29 results about "Airmanship" patented technology

The invention provides a pilot manipulation quality real-time analysis method and system in a wind shear environment, and relates to the technical field of aviation flight, and the method comprises the steps: firstly capturing flight manipulation and environment interaction data including flight state feedback data and pilot manipulation execution data; secondly, establishing a response association link set of the manipulation action and the environment change, taking the wind shear environment change as a trigger node, taking pilot manipulation execution as a response node, and taking flight state feedback as an association node; tracing the matching relation between the time sequence track of the control action and the environment change, and outputting a time sequence matching relation set; analyzing the adaptability dynamic change of the manipulation action based on the time sequence fit relationship set evolution, and outputting an adaptability dynamic change result; and finally, generating a manipulation adjustment guide based on the dynamic change result of the adaptability, assisting a pilot in optimizing manipulation actions in real time, and improving the flight safety and manipulation quality.

The invention discloses a low-altitude air route generation method, device and equipment and a storage medium, and belongs to the technical field of low-altitude flight. The method comprises the following steps: acquiring a three-dimensional space model and population density distribution of a target area; determining the path cost of each voxel based on the population density of each voxel at the ground projection in the three-dimensional space model, the obstacle state of each voxel and the distance between each voxel and the target facility; and taking a first position in the three-dimensional space model as a starting point, taking a second position in the three-dimensional space model as an end point, and taking the lowest sum of the path costs of voxels passing between the first position and the second position as a target to carry out path planning so as to obtain a target low-altitude airway. According to the scheme, the low-altitude aircraft can be far away from a densely populated area, avoids obstacles as much as possible and flies according to the instruction of the target facility in the target area, and meanwhile the flight efficiency and safety are guaranteed.

This invention relates to the field of helicopter flight management system technology, and in particular to a half-plane segment switching method for low-altitude obstacle avoidance flight. This method extracts flight plan information, calculates the turning direction based on the azimuth information of the preceding and following segments, and further calculates the turning angle. Based on the turning direction and angle, it calculates the azimuth of the angle bisector of the preceding and following segments, and then determines whether the helicopter meets the segment switching conditions based on the sign of its offset from the angle bisector. This segment switching method is independent of flight technical errors and significantly improves segment switching efficiency.

The invention relates to a flight capacity determination method and device, computer equipment, a medium and a product, and relates to the technical field of low-altitude flight. The method comprises the following steps: acquiring route grids occupied by a target route in an airspace to which the target route belongs, and environment influence coefficients corresponding to the route grids in a preset flight environment; acquiring a basic safety distance corresponding to the aircraft of the reference type; determining at least one target safety distance according to the environmental influence coefficient and the basic safety distance corresponding to the at least one route grid on the target route; and determining the flight capacity of the aircraft of the reference type in the target route according to the at least one target safety distance. According to the technology provided by the invention, the flight capacity can be quickly determined according to the environmental influence coefficient and the basic safety distance, and the basic safety distance can be corrected to obtain the actual safety distance based on the corresponding environmental influence coefficient of the air route grid in the preset flight environment, so that the flight capacity better conforming to the flight environment can be determined.

The invention discloses a flight skill assessment method, device and equipment for a pilot and a medium, and relates to the field of flight skill assessment, and the method comprises the steps: obtaining a flight parameter time sequence in a flight task process; determining pilot ability dimension estimated values according to the speed, the height, the change rate of the accelerator position, the pitch angle, the roll angle and the course angle in the sequence and the change characteristics of the sequence; determining an aircraft performance utilization dimension estimated value according to the speed, height and overload in the sequence; and respectively carrying out normalization and weighted summation on each index in the pilot capability dimension estimated value and the aircraft performance utilization dimension estimated value to obtain a flight technology evaluation index of the pilot. According to the method, the systematic mapping relation is established between the flight parameters and the manipulation behaviors and tactical decision-making ability of the pilot, the flight ability of the pilot is converted into computable and comparable structured indexes, and the effect of quantitatively evaluating the flight technology of the pilot by using the flight parameters is improved.

This application discloses a method, system, and electronic device for flight technical quality assessment. The method includes: selecting parameter types from historical QAR data based on the maximum relevance and minimum redundancy criterion as indicators for assessing flight quality; determining the weight coefficients of each indicator based on historical QAR data; determining the standard thresholds of each indicator based on historical target flight data; training and generating a personal flight habit model corresponding to the pilot to be assessed based on the first indicator parameter value, weight coefficient, and standard threshold of the pilot to be assessed in historical QAR data; and determining the flight quality assessment result corresponding to the pilot to be assessed based on the second indicator parameter value of the pilot to be assessed in current QAR data, the personal flight habit model corresponding to the pilot to be assessed, as well as the weight coefficient and standard threshold.

The application belongs to the technical field of aviation flight, and particularly relates to a multi-source data fusion and dynamic adjustment algorithm and system suitable for complex flight environment, which comprises the following steps: data acquisition and preprocessing; multi-source data fusion; path planning and dynamic adjustment; adaptive control and execution; exception handling and redundancy compensation. Based on the multi-source data fusion and dynamic adjustment algorithm, the flight strategy is dynamically adjusted in real time by fusing multiple sensor data, and the navigation ability and safety of the aircraft in the complex environment are significantly improved. Compared with the traditional navigation system relying on a single sensor, the self-navigation and control ability of the aircraft in the complex flight environment is significantly improved through the multi-source data fusion and dynamic adjustment algorithm, and the uncertainty problem caused by data loss and environmental changes in the prior art is effectively solved.

The invention relates to the technical field of flight simulation, in particular to a flight simulation equipment control quality goodness of fit calculation method based on incomplete test flight data. Comprises: determining a test item; acquiring real flight data of the test item and simulation data of flight simulation equipment; preprocessing the real flight data and the simulation data; complementing the missing part of the real flight data; and comparing the real flight data with the simulation data, and calculating the control quality goodness of fit. According to the invention, automatic testing of flight test data and simulated flight data can be realized, and the defect of inaccuracy caused by subjective artificial evaluation is overcome.

The invention discloses a single-person low-altitude aircraft based on a distributed power and intelligent attitude stabilizing system and a control method, and relates to the technical field of aviation flight, the single-person low-altitude aircraft comprises a central bearing unit, a control unit and a control unit, the central bearing unit is constructed into a rigid backpack structure conforming to a human body back curve; a distributed propulsion system includes; the pair of main lift ducted fans are symmetrically and pivotally mounted on two sides of the central bearing unit, and ducted nozzles of the main lift ducted fans can be controlled to perform vector deflection; the multiple auxiliary stabilizing ducted fans are installed on the adjustable exoskeleton supports corresponding to the four limbs of the user respectively, the multiple fans disperse propulsive force to the back and the four limbs, a real-time adjusting algorithm is matched, the body balance problem in the flying process is effectively solved, and the user can keep the stable posture without continuously and finely adjusting the limbs. By means of the design, the two hands of an operator can be naturally liberated in the flying process, and the device can be used for executing task operations such as shooting and detection.

The application relates to an airborne composite cable tension control method, and belongs to the technical field of aviation flight.The method steps are as follows: a two-dimensional composite cable damping-spring model is established; a two-dimensional coordinate system of the composite cable damping-spring model is established; a composite cable dynamics model is established; a test target object dynamics model is established; a test target object surface wall pressure distribution diagram is obtained; micro-element stress distribution diagrams of the composite cable at different positions under different working conditions are obtained; a power motor control model is constructed; stress fluctuation curves of the composite cable and the connection position of a mother machine are input into the power motor control model, speed and position control instructions of a direct-current brushless motor are obtained, the control instructions are executed by the direct-current brushless motor, action control of composite cable retraction and release is completed, and airborne composite cable tension control is completed.The control mode of the application is optimized, and compared with a traditional observer, an error is reduced by 26.45%, and the position and speed tracking effect is effectively improved.

This utility model belongs to the field of low-altitude flight technology and provides an electric pitch control mechanism for aircraft propellers. It includes a propeller assembly, a propeller hub, a drive assembly, and a pitch control module. The propeller assembly is connected to the propeller hub, and the pitch control module is installed inside the hub. A sensor assembly is mounted on the pitch control module to collect real-time changes in the propeller's angle or distance. The propeller assembly is connected to the pitch control module and uses the sensor assembly to collect and provide real-time feedback on these changes, thereby controlling the pitch angle. This patent uses sensors to collect the rotation angle of the lead screw shaft, the displacement of the pitch slider, and directly collect the pitch angle, enabling real-time feedback and control of the pitch angle. Its structure is simple, and it achieves stepless control of the pitch angle. Adjusting washers are used to adjust the clearance of the lead screw shaft within the propeller hub, improving the response speed of the lead screw shaft and the response accuracy of the propeller's pitch angle.

The invention relates to the technical field of flight, and discloses an aircraft capable of realizing free flight of human beings, the aircraft comprises an aircraft main body, when the aircraft is used, a micro turbine engine, a wing I and a wing II are arranged, a vector micro turbine engine is carried on the waist of the human beings, and the micro turbine engine generates vertical lifting force, so that the free flight of the human beings is realized. About 95% of the dead weight of the human body can be effectively counteracted, in-situ take-off of the human body is helped, meanwhile, the movable bionic wing membranes from the shoulders to the wrists adopt carbon fiber frameworks and self-adaptive skin structures, the first wing and the second wing are driven to do wing flapping motion through waving of back muscle groups and arms, and the wing flapping effect is achieved. Therefore, the high-efficiency thrust device fixed on the human body can help the human to take off in situ, and the wing I and the wing II can fly in the air like a bird, so that the flat-bottom take-off can be realized, and the free flying of the human in the true sense can be realized.

The application provides a pilot behavior detection method and system and an aircraft, and particularly relates to the technical field of flight, and comprises the following steps: calculating flight control quantity into control target flight parameters, and determining the real-time flight mode of the aircraft based on the real-time flight parameters of the sensor at the current time; matching an abnormal control judgment matrix according to the real-time flight mode, and inputting the control target flight parameters and the real-time flight parameters into the abnormal control judgment matrix to calculate a risk score; performing flight state evaluation on the aircraft based on the risk score, and determining that the pilot has abnormal behavior when the flight state is abnormal; or determining that the pilot does not have abnormal behavior when the flight state is normal. The application can identify whether the pilot has abnormal control by performing combined operation on the real-time flight parameters and the control target flight parameters; the application does not need to perform a large number of simulation tests or model training in advance, the calculation amount is small, and the demand and burden of the on-board processor operation amount are low.

This invention belongs to the field of low-altitude flight technology and provides an integrated rotor electric pitch control structure for aircraft. It includes a rotor assembly, a control module assembly, a drive assembly, and a pitch control module. A sensor assembly is installed at the bottom of the pitch control module. The control module assembly is mounted on the drive assembly and receives the pitch angle control signal input and the angle signal input from the sensor assembly. After internal calculation, it outputs the relevant speed signal to the drive assembly. A PID controller performs PID calculations on the error to obtain the control quantity and limits the control quantity. The angle of the lead screw shaft is monitored in real time through a sensor connector and fed back to the control module for closed-loop adjustment. This patent has a simple structure, achieves stepless control of the pitch angle, and improves control accuracy and response speed through angle feedback. It realizes integrated control and drive, simplifies the signal transmission structure, and improves signal quality and pitch performance.

The invention relates to the technical field of low-altitude operation safety and risk assessment, and provides a flight safety control method and system based on low-altitude risk directed network deduction, and the method comprises the steps: constructing a low-altitude risk directed network, calculating an avoidance interval corresponding to a plurality of collision event layer nodes according to a navigation performance error and a flight technology error, calculating the security interval of the plurality of collision event layer nodes according to the avoidance interval; calculating a judgment threshold according to the safety interval, calculating a time delay accumulation result according to a time delay transmission and accumulation process in the low-altitude risk directed network, deducing expected safety levels of a plurality of collision event layer nodes according to the judgment threshold and the time delay accumulation result, and determining the collision event layer nodes according to the expected safety levels and a target expected safety level. And outputting a safety level control scheme by controlling the reference time delay and the safety interval. According to the method, the expected safety level can be deduced, a control scheme is output to enable the safety level to reach the target expected safety level, and the low-altitude operation safety is improved.

The present invention is applicable to the field of flight technologies of low-altitude airspace vehicles, and provides a method for calculating flight path and anti-collision of a low-altitude vehicle, including: obtaining three-dimensional dimension data of the vehicle, and determining the corresponding earth grid level of the current vehicle according to the maximum dimension; establishing a path data set; calculating the grid set passed by the flight path. During anti-collision analysis, according to the code of the grid unit where the current vehicle is located and the distance from the center point, the spatial relationship between grid units is judged, and thus the spatial relationship of the vehicle can be obtained. The present invention does not display the path in the form of coordinate points, but displays the flight path in the form of earth grid units in three-dimensional space, making the path display more intuitive, the position more realistic and comprehensive, and also facilitating subsequent collision analysis; moreover, by judging the spatial relationship between the grid units where the vehicle is located, the problem of anti-collision detection during the flight of the vehicle in low-altitude airspace is solved.

The invention provides an intelligent flight decision-making auxiliary system and method based on multi-modal flight data, and relates to the technical field of aviation flight, and the method comprises the steps: firstly obtaining multi-source flight data which comprises multiple monitoring dimensions such as a flight attitude, an external environment, a dynamic parameter and the like and has a time correlation attribute; extracting performance characteristics and collaborative change characteristics of data of different monitoring dimensions in each flight scene, establishing a dynamic association model, determining influence weights based on the dynamic association model, generating scene decision factors, establishing association rules of influence transfer characteristics and flight operation response logic, and constructing a decision response link; finally, logic in the decision response link is converted into natural language expression, an intelligent flight decision auxiliary instruction containing flight operation suggestions and data monitoring key points is output, and the flight safety and efficiency can be effectively improved.

The invention is suitable for the technical field of aviation flight, and provides a flight plan generation method and system for an air traffic time-varying environment, and the method comprises the following steps: collecting data which comprises the origin-destination and plan time of a flight, the performance of an aircraft, the layout of waypoints and the airspace information of the waypoints; extracting features of an air traffic time-varying environment based on a space-time network; constructing a flight plan generation bilevel planning model considering the air traffic time-varying environment; designing a two-stage algorithm for solving a flight plan to generate a double-layer planning model; and evaluating the robustness of the solution. According to the invention, big data and artificial intelligence technologies are fused, a flight plan generation double-layer planning model considering a time-varying traffic environment and a two-stage solving algorithm thereof are established, and a robustness evaluation technology of a flight plan is discussed. A function of automatically generating an executable flight route point sequence and a corresponding flight path according to an air traffic time-varying environment is realized, and a technical support is provided for intelligent management of a flight plan by a daily dispatcher.

The invention provides a manned aircraft and unmanned aerial vehicle cooperative flight early warning method and system, and relates to the technical field of aviation flight, and the method comprises the steps: obtaining a manned aircraft route path, scientifically dividing and distributing a task region, and constructing a clear task dependence graph to clarify the relation between each unmanned aerial vehicle and the task region; environment safety levels are accurately divided through a safety evaluation model by using unmanned aerial vehicle sampling data, and a reliable basis is provided for subsequent decision making; the task weight of the unmanned aerial vehicle is dynamically and flexibly adjusted based on the security level, and an effective task switching decision is realized by a switching value quantitative index; and finally, through real-time monitoring, redistribution of the unmanned aerial vehicle and continuous updating of the security level and early warning information, a set of autonomous cooperative network mechanism for cooperative flight early warning of the manned aerial vehicle and the unmanned aerial vehicle, which is continuously optimized from task starting to task ending and adapts to environment change, is formed, the early warning response speed and the resource utilization efficiency in a complex environment are remarkably improved, and the early warning efficiency is improved. And the safety of cooperative flight and the task completion quality are effectively improved.

An embodiment of the present invention provides a method and system for fault recovery of distributed aerospace multi-flight control nodes, relating to the field of aerospace flight technology. The method is employed by a distributed aerospace multi-flight control node system and includes: when no online representative node exists in the system, each online flight control node in the system sends voting information to other online flight control nodes in the system; each online flight control node in the system sets itself as a representative node or a computing node based on the received voting information and subject to preset representative node election rules; the representative node uses its own local command log to update the local command log of the computing node, so that the local command logs of all computing nodes in the system are identical to the local command log of the representative node. This method achieves recovery from single-point failures in a multi-mode flight control system.

The embodiment of the invention provides a spaceflight distributed multi-flight-control-node fault recovery method and system, and relates to the technical field of spaceflight, the method is adopted by a spaceflight distributed multi-flight-control-node system, and the method comprises the following steps: under the condition that no online representative node exists in the system, performing fault recovery on the representative node; each online flight control node in the system sends voting information to other online flight control nodes in the system; each on-line flight control node in the system sets the on-line flight control node as a representative node or a computing node according to the voting information received by the on-line flight control node under the constraint of a preset representative node election rule; and the representative node uses the local command log of the representative node to update the local command log of the computing node, so that the local command logs of all the computing nodes in the system are the same as the local command log of the representative node. And recovery of a single-point fault of the multi-mode flight control system is realized.

The invention provides an aircraft flight deviation correction control adaptation method based on a single-mode or dual-mode image, and belongs to the technical field of airborne air-ground image flight. According to the method, the sensitivity of a control unit is matched with the dynamic change characteristic of a sensor image view field through a manually designed algorithm; the phenomenon of repeated overshoot of an aiming line caused by excessive sensitivity of control instruction input due to gradual change of a view field when the image guidance aircraft is manually controlled for target positioning is effectively eliminated, and meanwhile, the positioning precision of the aircraft and the stability and controllability of manual control of an operator are remarkably improved; the method is characterized in that photoelectric system image assistance, laser ranging indication and control unit sensitivity are automatically correlated and corrected in real time according to the distance between the aircraft and a target, so that the deviation between the aircraft and the target is quickly and accurately corrected; and the single / dual-mode image aircraft can be flexibly and manually controlled and accurately hit a moving target under the assistance of a photoelectric system.

The application provides an intelligent flight decision assistance system and method based on multi-modal flight data, and relates to the technical field of aviation flight. First, multi-source flight data containing multiple monitoring dimensions such as flight attitude, external environment and power parameters and having time correlation attributes are acquired. Then, the performance characteristics and cooperative change characteristics of different monitoring dimension data in each flight scene are extracted, a dynamic correlation model is established, the influence weight is determined based on the dynamic correlation model, the scene decision factor is generated, the association rules of the influence transmission characteristics and the flight operation response logic are established, the decision response link is constructed, and finally the logic in the decision response link is converted into natural language expression. The intelligent flight decision assistance instruction containing flight operation suggestions and data monitoring priorities is output, and the flight safety and efficiency can be effectively improved.

The application relates to a space domain risk early warning method and device, computer equipment, medium and product, and relates to the technical field of space domain flight. The method comprises the following steps: acquiring space grids corresponding to different height layers under a target space domain and risk environment data corresponding to the target space domain; for each space grid, determining risk influence information corresponding to the space grid based on the risk environment data corresponding to the space grid; acquiring a to-be-early-warned grid of a target aircraft in the target space domain; and based on the risk influence information corresponding to each space grid and the to-be-early-warned grid, performing risk early warning on the target aircraft. According to the technology of the application, a comprehensive and accurate risk map can be constructed according to the space grids under the target space domain and the risk environment data corresponding to the target space domain, so that after the to-be-early-warned grid of the target aircraft in the target space domain is acquired, accurate risk early warning can be performed on the target aircraft based on the risk map and the to-be-early-warned grid.

This invention discloses a method, apparatus, device, and storage medium for generating low-altitude flight paths, belonging to the field of low-altitude flight technology. The method includes: acquiring a three-dimensional spatial model of the target area and its population density distribution; determining the path cost of each voxel based on its population density at the ground projection of each voxel in the three-dimensional spatial model, the obstacle status of each voxel, and the distance between each voxel and the target facility; and performing path planning with a first position in the three-dimensional spatial model as the starting point and a second position in the three-dimensional spatial model as the ending point, aiming to minimize the sum of the path costs of the voxels traversed between the first and second positions, thereby obtaining the target low-altitude flight path. This solution allows low-altitude aircraft to stay away from densely populated areas, avoid obstacles as much as possible, and fly according to the instructions of the target facility in the target area, while ensuring flight efficiency and safety.

The invention relates to an airspace risk early warning method and device, computer equipment, a medium and a product, and relates to the technical field of airspace flight. The method comprises the steps of obtaining space grids corresponding to different height layers in a target airspace and risk environment data corresponding to the target airspace; for each space grid, risk influence information corresponding to the space grid is determined based on the risk environment data corresponding to the space grid; obtaining a to-be-early-warned grid of the target aircraft in the target airspace; and carrying out risk early warning on the target aircraft based on the risk influence information corresponding to each space grid and the to-be-early-warned grid. According to the technology of the invention, a comprehensive and accurate risk map can be constructed according to the space grid in the target airspace and the risk environment data corresponding to the target airspace, so that after the to-be-early-warned grid of the target aircraft in the target airspace is obtained, the to-be-early-warned grid of the target aircraft in the target airspace can be obtained based on the risk map and the to-be-early-warned grid. And carrying out accurate risk early warning on the target aircraft.

The utility model discloses a four-axis unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicle flight, the four-axis unmanned aerial vehicle comprises a fuselage, four flight assemblies are installed on the fuselage, and a battery used for providing electric energy for the flight assemblies is installed at the bottom of the fuselage; the flying assembly comprises a flying motor mounted on the fuselage, a rotating seat is fixedly mounted on an output shaft of the flying motor, and two flying blades which are arranged in a central symmetry manner are distributed at the two ends of the rotating seat; wherein the aircraft body is further provided with an adjusting assembly matched with the flight assembly, the adjusting assembly comprises two adjusting seats, the two adjusting seats are rotationally connected to the two ends of the rotating seat, and the flight blades are installed on the adjusting seats in a one-to-one fastening mode. The four-axis unmanned aerial vehicle solves the technical problem that the attack angles of the flight blades of the four-axis unmanned aerial vehicle in the prior art are difficult to adjust.

The present invention discloses a dual-hub route network optimization method and system, which belongs to the field of civil aviation flight technology. By obtaining input indicators, output indicators and environmental variables for evaluating the efficiency of the dual-hub routes to be optimized, a dual-hub route efficiency evaluation index system is established, the efficiency of the dual-hub routes is evaluated, and the technical efficiency value of each dual-hub route to be optimized is obtained. In order to analyze the operating characteristics of the dual-hub airports, the principles of reducing the overlap rate, efficient operation of the route network, passenger convenience and minimum route adjustment are proposed. With the goals of minimizing route overlap, minimizing route efficiency mismatch, minimizing passenger departure airport selection cost and minimizing route flight adjustment, a dual-hub route network optimization model is constructed and solved, and the network layout of the dual-hub routes is optimized to obtain the optimization results. The method evaluates efficiency before optimization, improves the overall route efficiency of the dual-hub, and can achieve differentiation and efficiency of the dual-hub route network.

The invention discloses a single-seat electric vertical take-off and landing aircraft, which relates to the technical field of flight and comprises an aircraft body, a rotor wing structure and a duct structure. The rotor wing structure comprises two first rotor wings, two second rotor wings and two third rotor wings. The duct structure comprises a first duct and a second duct, and the thrust directions of the first duct and the second duct are opposite. According to the scheme, the first rotor wing, the second rotor wing and the third rotor wing are deployed in a non-coaxial distributed mode, the problem of aerodynamic interference existing between coaxial rotor wings can be avoided, reduction of extra power loss is facilitated, meanwhile, through cooperation of the first duct and the second duct on the same side, when a single rotor wing or duct fails, the first duct and the second duct on the same side are matched, and the rotor wing or the third rotor wing cannot be damaged. The thrust compensation of the duct on the other side is used for quickly complementing part of lift gaps, stable yaw control torque can be output through the accurate matching of reverse thrust, and the flight stability and safety of the aircraft in a single-shot failure scene are effectively improved.