158 results about "Flight simulator" patented technology

The invention relates to the technical field of flight simulation control and precision measurement, provides a precise positioning method, system and device for a three-dimensional adjustable connecting piece of a flight simulator and a storage medium, and solves the problems of flight simulation control and precision measurement. The method comprises the following steps: acquiring the real-time stroke length of a motion control rod, rotation angle change data and a connecting piece vibration image, outputting a displacement prediction parameter through a platform kinematics model, and generating three-dimensional point cloud data; performing sub-pixel identification and distortion compensation on the image through a mark point identification algorithm to generate a three-dimensional visual coordinate; fusing the point cloud and the visual data, and processing through a Kalman filter to obtain a space pose offset; finally, a displacement compensation instruction is generated, the pose of the connecting piece is adjusted through a closed-loop controller, and accurate positioning of the connecting piece relative to a flight target reference coordinate system is achieved. According to the invention, the accuracy and stability of the pose control of the connecting piece in the dynamic vibration environment are improved.

The invention belongs to the technical field of flight simulator maintenance, particularly relates to a flight simulator predictive maintenance method based on machine learning, and solves the problems that existing maintenance depends on regular inspection and passive maintenance, fault early warning lags behind, and the false and missing report rate is high. The method comprises the following steps: acquiring historical operation data, sensor time sequence data, fault records and environmental parameters of a flight simulator, and carrying out cleaning, labeling and feature fusion preprocessing on the historical operation data, the sensor time sequence data, the fault records and the environmental parameters; constructing a composite health feature set containing statistical features, dynamic health state values and aerial material reliability parameters; a mixed prediction model (random forest feature screening + LSTM time sequence prediction + adaptive correction reliability evaluation) is adopted to train a model, prediction result fusion analysis and multistage decision rule post-processing are combined, and a maintenance work order and a spare part demand plan are output. According to the method, the accuracy and timeliness of fault prediction are improved, the maintenance conversion from passive response to active pre-judgment is realized, and the maintenance cost and the non-planned shutdown risk are greatly reduced.

The invention relates to the technical field of large language models, provides an automatic flight simulator interface code generation method, system and device based on a large language model and a storage medium, and solves the problems of low generation efficiency, poor accuracy and poor system adaptability of flight target interface codes. The method comprises the steps of obtaining interface data of multiple external devices of a flight target, and converting the interface data into structured input data after noise filtering and key information extraction; deeply analyzing the data by using a deep learning and semantic understanding algorithm, extracting key semantic information and generating an interface code template; instantiating the template content in combination with the example data and the interaction rule to generate a target code; generating a multi-scene test case based on a test case algorithm, and verifying code correctness, stability and performance; testing and performance results are comprehensively analyzed, model parameters and training data are dynamically adjusted, and closed-loop automatic code generation is achieved. According to the method, the generation efficiency, accuracy and system adaptability of the flight target interface code are improved.

A motion cueing system for a flight simulator includes a motion system controller configured to generate actuation commands for a movable simulator platform. The actuation commands are based on at least one of: an absolute attitude of a simulated aircraft; or a weighted function of a groundspeed of the simulated aircraft.

The invention belongs to the technical field of flight simulation training equipment control, and particularly relates to a full-motion flight simulator teacher seat adaptive control method, system and equipment. The problem that in the prior art, passive safety protection exists, high-frequency vibration interference exists, and dynamic working condition self-adaptive capacity is lacked, so that the posture imbalance risk of a teacher is caused is solved. The method comprises the steps that platform motion data, teacher skeleton key points and pressure distribution data are collected in real time, the current flight working condition is recognized after multi-source fusion processing, and the weight proportion of all data sources in deviation calculation is dynamically determined; by calculating the deviation between the weighted current posture of the instructor and the standard posture, a multi-direction self-adaptive adjustment instruction is generated to drive the seat to conduct displacement and angle adjustment, closed-loop adjustment is conducted on the basis of the residual deviation till the precision requirement is met, and active safety protection and intelligent self-adaptive adjustment of the seat are achieved.

The invention belongs to the technical field of flight control, particularly relates to a simulation control method and device for a control load system and a storage medium, and aims to solve the problem of limited effect during simulation control of the control load system in the prior art. The method comprises the following steps: acquiring manipulation input data; carrying out filtering processing on the joystick force / torque data, and carrying out dynamic simulation on the control load system through a pre-constructed digital twin system based on the filtered joystick force / torque data and the control position data so as to determine a virtual force / torque track of the control load system for responding to the control input data; acquiring current flight parameters of the flight simulator, and resolving according to a preset aerodynamic model to obtain a reference force / torque trajectory; and taking the reference force / torque track as a control target, performing optimization solution on the virtual force / torque track, and determining an actuator driving instruction. According to the method, the effect is better when the control of the control load system is executed.

The invention belongs to the technical field of flight simulation training equipment, particularly relates to an intelligent temperature control system for a flight simulator cabin, and solves the problem that the requirements of flight simulator temperature control on multi-dimensional physiological perception fusion, multi-target collaborative optimization and rapid personalized adaptation and active safety protection of new pilots cannot be met in the prior art. According to the method, a multi-modal sensing layer processes multi-channel skin physiological data, physical environment data and pilot electrocardiosignals, a human body heat balance equation for blood flow correction is constructed, and physiological feature vectors including predicted core body temperature, predicted average votes and predicted dissatisfaction percentage are generated; the decision-making layer generates a temperature control instruction and a confidence evaluation value through a meta-learning model, a reward function is in a four-dimensional dynamic weighting form, and the weight is adjusted through an IF-THEN rule according to the state; and the dynamic execution layer adopts a PID closed loop to adjust the partition temperature and triggers response in a grading manner. Accurate and personalized temperature control is achieved, and the training quality and safety are guaranteed.

The application discloses a torque transmission device of an airplane simulation pedal and a servo motor, belongs to the technical field of airplane pedal simulation, and is used for airplane simulation driving training, and improves the authenticity and stability of simulation training. The application sets a transmission mechanism and a force feedback mechanism in a fixed support, the force feedback mechanism is rotationally connected with the transmission mechanism and provides feedback force to the transmission mechanism, forward or backward force is applied to a foot pedal during operation and is transmitted to a gear potentiometer through the transmission mechanism, signals are collected through the gear potentiometer and are fed back to a server, the server and software realize the posture of the forward and backward directions of the airplane simulation pedal, force feeling is provided through the action of the servo motor, the pilot has the real feeling of real machine control, and the authenticity and stability of airplane simulation training are improved.

This application relates to a joystick device and a flight simulator. The joystick device includes a housing, a joystick shaft, and a connecting wire. The joystick shaft is connected to the housing and has a through hole that connects the interior and exterior of the housing. The connecting wire is movably disposed in the through hole; the connecting wire has a first end and a second end, the first end being disposed inside the housing and the second end extending outside the joystick shaft. The housing contains a wire receiving space, within which at least a portion of the connecting wire is bent and movably disposed. At least two rib assemblies are provided on the inner wall of the housing, and the first end of the connecting wire is fixed by engaging two adjacent, spaced-apart rib assemblies. By using two rib assemblies to hold and fix the connecting wire, and by providing a wire receiving space within the housing for bending the connecting wire to allow for its extension and retraction, the structure is simple and occupies little space.

The application relates to the technical field of signal processing, and provides a signal docking method, a signal docking device, equipment and a storage medium, the method comprises the following steps: obtaining to-be-docked signals between a flight simulator cockpit simulation device and a real machine system, obtaining corresponding signal conversion rules according to the signal types of the to-be-docked signals, and performing conversion processing on the to-be-docked signals according to the obtained signal conversion rules to obtain target signals for docking. Different conversion rules are used to perform conversion processing on different types of signals, signal docking between the cockpit simulation device and the real machine system is realized, for different real machine systems, only the conversion rules need to be adaptively modified during signal docking, the cockpit simulation device itself does not need to be modified, so that program architecture adjustment and test verification of the cockpit simulation device and interface protocol change can be avoided, the workload during signal docking is reduced, and the processing period of signal docking is shortened.

This invention proposes an efficient system and method for processing objective data from helicopter flight simulators. The system includes a data preprocessing module for preprocessing acquired complete flight data, including data fusion and time-series correction; a data segmentation module for segmenting the raw simulator objective data based on helicopter configuration, control variable changes, and flight status to obtain segmented data; a batch processing module for providing a batch processing entry point for multiple sets of segmented data, simultaneously importing multiple sets of segmented data and multiple data parameters into one or more other processing modules for processing; an outlier removal module for identifying and removing outliers from the batch-processed segmented data; a curve fitting module for correcting the data after outlier removal; and a filtering module for recovering the true information as much as possible from the segmented data containing interference.

The present application relates to a kind of based on rate of change feedback regulation's steering load friction simulation method, system, equipment and medium, method includes: the speed generated by motor of flight simulator is obtained and is normalized;After the speed after normalization is optimized and error and error differential processing;PID control output calculation is then carried out, and proportion term and differential term are obtained;Using slip rate limiter to calculate correction factor and for adjusting proportion term and differential term;Using the proportion term and differential term after adjustment to calculate normalized friction, and convert into actual friction.The method of the present application can automatically adjust friction model parameters according to actual operating state, without manual intervention, greatly reduce the debugging workload;Through dynamic parameter adjustment, more aggressive parameter setting is used when stable, realize faster friction commutation, while automatically relaxing parameter when steering load system tends to be unstable can ensure stability.

The invention provides a personalized training subject adaptive generation and recommendation method for an unmanned aerial vehicle driver, and the method comprises the steps: collecting environment dimensions and physiological and psychological state data through a flight simulator and wearable sensing equipment, carrying out the time-space alignment and normalization processing, discretizing situation parameters through the combination of the statistical features of a sliding time window and a clustering algorithm, and carrying out the adaptive generation and recommendation of a personalized training subject. Forming a standardized situation mode label set; performing off-line modeling on a situation compensation function library by utilizing historical behavior data and situation characteristics to realize accurate evaluation on various situation influence coefficients; in the real-time evaluation, the skill score and the situation adjustment amount are dynamically fused through the gating proportion parameter, personalized correction is carried out based on the personal historical offset characteristics, the stable and adaptive calibrated skill score is output, and the fairness, accuracy and individualization level of training evaluation are effectively improved.

This application relates to the field of eyepoint data compensation technology, providing a method and system for compensating eyepoint data in flight simulators, solving the problems of poor real-time performance and low accuracy of eyepoint data in flight simulations. The method includes: establishing a shared memory region between the simulation logic processing module and the eyepoint data sending module of the flight simulator; this region contains updated state variables in the form of frame IDs and a first-in-first-out shared eyepoint data area; after completing a frame attitude calculation, the simulation logic processing module updates the frame ID; the eyepoint data sending module obtains the latest eyepoint data through the position corresponding to the latest frame ID; then, combined with the instructor's station settings, airspeed, and ground speed data, the aircraft attitude mode is determined to be stationary, stable, or maneuvering; finally, linear interpolation is used for the stable mode, and a pre-trained lightweight LSTM is used for the maneuvering mode to predictively compensate the latest eyepoint data, obtaining the compensated data. This application improves the real-time performance and accuracy of eyepoint data in flight simulations.

The present application relates to the technical field of aircraft operating mechanism, in particular to a drive-control integrated aircraft side stick operating mechanism, which comprises a box body, a controller and a driver, a roll transmission shaft is rotatably supported in the box body, a U-shaped decoupling mounting seat is fixedly connected to one end of the roll transmission shaft, a pitch shaft is horizontally supported in the U-shaped decoupling mounting seat, a base is fixedly sleeved on the pitch shaft, a handle connecting rod and a handle assembly are sequentially connected to the upper end of the base, a roll motor drives a rocker arm I through a rocker arm II and a transmission connecting rod I, the rocker arm I is hinged to the roll transmission shaft, a pitch motor drives a fixed head through a rocker arm III and a transmission connecting rod II, and the fixed head is fixedly arranged at the end of the pitch shaft. The present application provides a drive-control integrated aircraft side stick operating mechanism with high integration, ultra-small volume, double-channel synchronous force sensing, microsecond-level real-time bus communication and plug-and-play, which is particularly suitable for the demand of high-fidelity, high-reliability and small-sized operating device of high-level flight simulator.

The invention discloses a structural parameter optimization method of a Stewart platform, and belongs to the technical field of parallel robots. The method comprises the following steps: firstly, establishing a mathematical model of a Stewart platform, carrying out degree-of-freedom analysis on the platform, and establishing a kinetic equation based on a positive and inverse kinematics relationship and a Lagrange method; then determining an optimization target which covers a working space, rigidity, motion precision and stability; on this basis, a particle swarm optimization (PSO) algorithm is adopted to carry out global optimization on key parameters such as branch length, platform layout, driver position and the like, and a fitness function is utilized to comprehensively evaluate platform performance; and finally, inputting an optimization result into finite element analysis (FEA) and multi-body dynamics simulation (MBD) software for verification. Experimental results show that the working space of the Stewart platform can be remarkably expanded, the motion precision and rigidity of the Stewart platform are improved, stress distribution is improved, and the overall stability is enhanced. The method breaks through the limitation of traditional empirical design and single-target optimization, has the advantages of high optimization efficiency, high global search capability and high convergence speed, is suitable for scenes such as flight simulators, precision machining and spaceflight test platforms, and has wide engineering application value.

The application relates to the technical field of electromechanical control of flight simulation training equipment, and provides a flight simulator corridor bridge safety control method, system, equipment and storage medium, which solves the problems of poor running stability and low control precision of the corridor bridge under load change. The method comprises the following steps: collecting height sensing signals and stress distribution signals in the lifting process of the corridor bridge, obtaining height data and stress distribution data through signal conditioning and analog-digital conversion processing, analyzing the real-time load distribution state according to the height data and the stress distribution data, and generating an electric cylinder adjustment instruction and a pre-tightening force adjustment instruction to realize dynamic compensation of the gravity center deviation; combining a fuzzy PID control model to generate a lifting motion control signal, processing the corridor bridge attitude estimation data through an attitude estimation algorithm, and correcting the motion control signal according to the corridor bridge attitude estimation data, so that high-precision smooth control of the lifting process of the corridor bridge is finally realized. The application improves the running stability and control precision of the corridor bridge under load change.

The invention discloses a multi-rotor manned flight simulator based on a Stewart platform, and belongs to the technical field of rotor unmanned aerial vehicles. The multi-rotor manned flight simulator based on the Stewart platform comprises a rotor unmanned aerial vehicle body, the rotor unmanned aerial vehicle body comprises a rack, first servo motors and folding propellers, and four sets of servo motors are symmetrically and fixedly distributed on the side face of the rack; the three-degree-of-freedom parallel mechanism comprises a fixed platform, a movable platform and driving branch chains, the fixed platform is fixedly connected to the lower side of the rack, and the fixed platform and the movable platform are hinged through a plurality of driving branch chains; the driving branch chain comprises a second servo motor, a ball screw and a telescopic rod. The second servo motor is fixedly connected to the lower side of the fixed platform and connected with the ball screw through a coupler. And the manned cabin is rotationally connected to the lower portion of the movable platform and used for bearing passengers, and the stability and riding comfort of the cabin are remarkably improved by means of the active control characteristic of the Stewart platform.

The present application relates to aerospace ground simulation experiment technical field, especially relates to a kind of for docking ground test large aerospace cabin section five degrees of freedom simulation device. Including two-dimensional drive unit and being set on two-dimensional drive unit active attitude setting unit, brake unit, plane motion measuring sensor and yaw unit, wherein 17T aircraft simulation piece is located in brake unit, active docking mechanism and passive docking mechanism are respectively arranged at the two ends of 17T aircraft simulation piece, active attitude setting unit and yaw unit are used to adjust the pitch, roll and Z attitude of 17T aircraft simulation piece;Docking ring gravity balance unit is arranged above active docking mechanism, for real-time balancing the gravity of active docking mechanism;Brake unit is used to brake 17T flight simulator, plane motion measuring sensor is used to measure motion parameter.The present application improves the precision and reliability of docking simulation, and can be used to verify the docking characteristics of manned lunar docking mechanism.

The invention discloses a simulation system and method of a flight simulator, relates to the technical field of flight simulation, and can solve the problem that flight simulation is not perfect enough. The system comprises a simulation cabin, an operation loading module and a simulation calculation module, the simulation cabin comprises a simulation control instrument; the simulation calculation module comprises a target physical calculation engine, and a flight calculation model is deployed in the target physical calculation engine; the operation loading module is used for acquiring a manipulation instruction based on the simulation manipulation instrument in real time and transmitting the manipulation instruction to the simulation calculation module; the simulation calculation module inputs the control instruction into a target physical calculation engine, the target physical calculation engine is used for solving a flight simulation result when the aircraft takes off on the ski-jump deck, and the flight simulation result comprises flight attitude information, flight motion information and collision information; the collision information is used for indicating the collision information of the aircraft and the ski-jump deck, and determining the ski-jump take-off effect of the flight simulator according to the flight simulation result in real time.

The application relates to the technical field of data driving, and provides a flight simulator simulation model correction method and device based on data driving, which solves the problems of poor consistency between a simulation model state and real data and low dynamic correction efficiency. The method comprises the following steps: identifying a current compound flight state of a flight target according to flight parameters of the flight target, wherein the flight parameters comprise counter-driving data; determining a deviation degree according to key parameters and secondary key parameters corresponding to the compound flight state; selecting a corresponding target state matching method according to the deviation degree and the compound flight state, and performing state matching according to the target state matching method; and after successful matching, calling a controller of a corresponding channel according to the compound flight state or a current flight stage, and correcting the state of a simulation model corresponding to the flight target through an existing control mode. The application improves the consistency between the simulation model state and the real data and the dynamic correction efficiency.

1. Name of the product in this design: Rotary Handle. 2. Purpose of this design: As a control handle for flight simulators or other equipment. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: 3D view 1.

The invention relates to the technical field of UDP communication, provides a flight simulator signal acquisition and transmission method, system and device based on UDP communication and a storage medium, and solves the problems of low transmission reliability and poor real-time performance of a flight target signal in a limited bandwidth environment. The method comprises the following steps: collecting multi-source heterogeneous signal data generated by a flying target; packaging the multi-source heterogeneous signal data into a UDP (User Datagram Protocol) data packet according to a preset data structure, and processing the UDP data packet by adopting a dual-core processor; transmitting the processed UDP data packet to the daisy chain network, generating a bandwidth allocation scheme based on the processed UDP data packet, and dynamically adjusting the transmission bandwidth of the processed UDP data packet according to the bandwidth allocation scheme; and transmitting the processed UDP data packet to the target avionics system according to the adjusted transmission bandwidth. According to the invention, the transmission reliability and real-time performance of the flight target signal in a limited bandwidth environment are improved.

The present application belongs to the technical field of flight simulators and throttle levers, and particularly relates to an eVTOL simulator throttle lever control system and method, aiming to solve the problems of being unable to adapt to the complex and diverse flight modes of eVTOL, non-smooth switching, and inconvenient hardware switching. The present application can switch back to the centering / non-centering mode in real time through a servo control unit, control each flight mode by customizing a torque model, does not need to manually modify the hardware, and quickly responds to changes in flight modes. Through an adaptive Sigmoid transition algorithm, torque smooth transition is achieved. The torque model and PWM signal algorithm of multi-mode adaptation accurately match the control requirements of different flight modes. The dual-path position acquisition and fault backup design improves the reliability of the equipment. The present application effectively improves the authenticity, safety and efficiency of simulation training, and meets the training needs of eVTOL pilots.

The application discloses a kind of aircraft special situation training quality evaluation model training set design methods of flight simulator, including step one, data acquisition, step two, data preprocessing, step three, the calculation of SHAP value, step four, feature weight calculation and weighted adjustment, step five, the retraining of model, step six, the determination of aircraft special situation training feature parameter, step seven, the building of evaluation model training set;The application is collected and preprocessed to flight simulator training data, and the method of using SHAP value is combined with weighted random forest model to select feature parameter, to build scientific, effective training quality evaluation model training set, not only can improve the efficiency and accuracy of data processing, but also can significantly improve the objectivity and reliability of special situation training quality evaluation, provide solid guarantee for the cultivation of pilot and flight safety.

This invention belongs to the field of flight simulator maintenance technology, specifically relating to a machine learning-based predictive maintenance method for flight simulators. It addresses the problems of existing maintenance methods relying on periodic inspections and passive repairs, delayed fault warnings, and high false alarm / missing rate. This invention acquires historical operational data, sensor time-series data, fault records, and environmental parameters from the flight simulator, and performs preprocessing including cleaning, labeling, and feature fusion. It constructs a composite health feature set containing statistical features, dynamic health status values, and aircraft material reliability parameters. A hybrid prediction model (random forest feature selection + LSTM time-series prediction + adaptive correction reliability assessment) is used to train the model. Combining prediction result fusion analysis and multi-level decision rule post-processing, maintenance work orders and spare parts demand plans are output. This invention improves the accuracy and timeliness of fault prediction, realizing a shift from passive response to proactive prediction in maintenance, significantly reducing maintenance costs and the risk of unplanned downtime.

The application discloses a flight simulation model and a modeling method for a variable stability flight simulator, and belongs to the technical field of flight simulation. The flight simulation model comprises an interface control module, a variable aerodynamic simulation module, a variable flight control simulation module, a physical property simulation module and a six-degree-of-freedom motion simulation module. The interface control module defines external data to be received. The variable aerodynamic simulation module establishes an aerodynamic derivative interpolation table and an aerodynamic coefficient expression according to a nonlinear aerodynamic data package, and superimposes the influence of externally configured aerodynamic parameters on the aerodynamic coefficients as an increment by reconstructing the aerodynamic coefficient expression. The physical property simulation module outputs the weight and inertia of an airplane. The six-degree-of-freedom motion simulation module calculates the motion state of the airplane. The variable flight control simulation module constructs flight control laws under different instruction types, and switches corresponding control laws and control gains in real time according to external configuration. The flight simulation model realizes double adjustment of aerodynamic parameters and flight control laws in the same flight simulation model.

A drive unit for air vehicle, which allows building the vertical take-off and landing vehicles, intended for use, for instance, in the production of flying taxis, as well as in the model-making branch and in the toy industry.The drive unit is composed of the air channel, in the form of a straight segment of a tube with circular section, which has fans with engines fixed on its both ends. The vertical draft force outlet-inlet nozzle opening is located between fixed fans of the drive unit.

1. Name of the product in this design: Control Panel. 2. Purpose of this design: This design is intended to be used as a control panel for a flight simulator. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: 3D view 1.

1. Name of this design product: Force Feedback Flight Simulator Base. 2. Purpose of this design: For use as a base for a force feedback flight simulator. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: 3D view 1.