233 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.

A low-altitude aircraft intelligent identification and emergency countering system relates to the technical field of low-altitude aircraft safety management and comprises a detection unit, an identification unit, a command decision platform, a scheduling unit and a countering unit. The detection unit is used for detecting all low-altitude aircrafts in a prevention and control area and obtaining flight data of all the low-altitude aircrafts; the identification unit is used for receiving the flight data and analyzing and judging the threat level of the low-altitude aircraft based on a fusion algorithm; the command decision platform is used for receiving the threat level of each low-altitude aircraft and sending a disposal instruction to the countering unit; the scheduling unit is used for giving a specific countering equipment scheduling instruction through an intelligent optimization scheduling algorithm according to the disposal instruction; the countering unit controls different countering devices to accurately strike low-altitude aircrafts with corresponding threat levels according to the scheduling instruction; according to the method, the malicious unmanned aerial vehicle can be accurately identified and can be countered in time.

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 relates to the field of electronic materials, in particular to an airplane deicing / electromagnetic low-scattering compatible structure and a design method thereof. The periodic high-wave-transmission electric heating impedance network is adopted, the impedance network is conformal to the wave absorbing structure, and the high-wave-transmission-rate performance is achieved through the patterning design of the impedance network; and the key icing area on the surface of the wave-absorbing structure is optimized to carry out partition resistance regulation and control, so that the purposes of partition heating and heat concentration adjustment are achieved, and more targeted deicing is achieved. According to the invention, the functions of electric heating deicing and electromagnetic low scattering can be realized at the same time, the deicing requirement of an airplane in a high-altitude or cold environment can be met, so that the flight safety of the airplane is protected, and the electromagnetic low scattering function of the airplane is not influenced. The method is expected to be applied to safety protection and electromagnetic compatibility of low detectable aircrafts in the future and becomes an important technical accumulation.

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 provides a low-altitude aircraft safety management system and method, and relates to the technical field of flight safety, and the system comprises the steps: carrying out the flight pre-safety management of a low-altitude aircraft, detecting the equipment state of the low-altitude aircraft, and evaluating the flight plan of the low-altitude aircraft; constructing a flight safety management model of the low-altitude aircraft, performing analysis evaluation and analysis early warning according to the current flight safety influence factors and the flight data of the low-altitude aircraft, obtaining a current flight risk value of the low-altitude aircraft, and performing real-time safety management on the low-altitude aircraft; when the low-altitude aircraft completes the flight plan, flight data is acquired for data archiving analysis, and the future flight plan of the low-altitude aircraft is optimized; and the flight safety management of the low-altitude aircraft is realized.

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 relates to the technical field of aviation guarantee, and discloses a method based on an aircraft guarantee whole-process task early warning model, and the method specifically comprises the steps: comprehensively collecting and preprocessing multi-source data, such as tasks, resources and historical data; deeply analyzing a task logic relationship, and modeling and quantifying a dependency relationship by using a directed acyclic graph; determining early warning indexes such as task progress deviation, resource utilization rate and task risk level; a machine learning algorithm is adopted to construct an early warning model, and an ensemble learning method is used for fusion to improve performance; setting an early warning threshold value, dynamically adjusting according to task types and priorities, triggering early warning when the threshold value is exceeded, and deploying emergency resources when high-grade early warning is triggered. According to the method based on the aircraft guarantee whole-process task early warning model, the guarantee task can be early warned in advance, the execution efficiency and quality are improved, safe operation of an aircraft is ensured, and the method further has the functions of data integrity verification, model parameter self-adaptive adjustment, multi-channel early warning notification, whole-process data tracing and the like.

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 invention discloses an aircraft error prevention maintenance far-end support system based on AR intelligent glasses, and relates to the technical field of aircraft operation and maintenance management. According to the aircraft error-prevention maintenance far-end support system based on the AR intelligent glasses, a virtual model is constructed according to real aircraft part information, aircraft part images are acquired by using an AR glasses terminal in a field environment, and related feature extraction is performed on different aircraft part images in cooperation with an AI image recognition technology, so that the error-prevention maintenance far-end support system based on the AR intelligent glasses is obtained. According to the method and the system, the intelligent identification effect of the aircraft parts is achieved, meanwhile, intelligent judgment of possible abnormal parts of the aircraft parts can be achieved through comparison of the position relation between related characteristics, the error prevention advantage is provided for aircraft safety investigation, communication interconnection between a plurality of AR intelligent glasses terminals is achieved through 5G communication, and the communication efficiency is improved. Distance interference is effectively avoided, and convenient conditions are provided for technical experts to remotely guide field staff to operate, maintain and overhaul airplanes in a real-time image transmission mode.

The invention provides a method for evaluating the clearance fit sealing performance of a plate fastener for a machine. The method comprises the following steps of initial leakage rate detection, air pressure loading test, leakage state detection after helium stamping, data analysis and evaluation and formation of the evaluation method. The leakage state of the aircraft composite fuselage fastener screw hole can be accurately recognized and positioned through an efficient method, and it is ensured that the sealing performance is accurately evaluated. The method is rapid and reliable, can comprehensively detect the sealing effect of the aircraft plate in the service state, verifies whether the aircraft plate meets the design requirements or not, and timely identifies potential weaknesses, thereby enhancing the safety and reliability of an aircraft. Meanwhile, the method can also verify the stability of the sealing performance of the screw hole under the continuous barometric load, and ensures the safe service of an airplane.

An aircraft fuel emergency oil drainage system is applied to a three-tank configuration fuel system comprising a wing oil tank and a central oil tank, and the wing oil tank is provided with an oil supply pump for supplying oil to an aircraft engine; the emergency oil drainage system comprises a central oil tank emergency oil drainage device and a wing oil tank emergency oil drainage device, the central oil tank emergency oil drainage device comprises a central oil tank emergency oil drainage pump, and the oil drainage pump is connected to an emergency oil drainage main pipeline leading to the outside of the aircraft body. The emergency oil drainage device for the wing oil tank comprises a jet pump and an emergency oil drainage branch, the jet pump comprises an inlet, an outlet and a suction inlet, the inlet is connected to an engine oil supply pump, and the outlet is connected to the emergency oil drainage branch to discharge fuel oil from the wing oil tank. The lowest mounting height of the suction inlet relative to the bottom of the wing fuel tank corresponds to the safe fuel level required by flight of the aircraft, and the fuel level can ensure that the aircraft is not overweight during safe landing and an engine has enough power. The invention further relates to an emergency oil drainage method adopting the system.

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 automatic feathering mechanism comprises a variable-pitch disc, a sliding groove is formed in the side wall of the variable-pitch disc, the sliding groove is in sliding connection with a propeller handle variable-pitch pin, a through hole is formed in the center of the variable-pitch disc, a variable-pitch nut is arranged in the through hole of the variable-pitch disc, and the variable-pitch nut is connected with the variable-pitch disc. The variable-pitch nut is internally in threaded connection with a variable-pitch lead screw, a lower limiting piece is arranged at the lower end of the variable-pitch lead screw, and an upper limiting piece is arranged at the upper end of the variable-pitch lead screw; the variable-pitch disc is connected with the variable-pitch nut in a sliding mode, and a limiting seat is arranged on the outer wall of the variable-pitch nut and located above the variable-pitch disc; the paddle handle variable pitch pin is eccentrically connected with a paddle handle of the paddle, and the axis of the paddle handle of the paddle is not coaxial with the pneumatic center of the paddle. After the power motor fails, unpowered fast feathering can be achieved, fuselage resistance is reduced, and the possibility of safe landing of the aircraft is increased.

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 invention discloses an aircraft landing gear safety pin error prevention management system, and relates to the technical field of aircraft safety management, and the method comprises the steps: completing hardware initialization through a main control chip and a sensor module, and loading a subsequent detection algorithm through an embedded computing platform; the three-axis acceleration sensor is used for monitoring the state of the airplane in real time, and whether the safety pin is correctly installed or not is rapidly detected through the RFID / NFC / Bluetooth / WIFI module; the state of the safety pin is detected preferentially through RFID / NFC / Bluetooth / WIFI, and a detection algorithm is started under the abnormal condition; when it is detected that the safety pin is not pulled out, a multiple alarm mechanism is triggered immediately; after the airplane is pushed in place, the state of the safety pin is verified through RFID / NFC / Bluetooth / WIFI and visual detection; and recording and analyzing various data results in real time. According to the invention, the safety risk caused by human negligence is greatly reduced, and the safety of airplane operation is improved.

The invention provides an electric aircraft permanent magnet synchronous motor current sensor failure control method and system based on an LSTM network, and the method comprises the steps: building a fault diagnosis module, detecting whether a current sensor breaks down or not through a sliding mode diagnosis system, and if the fault of the current sensor is monitored, carrying out the fault diagnosis; the input door of the LSTM network collects the rotating speed and position signals of the motor, and constructs and completes the current of the motor through the transmission and memory of the control information of the forgetting door and the output door, thereby guaranteeing the safe flight of the airplane.

The invention belongs to the technical field of aviation aircrafts, and relates to a redundancy voting method for aircraft wheel bearing signals. Through a reliable redundancy voting mode, the problem that when a single-side main wheel touches the ground in the landing stage, a classical majority monitoring voting method cannot effectively recognize the single-side airplane wheel touches the ground can be effectively solved, airplane wheel bearing signals can effectively and accurately represent the flight state of an airplane, it is guaranteed that a pilot can accurately control the attitude of the airplane, and the flight safety of the airplane is improved. And the airplane can safely land.

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.

- AIRCRAFT SAFETY DEVICE - This aircraft safety device transforms the fuselage into an emergency module in the event of damage [Fig.42]. There are three parts, the fuselage, the wings, and the elevator, [Fig.26]. They can be separated from each other, each of its parts grouping sub-devices which ensure this transition. The first part of this assembly, (the fuselage) represents the emergency module. This one has a Sigma device [Fig.30] which is composed of two ailerons. They have the particularity of blending into the mass of the wings of the aircraft of part 2 [Fig.28][Fig.29]. This emergency module integrates an Alpha device, [Fig.7] of two stabilizers which have the role of relay elevator. In the fuselage, there is a Theta device [Fig.30] composed of four fans distributed judiciously on each side of it hidden inside a dedicated compartment; and whose main function is to slow the fall of this rescue module, if necessary, but we can attribute other possibilities to it. This rescue module includes an Iota device [Fig.38][Fig.40], hatches which serve as landing gear, to cushion the impact on the ground and guarantee a horizontal plane whatever the type of terrain encountered. The second part of this assembly serves as a reception base for the rescue module. As for the third part of this assembly (the elevator) [Fig.41] [Fig.53] it is a drone whose mission is to tow this rescue module or to participate in rescue searches. FIGURE FOR ABBREVIATION: [Fig.3].

The present application belongs to the field of aircraft design technology, and particularly relates to a method and device for intelligently predicting the structural strength and stiffness characteristics of a reduced-order model. The method comprises: step S1, obtaining a first prediction model that has been trained for intelligently predicting the structural strength and stiffness characteristics; step S2, changing the parameter value of each input variable of the first prediction model, and determining the contribution rate of each input variable according to the output value of the first prediction model; step S3, selecting multiple input variables as reduced-order input variables based on the contribution rate; step S4, training multiple second prediction models with reduced-order input variables, calculating the prediction accuracy of each second prediction model with root mean square error or regression coefficient, and selecting the optimal second prediction model; step S5, predicting the strength and stiffness characteristics of the aircraft structure through the optimal second prediction model. The present application can improve aircraft safety and design efficiency.

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.