112 results about "Aircraft safety" patented technology

The invention provides an aircraft digital twinning situation deduction and risk assessment method in a complex meteorological environment, and belongs to the technical field of data processing, the aircraft digital twinning situation deduction and risk assessment method in the complex meteorological environment comprises the following steps: collecting and processing weather data covering parameters such as wind direction and wind speed; obtaining aircraft performance parameters and building a database; and inputting and analyzing the flight plan. By establishing a three-dimensional deduction model including dynamics, weather influence and environment models, aircraft situations under different weathers are deduced, and flight safety, performance and task risks are evaluated. The method has the advantages that weather factors are comprehensively and accurately analyzed, and influences are quantified through data acquisition and processing and a meteorological model; the system is suitable for various aircrafts, can integrate navigation and control systems, and realizes remote monitoring management; risk assessment is scientific and reliable, multiple factors are integrated, powerful support is provided for flight decision making, and aircraft safety and task success rate in complex weather are effectively improved.

The invention relates to the technical field of digital data processing, and discloses an aircraft safety data multi-source heterogeneous data acquisition method, which comprises the following steps of: synchronously controlling multiple types of sensors to concurrently execute physical obstacle three-dimensional investigation, micro-meteorological wind field construction and space electromagnetic spectrum surveying and mapping operation through a single unmanned aerial vehicle platform; and integrating the acquired three types of heterogeneous data into a three-dimensional spatio-temporal data base with a unified timestamp in real time. According to the method, endogenous space-time consistency of multi-source safety data at a collection source is ensured, information dislocation during traditional data fusion is avoided, a data base can truly reflect the instant coupling state of multiple risks, meanwhile, the exploration positioning capacity of the dynamic risks is arranged at a collection end in advance, and the data collection efficiency is improved. And an accurate and reliable decision basis is provided for flight safety assessment.

The invention relates to the technical field of low-altitude aircraft safety monitoring, and discloses a low-altitude aircraft and ground equipment safety monitoring and early warning system, and the system comprises an aircraft monitoring module which is used for collecting the dynamic position data of an aircraft and setting an airspace monitoring interval; the environment sensing module is used for dividing space nodes and analyzing environment data to generate security feature vectors; the risk positioning module is used for extracting key abnormal indexes and establishing risk grading rules; the dynamic prediction module is used for identifying a track correlation mode to calibrate an index and calculating a safety offset; the threshold value optimization module is used for deducing an optimal safety threshold value and generating a risk deviation sequence; and the early warning decision module analyzes the sequence and integrates the sequence into an early warning response decision scheme. The system realizes low-altitude global monitoring, risk analysis and dynamic early warning through multi-module cooperation, improves the accuracy and timeliness of low-altitude airspace safety management, and is suitable for safety guarantee of low-altitude aircrafts and ground equipment.

The invention discloses a multi-source data fusion-based low-altitude aircraft safety assessment method and system, and the method comprises the steps: analyzing the real-time flight data of a low-altitude aircraft, determining key flight parameters, determining the data characteristics of the key flight parameters, and assessing the safety state of the low-altitude aircraft based on the real-time flight data and the data characteristics, thereby obtaining a flight safety state assessment value; constructing a prediction model for prediction based on the historical flight environment data and a preset model to obtain flight environment prediction data; analyzing the flight environment prediction data, determining an environment state coefficient, determining an influence coefficient, and determining an environment influence coefficient based on the two coefficients; and correcting the flight safety state evaluation value based on the environmental influence coefficient to obtain a comprehensive safety evaluation value, and determining the safety level of the low-altitude aircraft based on the comprehensive safety evaluation value. According to the method, the capability of comprehensively monitoring and evaluating the safety state of the low-altitude aircraft is improved, the safety state of the aircraft can be accurately determined, the flight safety level of the aircraft is improved, and the flight risk is reduced.

The invention discloses a method for aircraft thrust imbalance warning and protection. The method comprises the following steps: acquiring thrust rod position angle signals and wheel load state signals of a plurality of engines after an aircraft lands and is grounded; determining whether the thrust states of the plurality of engines are consistent or not based on the thrust rod position angle signal and the wheel load state signal, wherein the thrust states of the plurality of engines comprise a positive thrust state and a negative thrust state; in response to the fact that one or more of the multiple engines are inconsistent with the remaining engine thrust state of the multiple engines, a warning instruction is sent out; and the reverse thrust cover corresponding to the engine in the negative thrust state is locked. The invention further provides a system for aircraft thrust imbalance warning and protection. By means of the method and device, the unbalanced thrust state of the aircraft can be prevented after the aircraft lands, an alarm is given to operation of a pilot, protection is provided, and the safety of the aircraft is guaranteed.

The invention provides a civil aircraft safety perception method and system based on virtual flight, and relates to the technical field of aircraft safety perception. A dynamic and hierarchical three-dimensional wind shear field model is constructed through space-time alignment and fusion of multi-source meteorological data; deep coupling of wind disturbance and aircraft dynamic response is realized based on a small disturbance theory and a flight dynamics model; continuous and dynamic quantification of risks is realized by combining and analyzing flight parameters and a safety threshold value dynamically adjusted based on wind disturbance intensity and utilizing multi-parameter risk level weighted integration; according to the method, the risk coefficient is coupled with the three-dimensional terrain and the virtual flight trajectory, hierarchical color mapping is adopted to carry out visual space visualization, and a complete closed loop from environment modeling to risk early warning is formed, so that the identification accuracy and timeliness of the flight risk in the wind shear environment are greatly improved, and the scientificity and practicability of security situation awareness are enhanced.

The invention relates to an aircraft component intelligent assembly data management system based on compliance verification, and belongs to the technical field of aerospace manufacturing. In order to solve the problems of data dispersion, low verification efficiency and difficulty in quality tracing in the aircraft component assembly process, the system comprises a standard process library construction unit used for constructing an aircraft component assembly standard process library which is clear in classification and contains detailed specifications; the assembly information acquisition unit is used for collecting assembly data in multiple channels and processing the assembly data into a structured data set; the data management system unit is used for integrating multi-source data and analyzing historical data and verification results to form a trend table so as to realize overall management; and the qualification checking unit is used for checking real-time data in multiple dimensions, generating a report and performing synchronous early warning. According to the system, intelligent management of the aircraft component assembly process is realized, the data processing efficiency and accuracy are improved, and the assembly quality and the safety and reliability of an aircraft are guaranteed.

The present invention discloses a method and system for real-time perception of the state of an aircraft's rudder surfaces. The system includes an embedded pressure sensor, an embedded processor, a signal transmission module, and an angle comparison module. The embedded pressure sensor uses a silicon chip and is arranged at specific positions on the front edge and upper and lower surfaces of the aircraft's rudder surface to monitor the pressure signal on the rudder surface in real time. The actual airflow angle and surface flow conditions of the rudder surface are solved based on these surface dynamic pressure information, and compared with the rudder control instructions input by the flight control system to determine whether the rudder angle has reached the specified position and whether flow separation has occurred on the rudder surface. The system and method for real-time perception of the state of an aircraft's rudder surfaces with embedded pressure measurement proposed by the present invention provide a beneficial monitoring means and feedback method for rudder manipulation and flow control during the flight of the aircraft, thereby avoiding aircraft safety accidents caused by rudder jamming or failure.

The invention discloses an aircraft fire simulation and fire extinguishing rescue evaluation system, and belongs to the technical field of aircraft safety. The system comprises an aircraft parameter input module, a fire scene simulation calculation module, a fire extinguishing and rescue strategy deduction module, a multi-dimensional effect evaluation module and a result output and optimization suggestion module, and all the modules realize data interaction through standardized data interfaces. And a closed-loop system of parameter input, dynamic simulation, rescue deduction, quantitative evaluation and optimization feedback is formed. The method solves the problems of inaccurate fire simulation and lack of dynamic quantification of rescue evaluation of a traditional system, can realize accurate reproduction of aircraft fire scenes and scientific evaluation of rescue schemes, provides data support for emergency decision making, and is suitable for fire emergency disposal research of various aircrafts such as civil aviation airliners and freight aircrafts.

The utility model discloses a rotary lever aircraft safety valve microswitch device, and relates to a microswitch device. The switch comprises a switch base, a switch connecting seat, a switch rotating support and a microswitch, a switch rotating shaft is arranged in the switch rotating support and is connected with an inner ring of a torsion spring, one fulcrum of the torsion spring is contacted with one end of the switch rotating plectrum, and the other fulcrum is contacted with the top of the right end of the switch base; one end of the switch rotating plectrum corresponds to the microswitch and is in contact with one fulcrum of the torsion spring, and the other end of the switch rotating plectrum corresponds to the pressing block screw. The device can meet the requirement for accurate feedback of the opening state of the aircraft safety valve.

The present invention belongs to the field of engineering thermophysics / aircraft safety technology, and relates to an observation device for droplet collision with a metal bottom plate and its application. The observation device of the present invention includes a lifting table, a data acquisition device, and a data analysis system. The experimental device can quantitatively measure the dynamic parameters such as the spreading radius, movement and sliding distance, and rebound height of the liquid droplet on the surface of the sample stage. At the same time, based on the light transmittance of the liquid droplet measured by a high-speed camera and the surface temperature of the liquid droplet measured by a high-speed infrared camera, the surface temperature distribution and phase change time of the liquid droplet can be studied. The data analysis uses a MATLAB program independently developed by the laboratory, which ensures the convenience and accuracy of data analysis. The entire system is of great significance for the research on the motion and phase change heat characteristic behaviors, laws, and mechanisms of water droplets impacting a solid cold surface or metal droplets impacting the surfaces of different metal materials.

This invention discloses a dynamic pressure-based method for testing and analyzing hammer shock waves in aero-engines, belonging to the field of aero-engine testing and structural strength design. The method first uses a surge-induced pressure method to generate hammer shock waves at the engine inlet. Based on the flow field characteristics of the air intake outlet section (AIP section) during surge, dynamic total pressure and static pressure measuring points are arranged in a combination of circumferential and radial directions. Pressure signals are synchronously recorded using a high-speed data acquisition system, and four characteristic parameters—surge overpressure, overpressure ratio, loading time, and pressure rise rate—are defined to quantitatively analyze the intensity, spatial distribution, and dynamic process of the hammer shock waves. This invention achieves rapid, accurate, and comprehensive characterization of the aerodynamic load of hammer shock waves, providing reliable input loads directly for the strength design of complex structures such as S-curve air intakes, thereby improving aircraft safety.

The application relates to the field of aircraft control, and discloses a landing gear actuating cylinder control device and a landing gear, which comprise a controller, a main control circuit and at least one standby control circuit, wherein the main control circuit comprises a detection circuit; the detection circuit is arranged at the landing gear actuating cylinder to generate a detection signal; the controller is used for generating an action instruction according to state information of an airplane and sending the action instruction to the main control circuit, so that the main control circuit controls the landing gear actuating cylinder according to the action instruction; the controller is also connected with the detection unit to acquire the detection signal, and when the detection signal does not satisfy a preset condition, the controller controls the standby control circuit to work and sends the action instruction to the standby control circuit. When the main control circuit fails, the standby control circuit is started to work, so that the stability of the landing gear actuating cylinder control system and the safety of the airplane are improved on the basis of preventing multiple controller interference and motor power disputes, so as to prevent the airplane from being unable to take off or land safely due to the failure of the actuating cylinder.

The invention discloses an aircraft countering method and system based on a TD3 algorithm in combination with a diffusion strategy, and relates to the technical field of aircraft safety prevention and control, and the method comprises the steps: an aircraft recognizes a target through a camera, carries out the global search of an image frame, locates the region where the target aircraft is located in the image frame, and carries out the local target tracking; a Kalman filter is combined to estimate a position, position information of a target aircraft is obtained, a binocular depth camera is utilized to carry out environment perception and obtain position information of the aircraft, the position information, the environment information and the position information of the aircraft are transmitted into a pre-trained aircraft countering decision model, and a countering strategy is obtained. And the aircraft reaches the position of the target aircraft according to the trajectory generated by the strategy for physical interception. According to the method, the countering strategy is quickly generated after the target aircraft is detected, and a new countering strategy can be quickly generated when the flight path of the target aircraft is changed, so that efficient strike on the target aircraft is realized.

The application provides an aircraft safety control algorithm test case generation method and system, including: initializing the position of P AB1 ; initializing the longitude and latitude perturbation step and the convergence threshold; calculating the lateral position of P AB1 relative to the AB connecting line; when the absolute value of the longitude difference is greater than the absolute value of the latitude difference, gradually perturbing the latitude of P AB1 according to the longitude and latitude perturbation step, outputting the longitude and latitude and the lateral position of P AB1 ; gradually perturbing the latitude of P AB2 according to the longitude and latitude perturbation step, outputting the longitude and latitude and the lateral position of P AB2 ; when the absolute value of the longitude difference is less than or equal to the absolute value of the latitude difference, gradually perturbing the longitude of P AB1 according to the longitude and latitude perturbation step, outputting the longitude and latitude and the lateral position of P AB1 ; gradually perturbing the longitude of P AB2 according to the longitude and latitude perturbation step, calculating the lateral position of P AB2 relative to the AB connecting line. The technical scheme of the application solves the technical problems of low efficiency and low accuracy in the prior art that test cases of safety control algorithms are manually selected and generated.

The present invention proposes a device and a method for calculating a safe 4D flight path for an aircraft to avoid conflicts with stationary or moving objects. The device according to the invention comprises a flight path safety module that interacts with a flight management system and consists of a conflict risk assessment module and a conflict resolution module. The conflict resolution results in a hierarchically ordered list of solution flight paths, which can be based on a lateral and / or a vertical solution and / or a combined solution, depending on the current state of the aircraft, the type of conflict, and the type of object.

The application discloses a low-altitude flight management and control method, system, device and medium based on satellite-ground broadcast fusion, and relates to the field of low-altitude aircraft safety management and control. The method comprises the following steps: a management and control center generates a wide-area flight permission instruction and sends the instruction to a satellite management and control node; the satellite management and control node broadcasts the wide-area flight permission instruction through satellite broadcasting; a ground management and control node supplements the wide-area flight permission instruction based on the regional management and control requirements of each region, generates regional flight permission instructions of each region, and broadcasts the regional flight permission instructions through ground broadcasting; a low-altitude aircraft determines its flight permission based on the wide-area flight permission instruction and the regional flight permission instruction, executes a flight task, and broadcasts its running state information through ground broadcasting; and a monitoring node generates airspace running situation information based on the running state information, the wide-area flight permission instruction and / or the regional flight permission instruction, and feeds back the information, so that the low-altitude flight management and control efficiency is improved.

The invention relates to the technical field of safe flight of aircrafts, in particular to a low-altitude aircraft safety interval assessment method and device, equipment and a storage medium. The evaluation method for the safety interval of the low-altitude aircraft comprises the steps that a rail car is controlled to run according to a preset track, the rail car carries a navigation system and a communication system of the low-altitude aircraft, and the navigation system and the communication system are in the state where electromagnetic interference signals are applied; in the running process, state information of the rail car is obtained; based on the state information and the preset track, evaluating the track keeping capability of the low-altitude aircraft; and determining the safety interval of the low-altitude aircraft based on the flight path keeping capability. According to the invention, the operation efficiency of the low-altitude aircraft can be improved on the premise of guaranteeing the flight safety.

The invention discloses a control method for gliding parachute-opening landing of an unmanned aerial vehicle, belongs to the technical field of safe landing of the unmanned aerial vehicle, and utilizes the unmanned aerial vehicle to enter gliding and adjust various states and parameters of the unmanned aerial vehicle to enable the unmanned aerial vehicle to meet conditions of safe parachute landing. The method comprises the following steps that an aircraft follows a route in an approaching state, and an automatic accelerator is controlled by speed; in the lifting rate zeroing stage, transverse guidance is closed, longitudinal guidance is controlled by the lifting rate, and an automatic accelerator is closed; in the gliding stage, longitudinal guidance is controlled by speed, and airspeed is equal to recovery speed; in the recovery stage, the longitudinal guidance is closed, the pitch angle is equal to the sum of the increment of the climbing angle and the increment of the attack angle of the parachute opening action, and the recovery system is started and parachute opening is performed until the aircraft lands safely to complete landing.

A simulation testing architecture can be applied to an aircraft monitoring system for an aircraft that includes complex algorithms (such as machine learning algorithms) for sensing objects around the aircraft and controlling the aircraft to avoid such objects. A reference scenario is selected from a plurality of stored scenarios based on a desired set of aircraft safety standards. A stochastic process is applied to generate a large number of conditional variations within a simulated environment, varying weather, objects in the airspace, points of failure, and the like to provide a representative sample of possible aircraft missions and encounters within the selected reference scenario. Synthetic environmental inputs are fed into the aircraft monitoring system software, and the resultant actions of the software are logged. These logs can be used to generate metrics on an encounter-level basis, a scenario-level basis, or across a population of scenarios.

The application discloses a supersonic or hypersonic aircraft safety protection method based on flow control, and is based on unsteady high-frequency pulse flow field excitation, adjusts the frequency and range of low-frequency pressure pulsation of a flow field discontinuity interference zone caused by unsteady motion of the flow field discontinuity, avoids strong coupling of the low-frequency pressure pulsation of the flow field discontinuity interference zone and an aircraft surface structure, and guarantees the integrity and reliability of the aircraft surface structure. The application is applied to the technical field of supersonic or hypersonic aircrafts, and by exerting unsteady high-frequency pulse flow field excitation on the flow field discontinuity interference zone of the supersonic or hypersonic aircraft, the safety protection capability of the aircraft can be effectively improved, by controlling the unsteady motion of the flow field discontinuity and locking at a specific frequency, the range of low-frequency pressure pulsation of the interference zone can be effectively reduced, thereby the vibration of the aircraft surface structure is reduced, and the safety protection of the supersonic or hypersonic aircraft is realized.

A magnesium hydride-based hydrogen storage hydrogen-fueling aero-turbine engine is disclosed, relating to the field of aero-turbine engines. It includes an air intake, fan, high-pressure compressor, combustion chamber, high-pressure turbine, low-pressure turbine, mixing chamber, nozzle, magnesium hydride heat exchanger, magnesium hydride storage tank, and intermediate hydrogen storage tank. Magnesium hydride is used as a carrier for airborne hydrogen fuel, providing hydrogen fuel for the aero-turbine engine. Using magnesium hydride as a hydrogen storage material in a hydrogen-fueled aero-engine offers significant advantages in hydrogen storage system design and aircraft safety. A magnesium hydride heat exchange and hydrogen release device is installed after the core engine outlet. Magnesium hydride is supplied in groups from the magnesium hydride storage tank via a mechanical device for endothermic hydrogen release. The released hydrogen is piped to the intermediate hydrogen storage tank for temporary storage before being supplied to the core engine combustion chamber for combustion. The released magnesium hydride is returned to the storage tank. The high-temperature exhaust gas of the aero-engine continuously provides heat for the hydrogen release of magnesium hydride, eliminating the need for external energy for the hydrogen release process.

This invention discloses a distributed situational awareness and safety decision-making method for manned and unmanned aerial vehicles (UAVs) in collaborative airspace. It dynamically aggregates the spatial topology and relative motion features of the local neighborhood of the aircraft using an EdgeConv graph neural network to generate a collaborative situational representation that incorporates the intentions of both manned and unmanned aircraft. A DRNN-LSTM hybrid model is used to learn temporal situational sequences, enabling a forward-looking quantitative assessment of future conflict risks. Manned aircraft commands are intrinsically embedded as conditional variables in the perception and prediction processes, making the safety-first principle an inherent constraint of the algorithm. Based on the risk assessment results and the constrained situational representation, a safety-first collaborative control command is generated through a distributed policy network, forming an autonomous closed loop of "perception-prediction-decision-execution" after execution. This invention achieves deep fusion of spatiotemporal situational awareness and risk foresight in complex airspace, internalizing manned aircraft safety as the core logic, and effectively improving the safety, adaptability, and mission efficiency of manned and unmanned aircraft collaborative operations.

The application relates to the technical field of digital data processing, and discloses a kind of aircraft safety data multi-source heterogeneous data acquisition method, comprising: through single unmanned aerial vehicle platform, synchronous control multiple sensors concurrent execution physical obstacle three-dimensional survey, micro-meteorological wind field construction and space electromagnetic spectrum mapping operation, the three kinds of heterogeneous data collected are integrated into three-dimensional space-time data base with uniform time stamp in real time. The application ensures that the multi-source safety data has endogenous space-time consistency at the collection source, avoids information misplacement during traditional data fusion, so that the data base can truly reflect the real-time coupling state of multiple risks, and the exploration positioning ability of dynamic risk is also placed in the collection end, providing accurate and reliable decision basis for flight safety evaluation.

The invention discloses a four-rotor aircraft data driving control method breaking through bandwidth constraint under hostile attack. The method specifically comprises the following steps: establishing a kinetic model of a four-rotor aircraft; converting the obtained kinetic model into an equivalent dynamic linearization equation by using a dynamic linearization method; designing a criterion function, and designing a data driving control method of the four-rotor aircraft; an event triggering mechanism is introduced, denial of service attack is considered, and then the final four-rotor aircraft safety event triggering data driving control method is obtained through arrangement of the obtained control method. According to the method, model-free adaptive control is applied to attitude control of the four-rotor aircraft, the advantages of PID are combined, malicious denial of service attacks are considered, an event triggering mechanism is introduced, the good flight quality of the aircraft is guaranteed, system bandwidth resources can be saved, and the working time of the aircraft is prolonged.

The present invention relates to the field of electronic materials, specifically to an aircraft de-icing / electromagnetic low-scattering compatible structure and a design method thereof. The present invention adopts a periodic high-wave-transmittance electric heating impedance network, conforms the impedance network to the wave-absorbing structure, and realizes high-wave-transmittance performance through patterned design of the impedance network; and by optimizing the key ice formation areas on the surface of the wave-absorbing structure to perform resistance control in partitioned areas, the purpose of zoned heating and concentrated heat adjustment is achieved, thereby achieving more targeted de-icing. The present invention can simultaneously realize the functions of electric heating de-icing and electromagnetic low-scattering, which can not only meet the needs of aircraft de-icing at high altitude or in cold environments, thereby protecting the flight safety of the aircraft, but also ensure that the aircraft's electromagnetic low-scattering function is not affected. It is expected to be applied to the safety protection and electromagnetic compatibility of future low-detectable aircraft, and become its important technical accumulation.

The invention discloses a divergence discrimination method for a deformable aircraft attitude control system based on multi-modal feature extraction, and belongs to the technical field of aircraft safety boundary evaluation. The method comprises the following steps: firstly, performing Gaussian smoothing filtering preprocessing on attitude angle tracking error signals of each channel to remove high-frequency noise; then, direct divergence judgment is realized based on sliding window linear regression and fluctuation intensity detection, and oscillation divergence judgment is completed by combining high-frequency and high-amplitude detection; and finally, correcting the divergence time, determining the earliest divergence channel, combining the divergence type and natural frequency of the error signal, analyzing the influence of nonlinear factors on the frequency domain characteristics of the system, and determining the relationship between divergence and cut-off frequency, thereby accurately identifying the divergence time and type. The method can effectively deal with non-linear interference such as atmospheric perturbation and execution mechanism saturation, realizes early divergence detection and mode recognition under multi-channel conjoint analysis, and has the characteristics of high accuracy, low calculation complexity and high engineering applicability.

An on-board system and method for leveraging multi-modal means of detecting runway incursions to increase aircraft safety, and to provide a necessary enabler for both reduced crew operations and autonomous flights in the future. The system and method detect incursions using visual perception for all types of vehicles and objects that may incur, and an ADS-B for self-reporting vehicles. The system and method fuse prior known information (such as ownship pose and map data) with detections from sensors and other sources. The system actively tracks detections and computes the current and predicted future states to decide if there is an on-going incursion on the runway. The system reports the runway state to the pilots and / or autonomous receivers.

To make it possible to safely operate a flying body.SOLUTION: A system that controls flight of a flying body includes a control unit that controls the flying body according to an operation instruction sent from a user. In a first operation mode, the control unit makes it possible to concurrently receive plural operation instructions. In a second operation mode, the control unit makes it possible to receive only one operation instruction.SELECTED DRAWING: Figure 1

The invention belongs to the field of aircraft state evaluation, and particularly discloses an aircraft safety state evaluation method based on multi-source data analysis, which comprises the steps of multi-source data acquisition, data set preprocessing, feature engineering, aircraft safety state grade evaluation and hyper-parameter tuning. According to the scheme, full-dimension multi-source data is collected, strong correlation features are screened through chi-square test, a feature subset is iteratively optimized through sequential feature selection, a feature scale is standardized and unified through standard deviation, a minority class of samples are specifically balanced by adopting an SMOTH algorithm and an SVM-SMOTH algorithm, and an optimal feature subset with high correlation, low redundancy and balanced distribution is constructed; by constructing a two-stage hybrid neural network model of a long-short-term memory network and a GRU, long-term time sequence association and short-term sudden change are comprehensively captured, accurate time sequence perception and real-time evaluation of the aircraft safety state are achieved, and safety state evaluation is more real-time and accurate.