16results about How to "Improve flight safety" patented technology

This invention provides an active flow control method and system based on intelligent algorithms. The method includes: determining the number of inlet parameter sets for a typical flight state point, constrained by simulation economy and sampling efficiency; performing numerical simulations according to the number of inlet parameter sets to obtain dataset 1, with inlet parameters as independent variables and flow field characteristics as dependent variables; obtaining dataset 2, with flight state as independent variables and flow field characteristics as dependent variables, through numerical simulation for a certain set of inlet parameters; constructing a proxy model of inlet flow field characteristics for a typical flight state point using deep learning based on dataset 1; constructing a proxy model of inlet flow field characteristics for a wide-speed-domain flight state based on the proxy model of inlet flow field characteristics for the flight state point, using a transfer learning algorithm and dataset 2; constructing an environment-agent interaction model based on a deep reinforcement learning algorithm, using the proxy model of inlet flow field characteristics for a wide-speed-domain flight state as the environment model for deep reinforcement learning; setting optimization termination conditions based on the environment-agent interaction model, and obtaining a control sequence with continuously optimal inlet performance under different flight states through deep reinforcement learning. This invention can stably adapt to flight scenarios with a wide speed range and a large airspace, and achieve real-time optimal control of the air intake flow field under a wide speed range, solving the problem of poor generalization ability of traditional methods under different operating conditions.

The application relates to a force couple balance and longitudinal array push-pull vertical take-off and landing high-speed aircraft, belonging to the technical field of aircrafts, which comprises a fuselage, a rotor, a fixed wing, a steering controller and a propeller. The rotor is installed at the top of the middle part of the fuselage through a rotor shaft, and a clutch is arranged between the rotor and a power system and / or a transmission system matched with the fuselage, so as to be controlled to be disconnected or to transmit power to the rotor. The steering controller comprises a fixed base and a rotating base, and each of the nose and the tail has a set of the rotating base. The propeller is provided with two propellers which are respectively installed on the rotating bases of the nose and the tail, and are controlled to rotate with the rotating bases relative to the fixed base. The force couple formed by the front and rear thrust vectors is used to balance the reverse torque brought by the rotor. When the propeller is coaxial with the middle axis of the fuselage, the wind area of the single propeller obtains double thrust. The application can improve the energy utilization rate, improve the carrying capacity, improve the flight safety performance and obtain a longer hovering time.

A method for planning an autonomous landing safe trajectory suitable for UAV inspection is proposed. After the UAV takes off, it acquires the current pose of the UAV, the point cloud map information of the surrounding environment, and the spatial orientation of the target point. By establishing the spatial transformation relationship between the camera coordinate system and the body coordinate system, the orientation vector relative to the ground target is calculated, and the target point is generated within the radar-sensible area. Based on the generated target point, an optimization function that minimizes the fourth derivative is constructed based on multiple high-order polynomials to generate a smooth trajectory with continuous position, velocity, and acceleration. The initial trajectory is transformed into a B-spline curve, and local trajectory segments with collision risk are optimized. A segmented penalty mechanism is designed based on the boundary threshold to guide the trajectory away from the boundary area. The time span is adjusted by calculating the trajectory derivative over-limit ratio, and a trajectory similarity cost function is introduced to ensure that the final optimized trajectory maintains the original geometric structure, thereby achieving trajectory control optimization and safe landing of the UAV.

The application discloses a kind of barometric altitude dynamic correction method based on airborne data.First, the sliding window parameters are screened using recursive feature elimination method, and then the sliding window is initialized and updated;Clean the sliding window data, first determine whether the sliding window data is null, then correct;For the data fusion multiple methods to detect outliers and correct after completing null judgment and correction;Construct the LSTM model and optimize the sliding window size, select the window size of the best performance indicator, use the LSTM model to correct the barometric altitude dynamically.This method has the characteristics of high precision, strong real-time, etc., improves the deficiency that the existing method can only correct the barometric altitude at a specific location, realizes the dynamic correction of barometric altitude in the whole approach process, improves the obstacle safety under low temperature conditions, at the same time, has the ability to correct the barometric altitude under high temperature conditions, and can be widely used in flight operation using barometric vertical navigation program.

This invention relates to the field of motor technology and discloses a high-power-density permanent magnet motor for unmanned aerial vehicles (UAVs). The motor includes a stator with a winding section and a frequency conversion section. The winding section is arranged in a ring array around the center of the stator, allowing for different coil combinations on a single winding. The winding section includes slots A, B, and C. Slot A is located on the inner wall of the stator, while slots B and C are located on the stator itself. The inner wall of the stator also has inlet holes A, B, and C. Inlet holes A and B communicate with slot A, and inlet holes B and B communicate with slot B. The motor employs a wide-range speed control to adapt to UAV operating conditions, featuring a six-speed adjustment function. The rated speed ranges from 8 r / min (8 Hz) to 48 r / min (48 Hz), and the speed ratio can reach 1:8 during weak field operation. This allows for precise matching of the power requirements of different stages of UAV operation, such as takeoff, cruise, and high-speed flight, achieving full operating condition coverage without motor replacement.

The invention discloses a flying robot and an unhooking system of the flying robot, the flying robot is connected with an unpowered aircraft through a traction piece and used for pulling the unpowered aircraft to rise through the traction piece, and the unhooking system comprises a controller, a receiver, a steering engine, a support, an opening and closing mechanism and a navigation module; the controller is connected with the receiver, the steering engine and the navigation module, the support is fixed to the flying robot, and the steering engine and the opening and closing mechanism are arranged on the support; the controller receives a preset remote control instruction from the receiver, the controller receives real-time data from the navigation module, the controller is used for generating an unhooking instruction based on the remote control instruction or the real-time data, and the steering engine controls the opening and closing mechanism to be opened based on the unhooking instruction, so that the traction piece is separated from the opening and closing mechanism. The unhooking instruction is generated through the controller based on the remote control instruction or the real-time data, the steering engine controls the opening and closing mechanism to be opened based on the unhooking instruction, rapid separation of the traction piece and the opening and closing mechanism is achieved, and the flight safety of the unpowered aircraft is improved.

This invention discloses a tilt-lift short takeoff and landing (STOVL) aircraft and its control method, comprising a fuselage, wing assembly, multi-layered distributed propulsion system, tilt drive assembly, and control unit. The wing is hinged to the fuselage via a pivot in the mid-rear section of the chord, and the tilt drive assembly drives the wing to rotate and adjust the angle of attack. The multi-layered distributed propulsion system includes a first rotor assembly located in the mid-rear section to the wingtip region of the wing and a second rotor assembly located on the lower surface of the wing near the fuselage. During cruise, the first rotor assembly is stopped and feathered, and the propulsion system tilts synchronously with the wing. This invention, through a layered distributed propulsion layout and synchronous wing tilting for synergistic lift enhancement, solves the problems of insufficient control torque at low speeds and high cruise energy consumption, achieving a balance between STOVL performance and cruise economy.

The utility model discloses a telescopic battery support belongs to unmanned aerial vehicle battery technical field, including carbon plate, adjusting support and bandage, carbon plate is used for placing battery group, and the top of carbon plate is opened and is equipped with a plurality of bandage holes, and adjusting support is installed at the top of carbon plate, and adjusting support is used for limiting battery group, and bandage is arranged in the bandage hole, and bandage is used for fixing battery group. The problem of battery group displacement and the flexibility of unmanned aerial vehicle being limited due to the bandage being easy to loosen or even break during flight and the existing fixing mode being difficult to adapt to batteries of different sizes or models in the prior art is solved. The utility model discloses through setting adjusting support, and the synergies with bandage, ensure that battery group does not loosen due to vibration or external force in the flight process, improves flight safety, can adapt to battery group of different sizes, greatly reduces the installation and adjustment time, and enhances the flexibility.

This invention discloses a UAV contouring flight system and method based on multi-sensor fusion and adaptive planning. The system includes a multi-sensor module for simultaneously acquiring 3D point cloud data, image data, and UAV inertial measurement data of the environment; a localization and mapping module for processing the acquired data through a tightly coupled fusion algorithm to output the UAV's real-time pose and a 3D map of the environment; an adaptive path planning module for identifying target objects based on the 3D environmental map and adaptively selecting and executing a matching path generation strategy to generate a contouring flight path that conforms to the target object's surface; and a flight control module for controlling the UAV according to the contouring flight path. This invention solves the problems of low positioning accuracy, inaccurate environmental modeling, and inability to generate high-precision 3D contouring paths for UAVs in environments lacking GPS signals, achieving efficient contouring for regular targets and high-precision contouring flight for complex targets.

The application belongs to the technical field of unmanned aerial vehicle path planning, and discloses an unmanned aerial vehicle path planning method and device, an electronic device and a storage medium, the method comprising: acquiring electromagnetic induction information of an unmanned aerial vehicle in a preset range, inputting the electromagnetic induction information into a preset multi-dimensional electromagnetic radiation cost model, calculating an electromagnetic radiation cost of the unmanned aerial vehicle in the preset range, based on the electromagnetic radiation cost, using a preset cost update rule to plan a flight path for the unmanned aerial vehicle, and obtaining an optimal flight path of the unmanned aerial vehicle in the preset range; through the above method, the flight safety of the unmanned aerial vehicle in a complex electromagnetic environment is improved.

This invention relates to the field of fuel cell technology and discloses a fuel cell heat dissipation system and control method for active balancing heat dissipation in unmanned aerial vehicles (UAVs). The fuel cell heat dissipation system includes a UAV heat dissipation assembly and an active balancing control subsystem. The UAV heat dissipation assembly includes a liquid cooling circuit and rotors disposed at the tips of multiple heat dissipation arms. The liquid cooling circuit includes coolant channels disposed inside the multiple heat dissipation arms. The coolant channels include in-arm liquid inflow pipes and in-arm liquid return pipes. Multiple in-arm liquid inflow pipes are arranged close to the inner side of the heat dissipation arms, and the multiple inflow pipes converge at the tips of the heat dissipation arms and connect to the in-arm liquid return pipes. The inflow pipes have an S-shaped variable diameter pipe structure, and their arrangement density gradually decreases from the root to the tip of the heat dissipation arm. The active balancing control subsystem includes a sensor group, an actuator group, and a controller. This invention can improve the reliability and flight safety of the UAV thermal management system.

This invention discloses an adaptive terrain-following flight control method and system for railway unmanned aerial vehicles (UAVs) that integrates multi-source terrain data and a data-driven model. The method utilizes an extended Kalman filter to estimate the change in rotational inertia online, dynamically correcting a preset initial dynamic model to obtain a dynamic baseline model. Simultaneously, it integrates multi-source terrain data to generate a terrain-following flight reference altitude surface that considers the track's geometric characteristics, using the track centerline as a constraint. Vertical and horizontal trajectories are planned based on the surface curvature, and dynamic yaw angles are calculated. A Gaussian process-enhanced prediction model is constructed, incorporating aerodynamic parameter perturbation learning and L1 adaptive laws into the nonlinear model predictive controller. An inner and outer loop cascaded architecture is used to solve for total lift and three-axis torque control quantities. Flight is driven by a pseudo-inverse assignment matrix mapped to rotor speed commands, and a safe distance is monitored in real time to trigger replanning. This method solves the problems of model mismatch and environmental adaptation in complex environments, improving flight safety and trajectory tracking accuracy.

This invention relates to the field of airborne geophysical exploration, and more particularly to an intelligent monitoring and predictive guidance method for helicopter-towed pods. This method involves arranging multiple GPS arrays on the flexible structure of the pod, fusing airborne GPS, radar altimeter, attitude sensor, video, and meteorological data to construct a pod oscillation model incorporating structural modes and identifying deformation parameters online. A multi-model adaptive fusion framework is established, employing extended Kalman filtering and a Bayesian weight update mechanism to achieve state estimation. The spatial wind field gradient is inverted and injected into the forced pendulum dynamics equation to predict the trajectory, calculating the ground contact risk index to trigger graded alarms. Pilot cognitive load is assessed based on eye-tracking and joystick spectral analysis, dynamically simplifying the guidance interface. Lateral / longitudinal oscillation patterns are identified in the body coordinate system, generating differentiated control commands. This invention achieves intelligent monitoring and predictive guidance of the pod's state, improving flight safety and data quality.

This invention provides a UAV (Unmanned Aerial Vehicle) line inspection path planning system and method based on UAV nests, belonging to the field of UAV control system technology. It includes a UAV nest layout module, which automatically optimizes nest placement using a Markov model and Actor-Critic network combined with particle swarm optimization algorithm; a path planning module, employing a two-stage hybrid algorithm based on deep reinforcement learning, using a pointer network to generate the order in which UAVs visit inspection points, and then embedding a heuristic search algorithm to search for the shortest feasible flight path; an environment modeling module, used to construct a 3D environment model of the inspection area and perform GIS rasterization processing; and a task allocation module, which rationally allocates inspection tasks based on UAV performance, task requirements, and environmental information. This invention, using the above-mentioned UAV line inspection path planning system and method based on UAV nests, effectively solves problems such as limited UAV endurance and poor environmental adaptability.

This invention discloses a method for UAV access capacity in the 1090 MHz band based on variable channels and mobility prediction. It introduces S-mode and A / C-mode messages in the real-world 1090 MHz band; and allows for the setting of corresponding channel propagation models according to different environments. All aircraft are modeled as mobile devices; and the ADS-B message update cycle can be adjusted according to the UAV's speed. Finally, the continuous packet loss situation and corresponding packet loss rate of civil aircraft and UAVs can be obtained. Under the condition of meeting the minimum message update rate of civil aircraft, i.e., maintaining the normal operation of the civil aviation surveillance system, the method analyzes how many UAVs equipped with ADS-B OUT devices can be added to this frequency band.

This invention discloses a safe and energy-saving trajectory solution method for UAVs based on vertically polarized antennas, integrating communication and control. First, a high-precision communication constraint model with attitude perception is established, revealing the antenna gain attenuation mechanism caused by lateral maneuvers. Then, using rigid body dynamics principles, the antenna pointing direction and acceleration vector are explicitly coupled. By introducing intermediate variables and dynamic decoupling projection techniques, the roll and pitch constraints, originally non-convex in Euler angle space, are accurately transformed into second-order cone constraints and linear polyhedral cone constraints in acceleration space, respectively. Finally, a second-order cone programming model with the goal of minimizing mechanical energy consumption is constructed and iteratively solved using a sequential convex approximation algorithm. This invention minimizes the mechanical energy consumption of UAVs during high-maneuverability flight while automatically avoiding antenna communication blind spots, solving the problem of difficult traditional non-convex optimization solutions. It is suitable for UAV application scenarios with high requirements for communication reliability and real-time performance.