mobile network power management and optimization method based on Stackelberg game theory, in the scene researched in the application, unmanned aerial vehicle has the module of data transmission by mobile network and the data transmission module between unmanned aerial vehicle and flight controller direct transmission simultaneously.Unmanned aerial vehicle has mobile network and direct transmission link simultaneously to carry out data transmission, so under the condition of limited unmanned aerial vehicle data transmission power, how to effectively allocate power to two kinds of data transmission mode is the problem needing to be solved in unmanned aerial vehicle data backhaul scene.Aiming at the above problem, the application provides a kind of unmanned aerial vehicle direct transmission and mobile network power management and optimization method based on Stackelberg game theory, and the above unmanned aerial vehicle direct transmission and mobile network backhaul link power limited problem is jointly formed into game model.The application aims to provide unique solution, physically in line with the scene of real application and can be effectively applied to engineering practice.

The embodiment of the application discloses a kind of unmanned plane soft fence control methods, obtain personnel state information, environment risk distribution information is generated based on the personnel state information, the time alignment processing is carried out to the environment risk distribution information, to obtain the risk distribution information corresponding to unmanned plane current time;Obtain the current flight state of the unmanned plane, predict the motion state in future period of time of unmanned plane, and determine risk assessment result according to the motion state and the risk distribution information;According to the risk assessment result, the operator control input is constrained and handled, to generate safety control instruction;The safety control instruction is input into the flight controller to execute flight control, and when the risk degree meets preset condition, safety protection strategy is triggered;It can effectively avoid unmanned plane into personnel dense or high-risk area, improve the flight safety and controllability of unmanned plane in complex personnel environment.

This utility model discloses an automatic testing system for flight controllers, relating to the field of unmanned aerial vehicle (UAV) technology. It includes a control unit, a sensor unit, a storage unit, a detection unit, a power supply unit, a display unit, an input unit, and an interface unit. The control power supply includes a master MCU and a slave MCU. The control unit is connected to the sensor unit, storage unit, detection unit, power supply unit, display unit, input unit, and interface unit. The sensor unit includes a compass, a barometer, and an IMU, and is connected to the detection unit. The storage unit contains a TF card. This utility model eliminates the need for additional instruments, reducing the cost of purchasing equipment. Furthermore, only the automatic testing system needs to be learned, reducing the learning difficulty and manual training costs for workers. Simultaneously, the flight controller is connected to the system via a single cable, reducing connection difficulty and shortening testing time from approximately 2 hours to about 10 minutes.

This invention belongs to the field of power diversion, and particularly relates to a diversion power supply method and system for multi-functional emergency lighting UAV systems. The method collects the state of charge of the onboard energy storage device, the real-time power consumption of the flight controller, and the target brightness parameters of the LED lighting. A mode arbitration signal is generated through threshold comparison, corresponding to three power supply modes. A multi-channel power distribution control unit achieves coordinated power management of the three channels, and output feedback enables smooth mode switching and overload protection. This invention significantly improves the stability and response speed of the onboard power supply system, ensures the safety of flight controller power supply, balances charging and lighting needs, and enhances the reliability of UAV emergency operations.

A fiber optic control system for an unmanned aerial vehicle, operating according to a data transmission protocol and comprising a ground-based transmit module and a fiber optic receiver module attached to the unmanned aerial vehicle, both modules being interconnected via a fiber optic cable, wherein the transmit module comprises a fiber optic transmitter, a remote control connected to the fiber optic transmitter via a first interface converter, and video goggles directly connected to the fiber optic transmitter, wherein the fiber optic receiver module comprises a fiber optic receiver and a coil with a fiber optic cable, wherein the fiber optic transmitter is connected to the fiber optic cable via a first connector, the other end of which is connected to the fiber optic receiver via a second connector, the first output of which is connected to the flight controller of the unmanned aerial vehicle via a second interface converter.while the second output is directly connected to the video transmission point of the unmanned aerial vehicle via the flight controller, characterized in that hardware interface converters RS485↔TTL are used.

This invention relates to a retractable arm and control method for a multi-rotor unmanned aerial vehicle (UAV), belonging to the field of UAV technology. It includes a fixed arm, a movable arm, a telescopic drive mechanism, a length monitoring device, a vibration sensor, and a piezoelectric actuator. The fixed arm has an external guide groove; the movable arm is fitted over the fixed arm, with an inner wall slider engaging the guide groove, allowing non-axial loads to be transmitted to the fuselage via the slider and guide groove, achieving separation of drive and load-bearing. The telescopic drive mechanism uses a self-locking screw-nut transmission mechanism, allowing for stepless continuous adjustment and self-locking upon power failure. A length monitoring device provides feedback on the arm length to the flight controller, forming a closed-loop control of the arm length configuration. The vibration sensor monitors fuselage vibration, and the flight controller controls fuselage vibration through primary vibration suppression of the rotor and piezoelectric actuator, and secondary vibration suppression through fine-tuning of the movable arm length. This invention solves the problems of easy wear, inability to achieve stepless continuous adjustment, and lack of active vibration damping in existing telescopic arm drive mechanisms, improving flight stability and reliability.

Techniques for controlling the operation of a component of an aircraft, such as an inverter used to provide electric energy to the aircraft's motor or an actuator used to control positioning of a control surface (e.g., an aileron, an elevator, a rudder, and / or the like) of the aircraft. In example embodiments, a command processor receives a first command pilot signal generated by a first flight controller component from the first flight controller component. The command processor receives a second command pilot signal generated by a second flight controller component from another command processor. The command processor may determine a consolidated command signal based on the two command signals. The command processor may control the operation of the component of the aircraft based on the consolidated command signal.

This invention provides a decoupled control system and method for independent drive of multiple range extenders in a multi-rotor unmanned aerial vehicle (UAV). The system includes: decoupling the motor throttle commands of the flight controller into independent power commands for each range extender's power generation unit by introducing a power management coordinator; separating the flight control loop from the power generation control loop, thus achieving hierarchical decoupling of flight control and power generation control. Simultaneously, by independently optimizing the design of the flight controller and the range extender's power generation unit, this invention can directly utilize commercially available low-power range extender modules, reducing the development risk and cost of high-power customized range extenders and simplifying flight control logic; furthermore, by limiting load disturbances within each power group and preventing global diffusion, flight stability can be improved. In addition, by grouping the rotors of the multi-rotor UAV, with each power group independently powered by a dedicated range extender's power generation unit and electrically isolated between power groups, this invention can alleviate the current sharing problem of parallel range extenders.

This application provides an aircraft structure control coupling test system, relating to the field of aircraft. Specifically, the system includes a control device and a vibration acquisition device mounted on the aircraft's airframe structure. The control device is connected to the aircraft's flight controller and is responsible for configuring the required frequency sweep range for the test. The flight controller generates an excitation signal based on the set frequency sweep range and transmits it to at least one actuator to excite the aircraft's airframe structure. The aircraft's inertial navigation system and vibration acquisition device work together to collect vibration information of the aircraft's airframe structure during the execution process. The control device analyzes the collected vibration information and determines whether the coupling test passes. This design improves the versatility of the test system, enabling it to adapt to the needs of different types and scales of aircraft structure control coupling tests.

The invention is an ejectable aerial power supply (10), an unmanned aerial vehicle system based thereon, and an operating method for the system. The aerial power supply (10) comprises a tether connecting unit (11), DC / DC converters (15, 25) for supplying energy from a connected tether (50) for on-board flight controller systems (41, 42) of an UAV (40), and a power control unit (20). The aerial power supply (10) further comprises an ejecting mechanism (30) that can be activated depending on energizing and charging conditions, and a descender device (31) that can be deployed after the aerial power supply (10) is separated from the UAV (40)

This invention relates to the interdisciplinary field of intelligent unmanned systems and computer vision, specifically disclosing a method for autonomous detection and tracking of Indo-Pacific humpback dolphins using UAV-borne vision. The method includes the following steps: S1, constructing an image database of Indo-Pacific humpback dolphins in a real-world environment; S2, training a high-precision Indo-Pacific humpback dolphin detection model, and lightweighting the model using structured pruning techniques; S3, inputting real-time airborne images into the detection model to obtain target detection box information, constructing visual servo feature vectors, and using a Kalman filter algorithm to optimally estimate the features and calculate the real-time deviation of the visual servo; S4, using a PID control algorithm to calculate the UAV's three-dimensional speed control commands and drive the flight controller to execute corresponding maneuvers. This invention's method for autonomous detection and tracking of Indo-Pacific humpback dolphins using UAV-borne vision enables real-time autonomous tracking and monitoring of Indo-Pacific humpback dolphins by UAVs.

This invention discloses an autonomous flight control method for unmanned aerial vehicles (UAVs) based on multi-sensor fusion and AI decision-making, relating to the field of UAV control technology. The method includes: acquiring multimodal physical detection data of the UAV in its flight environment to generate a three-dimensional spatial airflow distribution matrix; constructing a multi-dimensional state space set; outputting a reference trajectory coordinate set and a high-frequency rotor compensation bias for the reference trajectory coordinate set through the dual-path action space of the strategy decision network; acquiring high-frequency vibration spectrum data of the UAV body; determining action triggering conditions based on the high-frequency vibration spectrum data; and using the reference trajectory coordinate set and the high-frequency rotor compensation bias to perform physical attitude correction on the UAV's underlying flight controller based on the triggering conditions, thereby controlling the UAV to perform obstacle avoidance flight. This invention improves the safety and stability of autonomous flight of UAVs in complex dynamic environments.

The invention discloses a rocket take-off method, system and device and a medium, and relates to the technical field of spacecraft navigation, and the method comprises the steps: when a take-off contact signal is received, a rocket takes off; when the take-off contact signal is not received, inertial unit gyroscope information of the rocket is obtained; calculating an x-axis angle increment accumulated value, a y-axis angle increment accumulated value and a z-axis angle increment accumulated value of the gyroscope according to the inertial measurement unit gyroscope information; if any one of the x-axis angle increment accumulated value, the y-axis angle increment accumulated value and the z-axis angle increment accumulated value is higher than the corresponding angle increment accumulated threshold value, the rocket is controlled to take off, and otherwise, the rocket is controlled not to take off. After the rocket takes off, the attitude change response of the rocket body is fast, the precision of the zero point of the take-off time is improved, and the adopted algorithm is simple, reliable and easy to implement on a flight control machine.

This utility model relates to the field of unmanned aerial vehicle (UAV) technology, and more particularly to an impact-resistant UAV, comprising a body structure and core components. The body structure includes a spherical outer frame and multiple body supports, which are located within the spherical outer frame and connected to it via connectors. The multiple body supports are interconnected and form a ring structure. The core components include a lidar, a battery, a flight controller, and multiple propellers. The propellers are respectively mounted on corresponding body supports. The flight controller is fixed in the center of the ring structure formed by the multiple body supports. The battery is fixed on the flight controller, and a radar support is fixed above the battery. The lidar is mounted on the radar support. The UAV provided by this utility model is less prone to collisions with objects in extreme operating environments. When a collision does occur, it exhibits strong impact resistance, and its core components are not easily damaged.

This invention discloses a tethered unmanned aerial vehicle (UAV) airport system and its control method that automatically switches between tethered and free flight. The system includes an airport housing, an automatic cable reel assembly, an automatic cable disconnection and docking assembly, and an adaptable UAV. The airport housing integrates an automatic hatch, a liftable platform, a storage cavity, and charging and vehicle-mounted power supply interfaces. Both the hatch and platform are driven by stepper motors. The docking assembly is located inside the platform's conical cylinder, and the UAV has a pairing and locking mechanism and deformable landing gear, adaptable to fixed-point docking and ground landing. The system is linked by a PLC to various modules and the UAV flight controller, supporting vehicle-mounted manual / automatic control. The winch is powered by 400-900V DC output via AC-DC, and the onboard DC-DC converter provides battery charging. The PLC adjusts the cable reel speed based on tension sensor signals to stabilize tension. This invention significantly improves the scenario adaptability and operational efficiency of tethered UAV systems, meeting the engineering application requirements of various low-altitude operation scenarios.

A system for flight control of an electric aircraft includes a flight controller configured to provide an initial vehicle torque signal including a plurality of attitude commands. The system includes a mixer configured to receive the initial vehicle torque signal and a vehicle torque limit, receive an airspeed-based RPM limit, determine a plurality of modified attitude commands as a function of the vehicle torque limit, the attitude commands, and the airspeed-based RPM limit, generate, as a function of modified attitude commands, an output torque command including the initial vehicle torque signal adjusted as a function of the vehicle torque limit, generate, as a function of the output torque command, a remaining vehicle torque. The system includes a display, wherein the display is configured to present, to a user, the remaining vehicle torque and the output torque command.

A system for flight control in electric aircraft includes a flight controller configured to provide an initial vehicle torque signal including a plurality of attitude commands. The system includes a mixer configured to receive the initial vehicle torque signal and a vehicle torque limit, receive an airspeed-based RPM limit, determine a plurality of modified attitude commands as a function of the vehicle torque limit, the attitude commands, and the airspeed-based RPM limit, generate, as a function of modified attitude commands, an output torque command including the initial vehicle torque signal adjusted as a function of the vehicle torque limit, generate, as a function of the output torque command, a remaining vehicle torque. The system includes a display, wherein the display is configured to present, to a user, the remaining vehicle torque and the output torque command.

Methods and apparatus to create and perform drone displays are disclosed. An example drone display may include a first set of drones having a first drone type, and a second set of drones having a second drone type. A flight controller at each drone may provide commands to drone hardware through an abstraction layer, where the commands from the flight controller are common across different drone types and the abstraction layer translates the commands to drone-specific signals based on a configured drone type. A central management system may provide flight paths to the different sets of drones in a common format across different drone types, and may control multiple different types of drones using the common format.

This invention belongs to the field of aerospace technology and relates to a reusable rocket system and control method. The first-stage rocket sequentially comprises a first-stage ducted fan compartment, a first-stage air chamber, a first-stage electronic control compartment, a first-stage battery compartment, and a first-stage engine assembly. The first-stage rocket also contains a first-stage stabilizing fin assembly, a first-stage ducted fan, a first-stage battery, and a control module; the control module is connected to the first-stage stabilizing fin assembly. The second-stage rocket sequentially comprises a fairing, a second-stage battery compartment, a second-stage electronic control compartment, and a second-stage propulsion compartment. The second-stage rocket also contains a second-stage battery, a second-stage electronic speed controller (ESC), a second-stage receiver, a second-stage flight controller, a second-stage ducted fan, and a second-stage engine assembly. The ESC is connected to the second-stage ducted fan, and the flight controller is connected to the second-stage propulsion assembly. The above system and control method achieve automatic separation and recovery of the rocket system.

This invention discloses a bird-like aircraft with adjustable wing lift, comprising a fuselage, a flight controller, a tail fin, and at least one pair of wings. Each wing includes a wingplate and several damper flaps. The wingplates have several air intakes, and the damper flaps are rotatably mounted on the air intakes via pivots. The invention also includes a first drive mechanism for driving the wingplates to swing and simultaneously driving the damper flaps to rotate and open / close. The tail fin is either a first tail fin or a second tail fin. The first tail fin is connected to a second drive mechanism that drives its rotation and extension / retraction to deploy / retract. The second tail fin is connected to a third drive mechanism that drives its rotation and swing. The second or third drive mechanism is mounted on the fuselage and operates through the flight controller. This invention, through wing swing and damper opening / closing control, combined with the adjustment of the multi-functional tail fin, significantly improves the aerodynamic efficiency and attitude control precision of the aircraft, achieving multiple flight modes such as vertical takeoff and landing, hovering, forward flight, roll, yaw, and gliding.

The application relates to a compact flight controller, a first circuit board, a second circuit board and a third circuit board of which are sequentially and parallelly arranged on one side of a base; a power interface and a first communication port are arranged on the side of the base opposite to the first circuit board; the first circuit board comprises a first board body, a second communication port and a processor, a first accommodating portion is arranged between the first board body and the base, and the second communication port is located in the first accommodating portion; the second circuit board comprises a second board body and a plurality of third communication ports, a second accommodating portion for accommodating the processor is arranged between the second board body and the first board body; the third circuit board comprises a third board body and a plurality of fourth communication ports, a third accommodating portion for accommodating the plurality of third communication ports is arranged between the third board body and the second board body; the plurality of fourth communication ports are arranged on the side of the third board body opposite to the second board body; and the processor is connected with the first communication port, the second communication port, the third communication port and the fourth communication port.

This invention relates to the field of unmanned aerial vehicle (UAV) technology, specifically disclosing a four-way traction-type UAV takeoff assistance device to improve the takeoff stability and safety of UAVs under conditions of high turbulent airflow and continuous water spray interference within a well shaft. The device includes UAV body components, a universal pulley assembly below the UAV's center of gravity, four traction ropes, ground pulleys at the four corners of the takeoff platform, four cable reeling / releasing drive mechanisms, a tension sensor, a rotary encoder, a flight controller, and a synchronization control module. This invention adaptively updates high and medium disturbance thresholds by statically calibrating initial thresholds and using real-time monitoring of wind speed shear coefficients, peak wind speeds, and water spray intensity. After iterative optimization through residual feedback, it combines LSTM residual cascade decoding under high disturbance levels, MLP nonlinear mapping decoding under medium disturbance levels, and sliding window linear interpolation decoding strategies under low disturbance levels to generate a driving voltage signal for adjusting the damping loop. This process iterates until the flight controller terminates the traction.

The application discloses a method and system for integrating communication and sensing of an unmanned aerial vehicle (UAV) based on dynamic subcarrier allocation, which comprises the following steps: generating communication bits, convolutionally encoding and interleaving the communication bits to obtain flight control instructions and corresponding instruction serial numbers; dynamically allocating sensing subcarrier positions and communication subcarrier positions of a current frame according to instruction serial numbers of the current frame, and setting a guard interval between the two types of subcarriers; OCDM modulating the subcarrier sequence after the allocation to generate an OCDM integrated communication and sensing signal and transmitting the signal; receiving the OCDM integrated communication and sensing signal, OCDM demodulating the signal, separating out the communication subcarriers to restore the flight control instructions, and outputting the flight control instructions to a flight controller through a UART protocol. The application improves the coexistence ability and system reliability of the integrated communication and sensing signal in a complex electromagnetic environment.

Fig 1 A multirotor UAV 10 flies under control of an on-board flight controller(40, fig 2). The UAV 10 has sensors e.g. laser scanner / LIDAR 30, camera 32, GPS 34, compass 35 sending signals to the flight controller (40, fig 2). The UAV 10 uses the three-dimensional depth scanner 30 when flying in close proximity to an external structure (60, fig 4) to create a three-dimensional map of the external structure (60, fig 4) for control of the flight of the UAV 10 proximate thereto. The sensors detect a profile of the structure (60, fig 4) within a predetermined vicinity of the UAV 10 and is used by the flight controller (40, fig 2) to control movement of the UAV 10 to track the profile of the structure (60, fig 4).

An aircraft fly-by-wire flight control system comprises a flight controller, a control stick, a first elevator actuator, a second elevator actuator and an ultimate backup controller, the ultimate backup controller being connected to the control stick, the flight controller, a flap control computer, an ultimate backup start switch and the second elevator actuator, the flight controller comprising a first command calculation module, the ultimate backup controller comprising a second command calculation module and an ultimate backup switching module, the first elevator actuator being controlled by the first command calculation module of the flight controller, the second elevator actuator being controlled by the ultimate backup switching module of the ultimate backup controller, the ultimate backup switching module being controlled by the ultimate backup start switch, and the first command calculation module and the second command calculation module being switched by the ultimate backup switching module.

The present application relates to the technical field of unmanned aerial vehicle control, and particularly relates to a dynamic hovering anti-disturbance control method for unmanned aerial vehicles based on a neural network, comprising: constructing a time series convolution network as a disturbance observer to estimate total disturbance according to unmanned aerial vehicle state quantities and wind speed measurement values within a historical time window; constructing a deep deterministic policy gradient network as a controller to generate motor speed instructions according to state errors and total disturbance; jointly training the two networks through domain randomization in a simulation environment; deploying the trained networks to a flight controller, estimating total disturbance by the time series convolution network and generating speed instructions by the deep deterministic policy gradient network to drive the motor in real-time flight; and setting a safety constraint layer to perform amplitude limiting on the speed instructions or switch to a backup controller when state parameters exceed a threshold. The present application realizes high-precision hovering control under strong wind disturbance and guarantees safety and real-time performance.

This utility model provides a simple flight control leveling device, including a support base, a fine-tuning slide, and a test box. The support base is used to fix the device on the ground or platform. The fine-tuning slide is disposed on the support base and includes several sets of adjustment mechanisms and a slide top plate. The adjustment mechanisms are used to adjust the slide top plate to a horizontal position. The test box is placed on the slide top plate and has a receiving cavity for holding the UAV flight controller. A notch is provided on one side of the test box for the UAV flight controller cable to pass through. Compared with the prior art, this device is simple and low-cost for leveling UAV flight controllers and can quickly calibrate UAV sub-controllers, thereby improving the production efficiency of UAV flight controllers.