262 results about "Level flight" patented technology

The invention discloses a decision-making method and decision-making system for low-power autonomous landing based on a vertical take-off and landing unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicle landing decision-making. Comprising the following steps: acquiring topographic point cloud data, establishing a neural network model, and extracting and predicting topographic feature parameters including obstacle density and maximum height; calculating an obstruction influence index and a vertical energy consumption influence index in combination with cruise area point cloud data and real-time environment parameters including environment temperature, wind speed and the like, and correcting a return electric quantity threshold value; dynamically correcting the return electric quantity threshold value by further combining the health parameters of the battery, including storage time, cycle charging times and environment temperature; and comparing the dynamic homeward voyage electric quantity threshold with the real-time electric quantity, and generating a landing or homeward voyage decision instruction. The horizontal flight and vertical take-off and landing energy consumption of the unmanned aerial vehicle under different topographic conditions is comprehensively considered, and correction is performed in combination with the battery performance, so that the electric quantity management strategy of the unmanned aerial vehicle is more intelligent and precise.

The invention relates to a fighter bottom layer flight control method based on deep reinforcement learning. The method comprises the following steps: S1, designing a target updating mode and a termination condition function of flight control according to a simulation environment; s2, constructing a state space, an action space and a reward function controlled by the fighter according to the simulation environment; s3, building a deep neural network model based on a PPO algorithm; and S4, training a fighter bottom layer flight control model based on a PPO algorithm. According to the control method disclosed by the invention, the intelligent agent only needs to concentrate on advanced task planning when completing high-level task decisions such as battle and tracking, so that the training of basic decisions for bottom-layer aircraft control is reduced, the algorithm is easier to converge, and the learning cost is reduced.

The utility model relates to a cross-medium aircraft convenient for adjusting flight attitude, which comprises a water-drop-shaped centrosymmetric aircraft body with an aircraft head and an aircraft body, and the aircraft head of the aircraft body is positioned on the front side of the aircraft body. The aircraft body is further provided with an underwater power mechanism used for providing underwater flight power and an air power mechanism used for providing air flight power, the side portion of the aircraft body is connected with four or six fixed wings, slip-flow rudders controlled to rotate are arranged on the rear edges of the fixed wings, and the rotating axes of the slip-flow rudders are parallel to the wing faces of the fixed wings and perpendicular to the long axis of the aircraft body. Each fixed wing is provided with a slipstream rudder, so that the cross-medium aircraft can be conveniently controlled to pitch, roll, yaw and other actions, and the cross-medium aircraft can be conveniently switched between a hovering flight attitude and a level flight attitude.

The invention discloses an automatic control method of a four-power-source tiltable aircraft, relates to the technical field of flight control of tiltable aircrafts, is realized based on a PX4 flight control system, and is suitable for a tiltable aircraft provided with four independent tiltable power sources and corresponding tilting execution mechanisms. According to the method, through configuration of a tilting angle control module, a power distribution module and a full-stage flight logic scheduling module, full-stage automatic control of vertical take-off and landing, suspension, horizontal take-off, fixed-point horizontal flight, automatic cruise, one-key return flight, fixed-angle flight, power source fault handling and the like is achieved. Smooth transition of all flight modes is achieved, the stability of the attitude, the height and the position of the tiltable aircraft in different flight stages is maintained, meanwhile, the functions of automatic obstacle avoidance, fault emergency and the like are integrated, flight safety is guaranteed, flight stability and applicability are improved, and the method can be widely applied to various tiltable aircraft operation scenes.

The invention belongs to the field of aircraft design and control, and particularly relates to a control method of a combined type unmanned aerial vehicle based on passive hinge tilting. The composite unmanned aerial vehicle carries a tilting device and a fixed wing, the tilting of the tilting device is controlled by differential speed of motors at the two ends of the tilting device, and vertical take-off and landing and tilting transition of the unmanned aerial vehicle are controlled by adopting a PID control law. The main control board controls the main power motor and provides main power for the vertical take-off and landing stage and the horizontal cruise stage of the unmanned aerial vehicle. The sub-control board controls tilting motors at the two ends of the tilting device and provides power for enabling the tilting device to tilt. When the unmanned aerial vehicle takes off and lands, the tilting device is in a locked state, and after the unmanned aerial vehicle reaches a cruise height, the unmanned aerial vehicle is controlled to fly horizontally through the tilting device to complete a cruise task; and after the cruise is finished, the unmanned aerial vehicle is controlled to enter a hovering state through the tilting device. According to the invention, decoupling of forward flight and pitch angle attitude is realized, multiple purposes are realized, and flight tasks can be completed in a complex environment.

The invention discloses an airborne low-detectability photoelectric long-distance stable tracking and aiming method based on a time-sensitive opposite target, and belongs to the technical field of airborne photoelectric detection and target tracking. The method comprises the following steps: step 1, target detection and miss distance calculation: in a level flight section of an airplane, imaging a target in a field of view, carrying out target detection by adopting an optical flow method, and detecting a moving target by analyzing a motion vector of pixel points in an image sequence; and resolving the deviation amount of the target image relative to the visual axis in real time, namely the target pixel miss distance. 2, designing a stable tracking loop: designing a two-layer control structure for the stable tracking loop, stably inhibiting high-frequency disturbance by a gyroscope of an inner loop, performing tracking correction on low-frequency deviation by an outer loop based on pixel miss distance, and finally realizing high-precision tracking. On the basis of real-time pixel miss distance feedback, a two-layer control structure is designed, the miss distance fed back by an outer ring tracking loop is converted into an inner ring control instruction, and the tracking precision and stability are improved.

The invention relates to the technical field of hybrid aircrafts, and discloses a high-power take-off energy supply system for a hybrid aircraft based on superconducting magnetic energy storage, which is characterized in that a superconducting coil is directly soaked in a hydrogen storage tank of the aircraft, and a large amount of liquid hydrogen carried by the aircraft is used as a cold source of the superconducting coil; the weight of a refrigerating machine and a heat preservation tank which are necessary for original superconducting magnetic energy storage is saved; when the aircraft is in a scene with low power requirements such as level flight or landing, the power generated by the superconducting generator driven by the gas turbine is greater than the power required by the aircraft, and at the moment, the superconducting coil can be charged to realize energy recovery and storage; under the scene of high power demand such as takeoff, the advantages of high power density, high response speed and the like of the superconducting coil are utilized to provide electric power for the propulsion unit so as to meet the high-power demand of the aircraft in the stages such as takeoff and the like, and the high-power maneuvering, electric energy management and transmission capabilities of the hybrid aircraft are greatly improved.

The invention discloses an arbitrary three-dimensional terrain visual coverage unmanned aerial vehicle energy optimization trajectory generation method, which comprises the following steps of: generating visual coverage air route points: selecting a mountain region, acquiring a rough digital elevation model by utilizing a geographic information system or level flight shooting, calculating the air route points based on photogrammetry constraints, and calculating the visual coverage air route points; traversing the waypoints according to a predetermined sequence to complete a coverage task; modeling the energy consumption of the motor of the unmanned aerial vehicle: taking the brushless direct current motor as an object, carrying out mathematical modeling in combination with torque dynamics and electromagnetic equations of the motor, constructing a physical information neural network model, and training and optimizing flight data; and track optimal prediction control input mapping: designing an optimal prediction control method based on unmanned aerial vehicle dynamics, and calculating a mapping relation between the track and control input. According to the invention, the coverage efficiency can be obviously improved, so that the single flight coverage range of the unmanned aerial vehicle is expanded.

The invention discloses a meta universe task offloading and resource scheduling method based on deep reinforcement learning, and relates to the technical field of wireless communication, and the method comprises the steps: 1, putting an unmanned aerial vehicle cluster in a user dense region, and enabling a fixed edge server to obtain the position coordinates of the fixed edge server, each user and each unmanned aerial vehicle; 2, a user sends a rendering request to the fixed edge server through the unmanned aerial vehicle cluster; step 3, constructing an optimization target, converting the optimization target into a Markov decision process, solving the optimization target through a PPO algorithm, and obtaining a horizontal flight rate, a flight direction and a vertical direction rate of the unmanned aerial vehicle and a computing resource set available for edge equipment; step 4, the fixed edge server issues a decision result to the user and the unmanned aerial vehicle, and the user and the unmanned aerial vehicle execute a decision; and step 5, after the unmanned aerial vehicle completes the rendering task, returning a result to the user. The method has the characteristics of multi-node collaborative optimization, energy consumption optimization and resource utilization rate optimization.

Described are systems and methods for active weathervaning of a hybrid flight aerial vehicle, such as an unmanned aerial vehicle (UAV). Active weathervaning of the hybrid flight aerial vehicle during can be provided during vertical takeoff and landing (VTOL) / hover flight without the assistance of any low-speed wind sensors and during transitions between VTOL / hover flight and fixed-wing, wing-borne, horizontal flight. Additionally, active weathervaning can be provided during propulsion mechanism failure conditions where the aerial vehicle may be experiencing failure conditions associated with one or more propulsion mechanisms.

The invention discloses a flight trainee attention and error behavior detection method based on a multi-modal physiological signal, and the method comprises the steps: obtaining the electrocardiogram data, eye movement data and electroencephalogram data of a flight trainee in a flight training process, and subjective evaluation data; based on subjective evaluation data, dividing flight student attention distribution conditions into a high grade, a middle grade and a low grade by adopting a clustering algorithm; performing feature optimization processing on the physiological data, and constructing a physiological feature attention level flight behavior associated data set; constructing an attention distribution level judgment model and a flight error behavior detection and early warning model; and outputting an attention level judgment result and a flight error behavior detection and early warning result. According to the method, association mapping of the multi-modal physiological signals and flight performance is realized, an attention grading standard for a flight training specific scene is established, and conversion from passive response to active early warning is realized.

The invention belongs to the technical field of flight test, and discloses a cockpit vision field evaluation test flight method suitable for a troposphere manned airship, which comprises the following steps: selecting an airship test condition; the airship climbs to a preset field height and keeps level flight; a preset flight test action is completed; and commenting by a flight tester, and filling in a cockpit vision field commenting card. According to the method, the blank of the flight test method for evaluating the visual field of the cockpit of the troposphere manned airship with the vector propulsion system is filled, and the flight test efficiency and the flight test quality of the manned airship are improved.

A vertical take-off and landing aircraft which uses fixed rotors for both VTOL and forward flight operations. Some of the rotors are forward canted, while some of the rotors are forward facing. The forward canted rotors are tilted forward slightly from vertical and provide some forward propulsion during horizontal flight. The forward facing rotors may be fixed in a forward facing configuration. Forward swept wings allow for rotor placement which brings efficiency during hover operations.

The invention discloses an unmanned aerial vehicle route planning method, device and equipment and a medium, and the method comprises the steps: obtaining the real-time transient wind field data of an unmanned aerial vehicle, and generating the flow field information of time-space correlation according to the real-time transient wind field data; a flight energy consumption model is established based on the flow field information, the flight energy consumption model is adopted to calculate energy consumption in different stages, node energy consumption attribute values are obtained, and the different stages comprise a level flight stage, a climbing stage and a descending stage; and the node energy consumption attribute value is input into the heuristic search algorithm model to obtain the current path planning with the lowest energy consumption, so that the accuracy of the route planning is improved, and the route energy consumption is saved.

An aeronautical vehicle performs horizontal flight and / or vertical flight, and has a fuselage, a wing assembly having a first wing part and a second wing part rigidly coupled to one another, a rotor assembly, a horizontal thruster, and an attitude control system. The wing assembly is arranged rotatably with respect to the fuselage to rotate about a vertical pivot axis between a stow position and an active position. The rotor assembly includes two vertical thrust rotors arranged on a rotor support rotatably with respect to the fuselage to rotate the rotor assembly between a stow position and an active position. In a horizontal flight mode the wing assembly is in the active position and the rotor assembly is in the stow position, and in a vertical flight mode the wing assembly is in the stow position and the rotor assembly is in the active position.

The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a tailstock type overwater vertical take-off and landing fixed-wing unmanned aerial vehicle which can float and park on the water surface, can vertically take off to leave the water and is switched into a fixed-wing mode for cruising and level flight. The unmanned aerial vehicle comprises a four-rotor support buoy and a wing body fusion body fixed to the upper portion of the four-rotor support buoy, small wing type buoys are arranged on wing tips of the two sides of the wing body fusion body respectively, and lifting ailerons capable of deflecting up and down are arranged on the rear edges of wings on the two sides of the wing body fusion body respectively. And four motor rotor propeller propelling devices are uniformly arranged at the tip part of the four-rotor bracket buoy.

A rotorcraft consisting of a fuselage, a plurality of arms on which electric motors driving propellers are mounted, one or a plurality of pivoting rotor supports on which thrust generating rotors with one or a plurality of blades attach. The rotor supports are substantially vertical when the aircraft is flying vertically, hovering, or on the ground, and tilted with respect to the aircraft when the aircraft has a forward motion component. The rotors can be powered on the ground, in hover, or in vertical flight, and spin in autorotation in horizontal flight.

The invention relates to the field of bridge line shape detection in civil engineering, in particular to a large-span suspension bridge main cable line shape automatic calculation method based on airborne laser scanning. The method comprises the following steps: fusing high-precision inertial navigation, a differential GNSS (Global Navigation Satellite System), airborne laser scanning equipment and an RTK (Real-Time Kinematic) technology, and acquiring a large-scale fine point cloud model by utilizing a two-level route planning method: on the basis of an SCF-Net network, providing an SCF-Bridge-Net based on a sling attention mechanism in combination with the structural characteristics of a suspension bridge; inclination angle, elevation and mileage information of all cable clamps are realized through a geometric information calculation method, and linear measurement of a bridge is realized. According to the method for automatically calculating the line shape of the main cable of the large-span suspension bridge based on airborne laser scanning, aiming at obtaining point cloud of a large suspension bridge structure in the construction process, a high-precision inertial navigation system and a differential GPS fusion method are combined with airborne laser scanning equipment, and a route planning method with a cable clamp as a core path is established through a coarse scanning model; and fine scanning of the large-span suspension bridge is realized.

A flight mode transitioning device, method and system configured to facilitate transitioning between vertical flight mode and horizontal flight mode in a vertical take-off and landing (VTOL) aircraft, the device comprising at least one actuator mediated member capable of limiting the movement the aircraft wing so as to enable both forward fight and vertical flight.

An electric vertical take-off and landing (eVTOL) aircraft can enhance energy efficiency, safety, and operational range. A deployable wing structure can provide aerodynamic lift during horizontal flight, reducing reliance on energy-intensive propellers. Integrated flexible solar panels capture solar energy, contributing additional power and optimizing energy management. The wing system also includes an emergency descent mode, doubling as a glide-assist device for controlled landings during critical failures. The system offers modular configurations for various missions, ensuring adaptability and improved flight performance. The eVTOL can be implemented with systems and methods for mitigating motion sickness. The systems integrate tactile feedback systems into wearable devices and environmental components. Sensors detect motion and environmental changes, and a computing device can generate corresponding tactile feedback signals. Tactile actuators embedded in the devices or components provide non-visual motion cues, such as pressure, vibration, and haptic feedback, to resolve sensory mismatches between the vestibular and proprioceptive systems.

The invention discloses a novel tilting dual-rotor unmanned aerial vehicle, which belongs to the technical field of unmanned aerial vehicles, and comprises a wing body fusion fuselage and two outer wing sections, the two tilting rotor assemblies are used for providing power, controlling rolling, pitching and yawing in a vertical flight mode and controlling yawing in a horizontal flight mode, the two pitching and rolling rudder assemblies are used for controlling pitching and rolling in a horizontal flight state, and the two tilting rotor assemblies are symmetrically arranged in front of the wing body fusion fuselage; the pitching rolling rudder assembly is arranged in the middle of the outer wing section; the outer wing section is of a structure capable of being folded in the tail direction, so that the center of gravity is moved backwards to the position behind a stop point of the tail after the outer wing section is folded, and the unmanned aerial vehicle stably stops on a rod-shaped object with the diameter being 13 cm or less under the unpowered condition. On one hand, the problems that a tailstock type unmanned aerial vehicle is difficult to take off and land and a traditional unmanned aerial vehicle needs an undercarriage to take off and land are solved, and the problems that an existing unmanned aerial vehicle needs to be additionally provided with a parking actuator and needs to be parked with power are solved.

The invention discloses a training aircraft flight training simulator system in the field of aircraft training simulator systems, which comprises a cabin and instrument indicating system, a visual imaging display system, a flight resolving system, a control and control load system, a cabin buffeting system, a sound system, a console system and a computer network, the cabin and instrument indicating system is mainly composed of a cabin simulation system and a cabin instrument system. The visual imaging display system is displayed on the display distributor and the cabin and instrument indicating system through a computer network and the flight resolving system in an imaging mode. According to the invention, flight simulation training of sliding, takeoff, turning, level flight, gliding, landing and takeoff and landing routes under four meteorological conditions can be simulated; the special effect flight simulation training such as circling, diving, jumping, sharp rising turning, rolling, sharp circling descending, sideslip, horizontal 8-shaped, weight giving, inclined weight giving and semi-rolling reversing can be implemented.

The present invention relates to the field of unmanned aerial vehicles, and in particular to a control method, system and unmanned aerial vehicle for paraglider towing. The control method, system and unmanned aerial vehicle control the unmanned aerial vehicle to fly horizontally in front of the paraglider; obtain the relative position of the unmanned aerial vehicle and the paraglider in the air; obtain the height direction offset between the unmanned aerial vehicle and the paraglider through the relative position of the unmanned aerial vehicle and the paraglider in the air; set an offset threshold, compare the height direction offset with the offset threshold in real time, and obtain a comparison result; according to the comparison result, when the height direction offset between the unmanned aerial vehicle and the paraglider is greater than the offset threshold, control the unmanned aerial vehicle to lift or lower to adjust the height. By controlling the relative height of the unmanned aerial vehicle and the paraglider, the paraglider can obtain the maximum horizontal traction force provided by the unmanned aerial vehicle, improving the towing efficiency of the unmanned aerial vehicle. Under the condition of providing the same traction force, the load of the unmanned aerial vehicle is minimized.

A method of in situ measurement of an acoustoelastic constant (L) of a railway rail, using an ultrasonic wedge sensor to measure a stress-free (unloaded) time-of-flight (t0) in the vertical direction of the rail. Next, a vertical load of known load value is applied to the rail. While the vertical load is applied, the ultrasonic wedge sensor is used to measure a stressed time-of-flight value. The difference between the stress-free and the stressed time-of-flight is calculated to obtain a time-of-flight difference value (Δt). Based on the load value, the stress-free time-of-flight value, and the time-of-flight difference value, the acoustoelastic constant, L, may be calculated. The wedge sensor may be further used to measure the (stressed) horizontal time of flight, and a time-of-flight difference value in the horizontal direction may be used to measure longitudinal stress.

The present invention discloses a metaverse task offloading and resource scheduling method based on deep reinforcement learning, which relates to the field of wireless communication technology, including: step 1, placing a drone cluster in a user-dense area, and a fixed edge server obtaining the position coordinates of itself, each user and each drone; step 2, the user sends a rendering request to the fixed edge server through the drone cluster; step 3, constructing an optimization target, and converting the optimization target into a Markov decision process, solving the optimization target through the PPO algorithm, and obtaining the horizontal flight rate, flight direction, vertical direction rate and computing resource set available to the drone; step 4, the fixed edge server sends the decision result to the user and the drone, and the user and the drone execute the decision; step 5, after the drone completes the rendering task, the result is transmitted back to the user. The present invention has the characteristics of multi-node collaborative optimization, optimized energy consumption and resource utilization.

The application belongs to the technical field of aircraft simulation, and particularly relates to a flight simulation method and device under gust load. The method comprises the following steps: S1, performing aircraft 1g level flight trimming to determine the aircraft trimming angle of attack and the aircraft trimming elevator deflection; S2, determining the aerodynamic force of the aircraft; S3, performing dynamic response solution on the aerodynamic force of the aircraft to obtain the aerodynamic angle of attack, the flight speed and the pitch angular velocity, and determining the normal overload of the aircraft after superimposing the flight speed on the wind speed of the vertical gust field; S4, obtaining the elevator deflection calculated by the stability augmentation system, superimposing the elevator deflection at a simulation moment to obtain the actual required elevator deflection; and S5, re-determining the aerodynamic force of the aircraft according to the flight speed, the pitch angular velocity, the aerodynamic angle of attack and the actual required elevator deflection until the simulation is completed. The application considers the role of the stability augmentation system in the determination of the aircraft gust load, and the simulation process is simple and has high precision.

1. Name of the product in this design: Graphical User Interface for Adding Flight Information to Electronic Devices. 2. Intended use of this design: for use in an electronic device. 3. The key design feature of this product is its graphical user interface. 4. The image or photo that best illustrates the design points: Design 1 Interface Change State Diagram. 5. Other views are omitted as they are standard design. 6. Design 1 is designated as the basic design. 7. Purpose of the graphical user interface: This interface is used to add flight information in city-level flight service systems, such as operator information or aircraft information. Design 1: The main view is the initial interface. Figure 1 shows the interface that appears after clicking the "+" icon in the upper right corner of the main view of Design 1. Design 2's interaction is consistent with Design 1.

The invention discloses a fixed wing patrol aircraft flight attitude control method, and belongs to the technical field of unmanned aerial vehicles. Aiming at the technical contradiction that high-speed flight maneuverability and weapon shooting stability cannot be compatible, the method achieves breakthrough through the following innovative schemes that a four-wing propeller collaborative framework is designed, and each propeller is provided with a horizontal linear driver to achieve front-back telescopic displacement in the axial direction of a fuselage; in the horizontal flight stage, based on the feedback of a gyro stabilizer, pitching / rolling double-axis attitude accurate control is realized through the cooperative adjustment of propeller position stretching and rotation speed difference; triggering a layered compensation strategy by an ignition event, and synchronously adjusting the horizontal position and the rotating speed of a propeller according to the recoil force direction; and the tail vane intervenes in fine adjustment only when the yaw is out of tolerance. By combining the seamless conversion design of the vertical take-off and landing stage, the three technical problems of height loss without initial-speed deployment, low aerodynamic efficiency of high-speed flight and insufficient shooting precision are solved.

The present invention discloses a method, device and computer-readable storage medium for calibrating the drag coefficient of a multi-rotor. The method includes: performing flight tests at multiple set airspeeds along a straight and level flight route in a windless environment and a windy environment, and recording flight control logs according to a measurement sequence composed of airspeed, inclination angle and acceleration during the flight tests; combining each flight control log, respectively selecting corresponding measurement combinations according to the acceleration, endurance and acceleration corresponding stages; taking the least square solution obtained from a preset number of the measurement combinations as the calibration result, and applying the calibration result to a preset real-time airspeed estimation algorithm to obtain an estimation result. The present invention realizes a low-cost experimental calibration algorithm, efficiently and accurately calculates the multi-rotor drag coefficient function, and effectively verifies the accuracy of the calibration result and the estimation algorithm.

The invention discloses a horizontal flight display device and a horizontal flight display system, and relates to the technical field of flight display. The horizontal flight display device comprises a flight assembly which comprises a main body and a plurality of rotor wings arranged on the main body; the display assembly is arranged on the lower side of the flight assembly and connected with the main body, and the display assembly is provided with a display face facing the vertical lower portion; air gaps allowing airflow to pass through are formed in the positions, at least corresponding to the rotor wings, of the display assembly; the projection area of the multiple rotor wings on the display assembly in the vertical direction is smaller than the area of the display assembly. According to the flight display device, the display screen can be horizontally and stably displayed in the air.