37 results about "Flight (process)" patented technology

The invention provides a flight data packet data augmentation method, system and medium of a flight simulator. The flight data packet data augmentation method adopts a flight data packet data augmentation method based on the principle of flight mechanics, combines a Markov chain model and a historical flight data packet, performs data augmentation on the basis of real flight data, determines the state transition probability according to the historical actual flight data, then uses the Markov chain model to simulate the sequence change of the flight state, generates a flight state sequence, and calculates the flight attitude, speed, attitude angle, thrust and other changes in different flight stages in each state in combination with a random process, so as to generate flight data that is more in line with actual physical laws, ensure that the changes in engine parameters match the flight state of an aircraft, and constrain a physical model based on flight dynamics and aircraft parameters, so as to better simulate the dynamic changes and coherence in the flight process, and improve the authenticity and scientificity of the augmented data.

The invention discloses a carrier rocket flight load analysis method based on flight measurement data, and relates to the technical field of spaceflight, and the method comprises the steps: measuring a flight load in a rocket flight process, and obtaining actual flight strain data and actual flight trajectory data; according to the actual flight strain data and a pre-constructed load-strain corresponding relation, calculating a rocket body total load of each station on the rocket body; calculating the rocket body static load of each station in the actual flight process by using the actual flight trajectory data; subtracting the corresponding static load of the rocket body from the total load of the rocket body at each station to obtain the dynamic load of the rocket body at each station; and optimizing the flight load dynamic load theoretical calculation method by using the rocket body static load of each station and the rocket body dynamic load of each station to obtain an optimized flight load calculation method. The rocket body structure load in the actual flight process can be obtained through load measurement in the flight process, and therefore the static load of actual flight and the dynamic load of actual flight are obtained in a back-stepping mode.

The invention discloses an aircraft performance monitoring method, device, terminal and system and a storage medium, and the method comprises the steps: obtaining a preprocessed flight data stream from an airborne flight data preprocessing device in the flight process of a target leg, analyzing and processing the flight data meeting the effective leg screening condition in the preprocessed flight data stream to obtain the flight data of the effective leg; based on the flight data of the effective leg, calling an embedded performance factor analysis logic to carry out performance factor analysis so as to obtain a performance factor of the effective leg; and in response to a flight end instruction of the target leg, displaying a performance monitoring result on a display based on the performance factor of each effective leg. According to the invention, while the timeliness of airplane performance monitoring is improved, the interference on airborne system data is avoided, the safety is ensured, and an airplane crew can master the performance condition of an airplane in time.

The invention provides a flight stage determination method and device in a flight process, a medium and equipment, and relates to the technical field of data processing, and the method comprises the steps: obtaining a speed-height array list ZS corresponding to a target aircraft executing a flight task in response to the received ADS-B data returned by the target aircraft executing the flight task; and inputting the ZS and the QF into an HMM (Hidden Markov Model) to obtain a prediction result, marking the prediction result until two predicted target segmentation points are obtained, and ending the prediction. According to the method, the speed and the height serve as the observation sequence of the HMM model, the HMM model can predict the hidden state corresponding to the next ADS-B data more conveniently, and due to the learning ability of the HMM model, the predicted result is more accurate.

The application provides an aerodynamic parameter identification method based on an improved physical information neural network, comprising: obtaining a target flight state quantity in a flight process of an aircraft; inputting the target flight state quantity into the improved physical information neural network to obtain an aerodynamic parameter perturbation quantity, the aerodynamic parameter perturbation quantity being a difference quantitative value between a nominal aerodynamic parameter and an actual aerodynamic parameter in flight, a loss function of the improved physical information neural network being an integral loss function, the integral loss function establishing a connection between a dynamic model containing an estimated value and a real dynamic characteristic; and determining the actual aerodynamic parameter according to the aerodynamic parameter perturbation quantity and the corresponding nominal aerodynamic parameter. Through implementation of the application, the dynamic model containing the estimated value is connected with the real dynamic characteristic in an integral manner, correct dynamic information is ensured to be learned by the neural network in a training process, the accuracy of the aerodynamic parameter is improved, and the training difficulty is reduced.

A flight method for a moving body including a detection unit, the method includes: a first flight process of flying while the detection unit detects a surface of a normal portion other than a specific portion of a crane; and a second flight process of flying while the detection unit detects a surface of the specific portion of the crane in a state where at least one of a position, a turning angle, and a boom angle is different, compared to the first flight process.

1. Name of the Design Product: Flight Controller of Drone. 2. Use of the Design Product: The flight controller (flight control system) is the core component of a drone, used to control the attitude and altitude of the drone during operation, determine the flight path and route, and is the core system for completing the entire flight process, including takeoff, in-air flight, mission execution, and return and recovery. 3. Design Key Points of the Design Product: Lies in the shape. 4. Picture or Photo that Best Illustrates the Design Key Points: Perspective View.

The invention discloses a track prediction method based on an error reverse neural network, and relates to the field of track prediction, and the method comprises the following steps: obtaining historical track influence data and historical track data, and constructing an influence coefficient list according to the historical track influence data and the historical track data; constructing a track prediction model according to the influence coefficient list, the historical track influence data and the historical track data; acquiring flight influence data, flight path data and corresponding timestamps in the flight process, inputting the flight influence data, the flight path data and the corresponding timestamps into the flight path prediction model, outputting predicted flight path data, performing comparative analysis on the predicted flight path data and the flight path data, and performing correction processing on the flight path prediction model according to a comparison result to obtain the flight path prediction model. Obtaining a corresponding sequence error contribution value according to the timestamp; performing error analysis on the flight influence data to obtain an influence error contribution value; performing error updating on the track prediction model according to the error contribution value, and outputting predicted track data according to the error updating; according to the invention, the accuracy of track prediction is improved.

The invention relates to the technical field of aircrafts, and discloses an aircraft control method and device, an aircraft and a storage medium, when a comfortable motion adjustment instruction of a user for a target flight condition of the aircraft is received, that is, when the user wants to adjust the comfort of the target flight condition, first prompt information is displayed to the user, and the comfort of the target flight condition is adjusted. And guiding a user to carry out driving operation related to the target flight working condition so as to control the aircraft to carry out the current flight process, and collecting flight control parameters of the current flight process. After the current flight process is finished, collecting the comfort level of the user, and when the comfort level fed back by the user for the current flight process meets a comfort level threshold condition, configuring the flight control parameter of the current flight process as a target flight control parameter, and the flight process of the aircraft under the target flight working condition is controlled by using the target flight control parameter, and the comfort adjustment requirement of a user is met.

According to the high-rotation transient turbulent flow actuating mechanism control device and the simulated flight test method provided by the invention, the aerodynamic configuration of a flight body and the air flow field around the flight body are changed by accurately controlling the extension and retraction of the spoiler, so that the aerodynamic force and the aerodynamic moment suffered by the flight body are controlled, and the control effect is realized; that is, the spoiler actuating mechanism drives the spoiler to stretch out and retract through the high-frequency response motor so as to realize continuous, repeated and high-frequency super-agile continuous control, and the high-overload resistance of the actuating mechanism is ensured through the high-overload resistance design and the potting process of a mechanical structure; in addition, a simulated flight test device is also established, and the actuation performance of the turbulent flow actuation mechanism is tested in the simulated flight process. According to the invention, continuous, repeated and high-frequency continuous control can be carried out while high overload can be borne, and a control / actuation mechanism implementation way is provided for realizing guided transformation of a high-rotation flight system.

The invention discloses a flight risk assessment method based on data driving, and the method comprises the steps: collecting multi-dimensional flight state parameters in the flight process of an aircraft, and inputting the multi-dimensional flight state parameters into a flight state deep clustering network to obtain flight state data sets of different clustering categories; an entropy weight approximation ideal solution sorting algorithm is used to calculate the entropy weight of each clustering category and the closeness of the clustering category to an ideal solution; based on the aviation collision risk model, combining the entropy weight and the close degree to construct a flight risk assessment initial model framework; a clustering result and related values are substituted into the initial model framework for training and optimization; and processing the real-time flight state parameters by using the optimized model, and outputting a risk assessment result of the current flight stage. According to the method, the flight state is finely classified, the parameter weight is scientifically determined, and multiple technologies are fused, so that the evaluation accuracy and reliability are improved, and the flight safety of the aircraft can be effectively guaranteed.

The invention discloses a flight program verification method based on an integrated navigation system, and relates to the technical field of navigation, and the method comprises the steps: simulating a first flight path of an airplane in a preset scene in a simulation system based on a flight program, and setting a plurality of obstacles in the preset scene; the simulation error is injected into a simulation system, corresponding target positions, target postures and target speeds of the aircraft at different moments are calculated through loose integrated navigation, and the target positions, the target postures and the target speeds are fused into a second flight path; calculating a first number of triggered obstacle alarms and a second number of triggered obstacle alarms in a first flight path during operation of the aircraft; and calculating a first average number and a second average number, dividing the second average number by the first average number to obtain a threshold score, and determining that the flight program is qualified when the threshold score is greater than or equal to the target threshold. By means of the technical scheme, the accuracy of verifying the flight program can be improved, and then the safety of the aircraft in the flight process can be improved.

The invention relates to the technical field of communication, and provides an aircraft path planning method, device and equipment based on communication optimization, and a medium, on one hand, mobile communication data of a monitoring area is collected in an auxiliary manner by using a ceclay packet filter, nanosecond timestamp marking can be realized, and thus the time delay measurement precision is improved; on one hand, in the flight process, a mobile communication service quality three-dimensional thermodynamic diagram of a monitoring area is generated based on a height attenuation factor and mobile communication data, the mobile communication service quality of a three-dimensional space can be accurately predicted, and an accurate real-time obstacle avoidance decision basis is provided for subsequent aircraft path planning; and on the other hand, the cost value of each candidate path is calculated, the candidate path with the lowest cost value is selected as the target path, and the target aircraft is controlled to fly to the flight end point according to the target path, so that more accurate three-dimensional path planning can be realized by introducing the path cost, and the success rate of rapidly and safely arriving at the end point is higher.

The invention relates to the technical field of aircraft four-dimensional motion simulation analysis, in particular to an aircraft four-dimensional motion rapid analysis method based on longitudinal static aerodynamic force simplification, which comprises the following steps: obtaining an aerodynamic data lookup table and an engine data lookup table based on aerodynamic data and engine data of an aircraft; establishing an aircraft four-dimensional motion analysis model for calculating flight state parameters according to the external influence parameters of the aircraft; acquiring a control signal of four-dimensional motion analysis of the aircraft to obtain the external influence parameters in the flight process; analyzing external influence parameters based on the aircraft four-dimensional motion analysis model to obtain flight state parameters; and processing the flight state parameters in the flight process to obtain a flight animation of the aircraft, and taking the flight animation and the flight state parameters in the flight process as analysis results. The method can improve the calculation efficiency of aircraft analysis.

The invention relates to a new-generation information technology, and discloses a method and a system for controlling a flight area of an aircraft, so as to improve the adaptability to a test environment. The method comprises the following steps: calculating a conversion matrix between associated coordinate systems; in the flight process of the aircraft, the coordinates of the current point and the corresponding safe area boundary in the emission coordinate system are solved in real time according to the conversion matrix between the associated coordinate systems, the latitude and longitude information of the current point and the azimuth angle data of the flight test reference trajectory; according to the coordinates of the emission coordinate system corresponding to the safe area boundary, the earth rotation angular velocity of the emission coordinate system and the original point vector diameter of the emission coordinate system, the longitude and latitude corresponding to the safe area boundary are calculated; according to the latitude and longitude of the current point and the latitude and longitude corresponding to the safe area boundary, judging whether the current point is in the safe area range, and if the current point is in the safe area, resolving a normal flight control program; otherwise, resolving the safety control program to enable the aircraft to dive to land.

The application discloses a kind of pilot health index real-time monitoring device, belong to monitoring technical field, including: shell, mounting block, rotating mouth, camera, rotating drive mechanism, central processing unit, alarm;The device of the application is installed in the adaptive position of aircraft, will not increase any burden in the flight process of pilot, at the same time, also will not cause the occlusion of the line of sight in the flight process of pilot, improve the use safety of device.

The invention discloses an aircraft flight time control method suitable for low-altitude economy, and relates to the technical field of aircraft control, and the method comprises the steps: S1, data acquisition, S2, atmospheric environment prediction and ground speed calculation, S3, flight time and scheme judgment, S4, flight time adjustment scheme calculation, and S5, flight process monitoring and adjustment. According to the method, the air route of the aircraft is automatically planned and adjusted through the computer, a traditional manual adjustment mode depending on a driver is replaced, the computer can automatically calculate the optimal adjustment scheme within the required precision through the method, the flight air route meets the adjustment requirement, the problems of inaccuracy, instability and the like caused by human factors are reduced, and meanwhile the adjustment accuracy is improved. Under the scene that multiple aircrafts share the air route, the flight time of each aircraft can be controlled more accurately, potential safety hazards such as meeting in the air are avoided, and the overall flight efficiency is improved.

The invention discloses a high-speed aircraft trajectory planning method and device based on active flow control multivariable coupling, a medium and equipment, and the method comprises the steps: obtaining a first group of correlation coefficients of an aircraft affected by a jet flow, and obtaining a second group of correlation coefficients of the aircraft not affected by the jet flow; replacing the second group of correlation coefficients with the first group of correlation coefficients to obtain a new kinematic equation and a new kinetic equation; determining an aircraft trajectory planning model based on the active flow control system based on the control quantity, the constraint condition, the target function, the new kinetic equation and the new kinematical equation; the aircraft trajectory planning model based on the active flow control system is solved, the target planning trajectory of the aircraft is obtained, the trajectory planning flexibility and efficiency are improved, the controllability and stability of the aircraft in a complex environment are enhanced, and the aircraft trajectory planning method and device are suitable for large-scale popularization and application. Therefore, the trajectory planning system can more intelligently respond to various dynamic changes in the flight process, so that the smooth completion of the flight task is ensured.

The invention discloses a space situation enhancement method and system based on a cortex fusion technology, and relates to the field of aerospace flight attitude perception. In order to solve the problems that an existing space situation perception intervention means cannot take effect in real time, a large number of cognitive resources are occupied and the like, a head tactile stimulation array is adopted in the scheme, flight attitude information is mapped into graded vibration feedback through a cortex tactile fusion technology, and low-delay transmission is achieved through a trigeminal neural pathway. The system comprises a vibration patch helmet, a closed-loop control module and a data transmission unit, stimulation points cover six areas such as the forehead and the top of the head, and single-point and combined vibration prompting is supported. According to the method, secondary cognitive processing of a pilot is not needed, airsickness and flight illusion risks are remarkably reduced, occupation of cognitive resources is minimized, real-time enhancement of space situation awareness in the flight process is achieved, and the method is suitable for flight auxiliary scenes of various aircrafts.

The application provides a flight parameter reproduction and simulation flight simulation state instant switching control method, system and medium, which is based on the data recorded by the trainee during the simulation flight training task, and the flight simulation data driven flight reproduction is performed, the control load data of the flight reproduction is obtained, the deviation is obtained by comparing the control load data with the standard control load data, the reproduction channel arbitration is performed according to the deviation, and the real-time operation data is switched to reproduce, that is, the real-time control data of the trainee from the instructor is received, the flight training data of the trainee is replaced by the real-time control data of the instructor, and according to the comparison representation of the real-time control data of the instructor and the flight process of the aircraft, the dynamic synchronization of the flight parameter reproduction and the simulation flight simulation state instant switching is performed, the historical / real-time control difference is superimposed and displayed, the visualization of the evaluation and review process is realized, and the timeliness and accuracy of the flight simulation training teaching feedback and evaluation are significantly improved.

The invention provides a flight parameter reproduction and simulated flight simulation state instant switching control method and system and a medium, and the method comprises the steps: carrying out flight reproduction driven by flight simulation data according to data recorded when a training person executes a simulated flight training task, obtaining control load data of the flight reproduction, and carrying out the simulation of the simulated flight training task; the method comprises the following steps: acquiring data of a control mechanism, comparing the data with standard control load data to obtain a deviation, performing reproduction channel arbitration according to the deviation, and switching to real-time operation data for reproduction, namely receiving real-time control data from a teacher to the control mechanism, replacing flight training data of a student as the real-time control data of the teacher, and outputting the real-time control data. And according to the real-time manipulation data of the teacher and the comparative representation of the flight process of the aircraft, through the dynamic synchronization of flight parameter reproduction and real-time switching of the simulated flight simulation state, the historical / real-time manipulation difference and the visual evaluation and commenting process are displayed in an overlapping manner, so that the timeliness and accuracy of flight simulation training teaching feedback and evaluation are remarkably improved.

The invention discloses an alarm threshold determination method and a related device, and the method comprises the steps: firstly obtaining historical flight data which is used for identifying the state of flight equipment in a historical flight process, and then obtaining a historical alarm threshold through a rule algorithm based on the historical flight data, wherein the rule algorithm is constructed based on the influence weight of the environment data and the flight parameters on the safe flight state of the flight equipment, the influence weight is determined based on artificial experience, and then a corresponding dynamically changing historical alarm threshold can be obtained based on historical flight data obtained in a real scene according to the rule algorithm. And finally, training the machine learning model according to the historical flight data and the historical alarm threshold to obtain a threshold calculation model, so that the threshold calculation model can be applied to a subsequent real flight process to obtain an alarm threshold which adaptively changes according to a real scene, and dynamic adjustment of the alarm threshold is realized. Therefore, the alarm accuracy is effectively improved.

The invention provides a power battery temperature prediction method and device based on eVTOL typical flight characteristics, and belongs to the technical field of aviation engineering such as an aircraft technology, a power technology, an avionics technology and an electromechanical system technology. The method comprises the following steps: collecting time sequence data of current and temperature in real time after the eVTOL takes off, calculating a time-current curve curvature through a high-precision non-equidistant five-point curvature method, and determining a flight state conversion time point; according to typical characteristics of different flight states, fitting a temperature-time change relationship between the take-off stage and the initial stage of the cruise stage through partial data of the take-off stage and the cruise stage; and predicting the temperature change of the remaining voyage in the flight process by using the obtained fitting parameters in combination with the remaining cruise duration and the landing duration. The method has the characteristics of simplicity, high efficiency and high practicability, can predict the temperature change in the later flight period in the initial flight period, provides effective data support for eVTOL power battery thermal management, and lays a foundation for safe flight.

The application relates to a flight data abnormality detection method and system based on a dual-view enhanced Transformer, and belongs to the technical field of aviation safety. The application extends the flight safety abnormality detection task to beyond the traditional overrun event, and aims at the subtle and often undetected abnormality in the flight process. According to the fact that QAR data is a typical form of time series data, the flight safety problem is re-expressed as an abnormality detection task in time series analysis. In addition, in order to solve the challenge of excessive dependence on expert labeled data in flight safety research, an unsupervised abnormality detection model specially designed for QAR data is designed. Finally, according to the sparse characteristics of QAR data, a time series abnormality detection model architecture based on reconstruction is designed. The application can timely identify the condition deviating from the normal flight mode, provide early warning information for airlines, and effectively assist experts in analyzing abnormal flight behavior, and has a wide application prospect.

The utility model discloses a fire-fighting pod and an aircraft, which belong to the technical field of aircrafts, the fire-fighting pod comprises a pod body and a connecting rod, the connecting rod is provided with a first connecting device used for connecting the top of the pod body and a second connecting device used for connecting an arm connector of the aircraft, the first connecting device is located in the middle of the connecting rod, and the second connecting device is located in the middle of the connecting rod. The second connecting device is located at the end of the connecting rod, in the flight process of the aircraft, the cabin body is hung below the aircraft fuselage through the connecting rod, the connecting rod bears force transmitted by the aircraft fuselage and the cabin body and deforms, the connecting rod provides buffering and damping for the cabin body, and the service life of the cabin body and all parts on the cabin body is prolonged.

The application discloses a kind of based on data-driven flight risk assessment method, the method collects the multidimensional flight state parameters in the process of aircraft flight, input flight state depth clustering network obtains the flight state data set of different clustering categories;The entropy weight value and the closeness to ideal solution of each clustering category are calculated using entropy weight approximation ideal solution sequencing algorithm;Based on aviation collision risk model, construct flight risk assessment initial model framework in combination with entropy weight value and closeness;The clustering result and related numerical value are substituted into initial model framework to train and optimize;Real-time flight state parameters are processed using the optimized model, and the risk assessment result of the current flight phase is output.The method classifies flight state by refinement, scientifically determines parameter weight and fuses multiple technologies, improves the evaluation accuracy and reliability, and can effectively guarantee the flight safety of aircraft.

The invention discloses a pilot health index pre-estimation method and system based on a plateau flight process, and relates to the technical field of pilot health index pre-estimation, and the method comprises the steps: obtaining the current flight data in the flight time, inputting the current flight data into various types of pre-estimation models for processing, obtaining each piece of health pre-estimation information corresponding to the duration of the flight time in the future; according to each piece of health pre-estimation information, the model weight of each type of pre-estimation model is calculated by using an objective weighting method, and a health index pre-estimation result is calculated by using each type of model weight and the corresponding health pre-estimation index; obtaining new current flight data of the duration corresponding to each time step according to each time step interval, and updating the future duration and the health index estimation result through the new current flight data; and real-time monitoring and estimation of the health indexes of the whole plateau flight process of the pilot are realized.

The invention discloses a game flight control method and device and electronic device.The method comprises the steps that the flight direction and the flight speed of a current virtual player are obtained; according to the flight direction and the flight speed of the current virtual player, in the process of controlling the current virtual player to fly in the game picture, determining a set angle of a blocking surface according to a flight angle of the flight direction of the current virtual player relative to a world coordinate system and a pre-configured first included angle interval, the pre-configured first included angle interval is used for limiting the included angle between the blocking surface and the flight direction, and the blocking surface is used for simulating the resistance of the current virtual player in the flight process; and setting the blocking surface in a preset range of the current virtual player according to the setting angle of the blocking surface, and in the process, simulating real flight by setting the blocking surface, and providing real flight experience for the player.

The invention discloses a flight quality evaluation method, a storage medium and a program product, and relates to the technical field of aircrafts, and the flight quality evaluation method comprises the steps: responding to an evaluation instruction for a flight system, determining whether the evaluation instruction is an identification instruction, if the evaluation instruction is the identification instruction, obtaining a flight signal, and based on the flight signal, determining whether the flight signal is an identification instruction; determining a corresponding flight system model, and evaluating the flight quality of the aircraft based on the flight system model to obtain an evaluation result; the flight signal is an excitation signal obtained by a flight system and a response signal generated by the flight system in the flight process of the aircraft, and the flight system model has a mapping relation between the excitation signal and the response signal. Flight quality evaluation can be carried out on the aircraft through the flight system model under the influence of the flight environment factors and the state of the aircraft.

The invention belongs to the technical field of aircraft performance design, and particularly relates to a method for designing an aircraft vertical route based on dynamic programming, which comprises the following steps: firstly, determining a fixed task by combing the scene of the whole flight task, constructing the general form of the whole vertical route according to the sequence, and decomposing into a plurality of local vertical routes; then, the flight weight of the cruise height is marked, and each flight process is divided into a plurality of stages through the change of the weight; and setting the flight height of the aircraft at the beginning of each stage as a state, and establishing a relationship between the state and the flight stage. And setting the flight height of the aircraft at the beginning of each stage as a state, and establishing a relationship between the state and the flight stage: increasing a state numerical value to climb, not changing the numerical value to cruise flight, and decreasing the numerical value to descend. Therefore, the task process is processed into a multi-stage decision-making problem, no post-effect is obviously satisfied, and the optimization problem of the vertical air route is processed by using a dynamic planning method.