84 results about "Automatic landing" patented technology

The invention provides a safety device based on mine ventilation network simulation regulation and control and a use method thereof, and belongs to the technical field of underground safety equipments.The side portion of a frame body is provided with two regulation and control air channels, two transmission modules are arranged between the two regulation and control air channels, and a data acquisition and communication module capable of sliding and ascending and descending is clamped between the two transmission modules; fixing modules are installed on the frame body and the regulation and control air channel, the regulation and control air channel is divided into three sections, a dust removal module is installed in each section, and an air speed detector is arranged on the rear portion of each dust removal module. Comprehensive perception, intelligent regulation and control and convenient maintenance of the mine ventilation system are achieved, a digital twinborn model is accurately constructed through the mobile acquisition module, a data basis is provided for intelligent analysis, the controller can automatically optimize and adjust a fan, the response is fast, an original automatic landing maintenance mechanism is adopted, and the maintenance efficiency is improved. When the air duct is blocked, an alarm can be given and the air duct falls to the ground, so that the maintenance work does not need climbing operation, safety and high efficiency are realized, and the reliability and safety of the system are remarkably improved.

The invention discloses an efficiency evaluation method of an automatic landing aid decision-making system and a medium, and relates to the field of automatic landing, and the method comprises the steps: obtaining physiological data and flight data of a driver during the execution of an aircraft landing task; a driver executes an aircraft landing task by relying on the automatic landing aid decision-making system; preprocessing the physiological data and the flight data respectively; on the basis of the preprocessed physiological data, a load level value of the driver is calculated by using a sliding window of multiple time scales and a dynamic entropy weight method; extracting features of the preprocessed flight data by using principal component analysis, and calculating an Euclidean distance between the corresponding features and the expert flight data to obtain a landing operation performance level value of the driver; normalizing and adding the load level value and the landing operation performance level value to obtain an effectiveness evaluation score; and when the efficiency evaluation score is greater than or equal to a first threshold value, the efficiency of the automatic landing aid decision-making system is optimal. According to the invention, the efficiency of the automatic landing aid decision-making system is effectively evaluated.

The invention discloses a control method and system for automatic landing of a shipborne unmanned rotorcraft in a specified deck area, and belongs to the technical field of automatic control of unmanned rotorcrafts. The method comprises the following steps: step 1, planning an ideal landing line of the unmanned rotorcraft based on the position of the unmanned rotorcraft and the position of a ship deck; step 2, obtaining a position error of the rotor unmanned aerial vehicle based on the ideal landing line; step 3, predicting the operation attitude of the ship to obtain a ship attitude prediction result; and step 4, generating a predicted ideal landing line of the unmanned rotorcraft based on the ship attitude prediction result, and performing trajectory tracking flight control on the unmanned rotorcraft based on the position error of the unmanned rotorcraft to complete automatic landing of the unmanned rotorcraft in the specified deck area. According to the invention, the automatic landing task of the shipborne unmanned rotorcraft in the designated area on the ship can be realized.

The invention relates to the field of unmanned aerial vehicle automatic landing control, and discloses an unmanned aerial vehicle wind-resistant landing control system which comprises an external wind-resistant structure module arranged on the periphery of an unmanned aerial vehicle landing area, and the external wind-resistant structure module adopts a fixed conical cover body design; the external windproof structure module guides external airflow into the landing area, and the size and the height of the top opening of the conical cover body are shown in the specification. A local low-wind-speed environment is constructed through the external windproof structure module, the wind speed of a landing area is effectively reduced, and the wind speed of the landing area is effectively reduced in combination with real-time estimation and accurate control of the environment perception and decision control module on the external wind speed and the tail-section attitude correction capability of the attitude correction and re-landing strategy module. The landing point alignment accuracy of the unmanned aerial vehicle under the condition of crosswind, gust or sudden wind direction change is remarkably improved, and horizontal drifting and landing failure caused by wind disturbance are effectively avoided.

An embodiment provides convergent tracking for Global Navigation Satellite System (GNSS) signals (e.g., binary offset carrier (BOC), etc.) in GNSS applications, such as positioning, navigation, timing, and guidance. The embodiment employs a situation-aware two-dimensional (2D) routing algorithm that provides fast convergence to stable tracking. Further, an embodiment may provide subcarrier phase ambiguity resolution that resolves carrier phase with assurance to support high integrity navigation, including high integrity real-time kinematic (RTK) applications. Moreover, an embodiment may provide tracking to more accurate subcarrier phase estimates. This may provide up to four times better ranging accuracy. Accordingly, an embodiment provides robust tracking performance of BOC signals under varying levels of dynamics, high jamming tolerance, more ranging accuracy, support for high integrity navigation, and support for high integrity RTK based positioning and high precision navigation and automatic landing.

The invention belongs to the field of flight control, and particularly relates to an aircraft automatic landing simulation method and device based on a fuzzy theory, and the method comprises the steps: S1, obtaining simulation input parameters at a current moment; s2, inputting the simulation input parameters into a pre-constructed glide rule base and a pre-constructed approach rule base to obtain a sinking rate instruction; s3, calculating a subsidence rate deviation according to the subsidence rate instruction and the subsidence rate; s4, inputting the subsidence rate deviation into a pre-constructed pilot rule base to obtain an elevator instruction; s5, determining an accelerator instruction based on a pre-constructed accelerator rule base; and S6, inputting the elevator instruction and the accelerator instruction into an aircraft landing simulation system to obtain simulation input parameters at the next moment. The anti-interference performance of the aircraft is improved, and the landing safety of the aircraft is improved.

The invention belongs to the field of aircraft landing, and particularly relates to an aircraft automatic landing flight quality evaluation method, which divides a landing process and analyzes the influence of different landing stages on arresting landing, determines evaluation indexes of each stage, a decision point and a touch plate point, and then establishes a comprehensive evaluation system of the landing process. The method comprises the following steps of: firstly, obtaining a weight factor of an evaluation index system by utilizing an expert scoring method, and introducing different membership functions to score an evaluation index; and finally, obtaining a comprehensive evaluation score of the automatic landing process of the aircraft by combining the evaluation score of the index in each stage and the weight factor of each level. By evaluating the automatic landing process and constructing a comprehensive evaluation system, the systematicness and logicality of the evaluation method are improved; a weight factor is obtained by utilizing an expert scoring method, so that the trueness of an evaluation result is improved; and engineering realization is easy.

An automatic landing system for a vertical take-off and landing craft, a vertical take-off and landing craft, and a landing control method for a vertical take-off and landing craft comprise: a relative position acquisition unit which defines the position of an artificial satellite as a reference point, which compares carrier phase data conveyed from the artificial satellite to a vertical take-off and landing craft with carrier phase data conveyed from the artificial satellite to a landing target point, and which acquires the relative positions of the vertical take-off and landing craft and the landing target point; and a control unit which controls the vertical take-off and landing craft so that the relative positions reach zero.

The invention discloses an automatic landing control method and device based on hierarchical reinforcement learning and a medium, and relates to the technical field of unmanned aerial vehicles, and the method comprises the steps: employing an expert experience weighting device to add attention weights to environmental parameters and aircraft state parameters, and obtaining the weighted environmental parameters and aircraft state parameters; according to the empowered environment parameters, the empowered aircraft state parameters and the decision memory, using an upper reinforcement learning network to make a landing decision to obtain a decision result, and updating the decision memory according to the decision result; and according to a decision result, performing flight control on the aircraft through a lower-layer reinforcement learning network by using the weighted environment parameters and the weighted aircraft state parameters to complete landing. The aircraft landing decision is made through the upper reinforcement learning network, the aircraft is adaptively controlled through the lower reinforcement learning network, the aircraft is guided to land automatically, and the adaptability and robustness of the aircraft in the automatic landing process are improved.

A system for determining an automatic landing path for an aircraft that can conduct automatic landings in many different scenarios. The system includes an aircraft landing controller, a network of sensing systems comprising a Global Navigation Satellite System (GNSS), an Instrument Landing System (ILS), and a vision sensing system, a processor, a communication device, and computer-readable memory. In operation, the system receives one or more radio signals from the ILS, one or more GNSS signals from the GNSS, and one or more vision sensor signals from the vision sensing system. The system evaluates, via the processor, the received signals to generate an aircraft landing profile indicative of the method of automatically landing the aircraft. The system transmits the aircraft landing profile to the aircraft landing controller. The system can provide automatic landings for any approach type including on runways without published instrument approaches.

To facilitate introduction of an automatic shore arrival device to a vessel.SOLUTION: An automatic shore arrival device 31 is applied to a vessel provided with outboard engines 2, 3, steering actuators 8, 9, and a joystick maneuvering device 21. The joystick maneuvering device 21 has an operation lever 23, a manual operation processing unit 24, and a propulsion control unit 26. The manual operation processing unit 24 outputs a lever operation signal corresponding to displacement of the operation lever 23 to the propulsion control unit 26, and the propulsion control unit 26 moves the vessel by controlling the outboard engines 2, 3 based on the lever operation signal. The automatic shore arrival device 31 includes a present position detection unit 32 for detecting a present position of the vessel, a shore arrival position determination unit 33 for determining a shore arrival position, and an automatic shore arrival processing unit 34. The automatic shore arrival processing unit 34 outputs a lever operation signal corresponding to displacement of the operation lever 23 required to move the vessel from its present position to the shore arrival position to the propulsion control unit 26 of the joystick maneuvering device 21.SELECTED DRAWING: Figure 1

The invention relates to an image recognition and target tracking method and system based on an unmanned aerial vehicle, and aims to provide a technical scheme capable of realizing efficient and accurate target recognition and tracking. According to the invention, the high-resolution camera is installed on the unmanned aerial vehicle, and the recognition and tracking of targets such as the ground, buildings, vehicles and the like are realized by using an advanced image recognition algorithm. According to the image recognition algorithm, the deep learning technology is adopted, image features can be automatically extracted, feature points do not need to be manually selected, and the recognition accuracy and real-time performance are improved. Meanwhile, a multi-target tracking technology is adopted in the target tracking algorithm, multiple targets can be tracked at the same time, and the target tracking effect is better than that of a traditional technology. The system also has a series of advantages. Firstly, the system can achieve the functions of automatic take-off, autonomous flight, automatic landing and the like, and the autonomy of the unmanned aerial vehicle is improved. And secondly, the system can automatically plan the optimal flight path by analyzing the target position and the environment information, so that the efficiency of the unmanned aerial vehicle is improved. And finally, the system can automatically alarm the user, measures are taken in time, and accidents are avoided.

The utility model discloses a whole tray automatic landing device which is beneficial to conveying finished product trays and improving the working efficiency, the structure is named as the whole tray automatic landing device, a roller way conveyor in the whole tray automatic landing device drives a plurality of conveying roller shafts to convey the finished product trays to a tray fork in place and then stops; the two sets of pull rods and the two sets of plate chains are pulled through the two sets of hydraulic adjusting rods, the lifting frame is driven to ascend and descend, meanwhile, the stability in the lifting process can be guaranteed through the multiple lifting wheels, the falling-off situation is prevented, the tray fork is driven to lift a finished product tray to be higher than the conveying frame by a certain height, and then the finished product tray is conveyed to the conveying frame. The moving motor is driven, the first movable chain wheel drives the first transmission chain and the first transmission chain wheel to conduct transmission, and therefore the multiple sliding wheels drive the moving frame to horizontally move on the two sets of walking rails.

In order to help pilots relying on manual visual inspection to realize autonomous landing more safely, the invention provides a method for assisting autonomous landing by using an airborne Doppler navigation radar and an airborne radar altimeter. Firstly, the glide speed can be obtained by directly utilizing the existing speed detection data of the airborne Doppler navigation radar. And secondly, calculating an inclination angle in a vertical plane by using detection data of Doppler frequency shift by a Doppler navigation radar, thereby obtaining a glide angle. Or the glide angle is calculated according to the trigonometric function relation by using the three-dimensional velocity component measured by the airborne Doppler navigation radar. And then on the basis of acquiring height measurement data by using an airborne radar altimeter, calculating a glide distance by using the acquired glide angle and a trigonometric function relationship. Furthermore, if the aircraft is further provided with a flight management system, an automatic driving system and the like, technical support can be provided for semi-automatic landing by using landing data provided by an airborne Doppler navigation radar and a radar altimeter.

The invention relates to an aircraft landing automatic braking system and method, and the aircraft landing automatic braking system comprises an automatic braking switch, an aircraft management computer and an aircraft wheel braking system; after the automatic brake switch is turned on, the airplane enters an airplane automatic brake mode; in the automatic braking mode of the airplane, the airplane management computer judges whether the airplane is grounded or not according to the received airplane speed, the main landing gear airplane wheel bearing state and the main airplane wheel rotating speed; after the airplane is grounded, the airplane management computer judges whether a braking condition is met or not according to the position of a throttle lever and the state of a spoiler; when the braking condition is met, the airplane management computer calculates the braking distance and the braking deceleration rate; the airplane management computer issues a braking instruction to an airplane wheel braking system according to the braking deceleration rate; after receiving the braking instruction, the airplane wheel braking system automatically applies braking pressure according to the braking deceleration rate, so that the airplane decelerates at the braking deceleration rate, braking is completed, and then the airplane exits from the automatic braking mode.

The invention discloses an automatic landing system for a swimming pool robot. The automatic landing system comprises a fixing part, a lifting part, a tray, an inflation device and a signal device. The fixing part is fixed to the bank of the swimming pool, one end of the lifting part is connected with the fixing part, the other end of the lifting part extends below the water surface of the swimming pool, the tray is arranged at the extending end of the lifting part, the inflation device is internally or externally connected to the lifting part, and the signal device is arranged on the lifting part or the tray. The swimming pool robot is guided to be accurately parked on the tray through the signal device, buoyancy generated by the inflation device is used for driving the lifting part to be lifted, a smooth slope is formed for the robot to land, and the problems that an existing swimming pool robot is difficult to land, and a traditional landing device is complex in structure and high in energy consumption are solved. The device has the advantages of being simple in structure, low in energy consumption, stable in operation and high in safety, and can efficiently assist the swimming pool robot in completing automatic ashore operation.

The invention relates to the technical field of unmanned aerial vehicle cluster control and autonomous landing, in particular to an unmanned aerial vehicle cluster infrared guide automatic landing method and system.The infrared guide transmitting devices are arranged at the four corners of a ground rectangular landing area, and each device divides an airspace into a plurality of sub-airspaces; and infrared signals including the equipment code, the landing permission code and the check code are transmitted in turn in a time division multiplexing mode. And the unmanned aerial vehicle obtains three-dimensional coordinates and height information of the unmanned aerial vehicle in the airspace by receiving four-corner signals and decoding the four-corner signals, so that accurate positioning and guiding without satellite signals are realized. The system cooperatively controls the landing sequence, and guides the unmanned aerial vehicles to land in a staggered manner in batches according to the sequence of odd rows and odd numbers, odd rows and even numbers, even rows and odd numbers, and even rows and even numbers, so that the collision risk is effectively avoided. The method has the advantages of being high in anti-interference capability, high in positioning precision, good in collaboration and suitable for a complex electromagnetic environment.

The application provides a stability enhancement system for aircraft lateral layered control, belongs to the technical field of automatic flight control, and relates to the technical field of automatic flight control.The system meets the design standard of a civil aviation IIIa control system.The system adopts a layered control architecture combining outer loop PID track tracking control and inner loop lateral heading model predictive control (MPC).The outer loop PID control is responsible for basic track tracking, and the inner loop MPC finely adjusts the heading angle and the track to ensure that the aircraft accurately aligns with the runway and stably flies.The method not only improves the control precision and response speed, but also significantly reduces the calculation burden, enhances the robustness and anti-interference ability of the system by combining the simplicity of the PID control and the multivariable optimization capability of the MPC.The system can effectively improve the stability of the aircraft lateral control under complex flight environment, and ensures the safety and reliability of the aircraft during the automatic landing task.

The application provides a kind of safety device based on mine ventilation network simulation regulation and control and its use method, belongs to underground safety equipment technical field, two groups of regulation and control air duct are installed on the side of frame, two transmission modules are arranged in the middle of two groups of regulation and control air duct, the data acquisition and communication module that can slide and lift is clamped between two transmission modules, fixed module is installed on the frame and regulation and control air duct, regulation and control air duct is divided into three sections, and dust removal module is installed in each section, and wind speed detector is arranged at the rear of dust removal module.The application realizes the comprehensive perception, intelligent regulation and control and convenient maintenance of mine ventilation system, accurately constructs digital twin model through mobile acquisition module, provides data basis for intelligent analysis, and the controller can automatically optimize and adjust the fan, responds quickly, the unique automatic landing maintenance mechanism can alarm and land to the ground when the air duct is blocked, so that the maintenance work does not need to climb, is safe and efficient, significantly improves the system reliability and safety.

The invention relates to the technical field of manned aircrafts, in particular to a manned aircraft, an off-line state automatic control system and method thereof and a storage medium. The method comprises the following steps: acquiring battery power, motor temperature, flight time and residual voyage data of the aircraft in real time through an endurance monitoring module; when it is detected that the aircraft enters the off-line state, a preset off-line control strategy is started; a safe landing point or a return path is dynamically generated according to the endurance monitoring data, and the aircraft is controlled to execute automatic landing or return operation; and continuous power supply of the key system is guaranteed through the redundant power supply module. The method has the advantages that the safety is realized; the accident risk in an offline state is reduced by combining the endurance data and the terrain information; reliability: a redundant power supply design ensures continuous operation of a key system; the compatibility is that various aircraft structures such as multi-rotor and fixed-wing aircraft structures are supported.

The invention discloses an aircraft landing method and system and a storage medium, and the method comprises the steps: receiving an aircraft landing instruction, and controlling a visual recognition module to determine an idle target parking apron within a preset range below an aircraft; controlling a visual identification module to identify a visual positioning identifier on the target parking apron so as to determine a first pose of the aircraft relative to the target parking apron; controlling a radar identification module to identify a radar positioning identifier on the target parking apron so as to determine a second pose of the aircraft relative to the target parking apron; and a fusion pose is determined according to the first pose and the second pose, and the aircraft is controlled to land on the target parking apron according to the fusion pose. According to the invention, the accuracy of positioning between the aircraft and the target parking apron is improved, and then the safety of the aircraft during automatic landing is improved.

The embodiment of the invention provides an unmanned aerial vehicle automatic propeller returning method and an unmanned aerial vehicle hangar, the unmanned aerial vehicle automatic propeller returning method is applied to the unmanned aerial vehicle hangar and the unmanned aerial vehicle, the unmanned aerial vehicle hangar comprises a side wall, a hangar door and a landing platform, and the hangar door comprises a lifting part capable of lifting in the vertical direction; the method comprises the steps that an unmanned aerial vehicle hangar responds to a received first signal representing that an unmanned aerial vehicle lands on a landing platform, and a lifting part is controlled to ascend, so that part of paddles of the unmanned aerial vehicle interfere with the lifting part to return; and the unmanned aerial vehicle hangar controls the landing platform to move to a first position in the unmanned aerial vehicle hangar in response to a received second signal representing that part of the paddles are returned, so that the remaining paddles of the unmanned aerial vehicle interfere with the side wall to return.

The invention belongs to the technical field of motion estimation signal simulation generation, and particularly relates to a mobile platform ship surface motion estimation signal simulation and compensation verification method, which comprises the following steps: designing a deck motion estimation signal based on a deck motion model, inputting the deck motion estimation signal into ground automatic landing guide control equipment, and generating a control estimation signal; setting a virtual ideal carrier landing point in the ground automatic carrier landing guide control equipment, determining a numerical range of lifting of an ideal route according to the virtual ideal carrier landing point, and giving an initial value of the ideal carrier landing point according to the numerical range; a simulated deck motion estimation signal is sent to an aircraft through a land-based airport, an aircraft flight control system carries out deck motion compensation instruction resolving and deck motion compensation effect evaluation, deck motion compensation algorithm verification is completed, and a ship-based function verification risk is released in advance. The deck motion compensation verification can be completed without actual verification, the efficiency is high, and the cost is low.

An automatic landing control method for a large-scale fixed-wing unmanned aerial vehicle. The method comprises: dividing a landing phase of an unmanned aerial vehicle into an approach level flight phase, a final approach glide slope phase, a first landing flare phase, a second landing flare phase and a landing rollout phase; in the approach level flight phase, controlling the unmanned aerial vehicle to maintain a target level flight speed and a target approach level flight altitude, and to align a lateral offset and a track angle with a runway extended centerline and track the runway extended centerline; in the final approach glide slope phase, controlling the unmanned aerial vehicle to maintain a target glide speed and a target glide angle; in the first landing flare phase, controlling the unmanned aerial vehicle to maintain a target vertical speed and an airspeed; in the second landing flare phase, controlling the unmanned aerial vehicle to maintain the target vertical speed and the airspeed; and in the landing rollout phase, controlling the unmanned aerial vehicle to decelerate to 0, and at the same time, controlling the unmanned aerial vehicle to maintain a target lateral offset and a target heading angle and keep same on a runway centerline. The control method enables precise control over the automatic landing of an unmanned aerial vehicle, thereby greatly improving the robustness and safety of the automatic landing of the unmanned aerial vehicle.

The application discloses an automatic landing control method and system, relates to the field of flight control technology, and comprises the following steps: constructing a longitudinal dynamics model of an airplane, and discretizing the model to obtain a discrete state space equation; acquiring the longitudinal motion state quantity of the airplane, the steady-state target quantity of the deck of an aircraft carrier and the steady-state disturbance quantity of the wake flow of the aircraft carrier at the current moment; solving the discrete state space equation based on the equation by using a whale optimization algorithm to obtain an optimal prediction control input sequence; filtering and correcting the longitudinal motion state of the airplane after control by using a Kalman filter; and landing if the corrected state meets preset landing conditions, or returning to acquire data again. The application combines model prediction control dynamic constraints and Kalman filter noise reduction, and quickly solves by using a whale optimization algorithm, so that the landing precision and anti-interference ability in a complex environment are significantly improved.

The application provides an automatic landing method for a power inspection unmanned aerial vehicle in a landing stage, and the main design includes or is based on: 1, a landing gear structure design based on multiple sensors; 2, a judgment logic considering multiple ground contact conditions; 3, an automatic landing method for the power inspection unmanned aerial vehicle in the landing stage, which comprises landing area judgment and landing process sensing, that is, a complete landing detection scheme is provided in the landing-ground contact stage of the power inspection unmanned aerial vehicle, the ground sensor and the unmanned aerial vehicle antenna are integrated on the landing gear, the load of the machine body is reduced, the design complexity is reduced, the design cost and time of the machine body of the unmanned aerial vehicle are reduced, the safety of the unmanned aerial vehicle in the landing-ground contact stage is improved, the cost of the machine body of the unmanned aerial vehicle is reduced, and the inspection efficiency of the unmanned aerial vehicle is improved.

The present application relates to the technical field of unmanned aerial vehicle cluster control and autonomous landing, in particular to an unmanned aerial vehicle cluster infrared guidance automatic landing method and system, the present application arranges infrared guidance emitting devices at four corners of a ground rectangular landing area, each device divides the airspace into multiple sub-airspaces and emits infrared signals containing device codes, landing permission codes and check codes in turn through time division multiplexing. The unmanned aerial vehicle decodes the four-corner signals to obtain its three-dimensional coordinates and height information in the airspace, realizing accurate positioning and guidance without satellite signals. The system controls the landing sequence in cooperation, guides the unmanned aerial vehicles to land in batches in the order of odd-numbered rows of odd numbers, odd-numbered rows of even numbers, even-numbered rows of odd numbers and even-numbered rows of even numbers, effectively avoiding collision risks. The present application has the advantages of strong anti-interference ability, high positioning accuracy, good cooperativeness and suitability for complex electromagnetic environments.

This invention discloses a dynamic obstacle avoidance and automatic landing optimization system for unmanned aerial vehicles (UAVs) in multiple scenarios and across the entire domain, relating to the fields of UAV defense and environmental perception technology. The method includes: controlling a scanning UAV equipped with a camera array to collect spatial and ground images, simultaneously acquiring attitude and positioning data; a processing center preprocessing and seamlessly stitching the images to generate a panoramic image of the entire environment; fusing multi-source monitoring data to form a complete dataset covering both indoor and outdoor environments; constructing a multi-index evaluation model to identify safe, landable areas through semantic segmentation and target detection; transmitting environmental data to a receiving device, guiding it to automatically aim and send appropriate landing commands. This invention achieves 360-degree, all-around environmental detection without blind spots, expands the coverage of landable areas, and improves the accuracy of safe area identification and the coordination between scanning and landing.

The application discloses an automatic landing auxiliary decision system performance evaluation method and medium, relates to the automatic landing field, and comprises the following steps: acquiring physiological data and flight data of a pilot when the pilot performs an airplane landing task; the pilot performs the airplane landing task by relying on an automatic landing auxiliary decision system; the physiological data and the flight data are preprocessed respectively; based on the preprocessed physiological data, a load level value of the pilot is calculated by using a plurality of time scales of a sliding window and a dynamic entropy weight method; principal component analysis is used to extract features of the preprocessed flight data, and Euclidean distances between the corresponding features and expert flight data are calculated to obtain a landing operation performance level value of the pilot; the load level value and the landing operation performance level value are normalized and added to obtain a performance evaluation score; when the performance evaluation score is greater than or equal to a first threshold value, the performance of the automatic landing auxiliary decision system is excellent. The application effectively evaluates the performance of the automatic landing auxiliary decision system.