102 results about "Control system design" patented technology

This patent discloses a computer system for humanoid robot control system design and implementation, featuring a digital humanoid robot with dynamical models and a set of single-input-single-output (SISO) and multi-input-multi-output (MIMO) controllers. The system comprises a main software program, a generative Al humanoid robot intelligence engine, a robot motion path planner module, and a control system simulation engine. It enables efficient design, testing, validation, and implementation of robot control systems, significantly reducing time to market. The system supports seamless upgrades to accommodate new designs and components, enhancing applications in industrial automation, healthcare, public safety, and more, aligning with the goals of the 4th Industrial Revolution.

The invention belongs to the technical field of airborne radar phased-array antenna wave control system design, and particularly relates to an airborne radar phased-array antenna wave control system multi-node software online upgrading method, which comprises the following steps of: 1, synthesizing upgrading files of software needing to be upgraded into a total upgrading file; step 2, extracting a total upgrading file from the software configuration library, sending the total upgrading file to a main node of a system to be upgraded by an upper computer, and performing file verification; step 3, extracting frame header information of the total upgrade file by the master node of the system to be upgraded, comparing the information of each upgrade file with the information of each slave node software collected in real time, and judging whether to upgrade each slave node software; 4, the master node of the to-be-upgraded system disassembles the upgrade file needing software upgrade according to the upgrade file information in the total upgrade file frame header, and issues the upgrade file to the corresponding slave node; and step 5, upgrading the software by the slave nodes needing to be subjected to software upgrading according to the upgrading file.

The invention belongs to the technical field of aircraft control system design, and particularly relates to a dual-redundancy steering engine controller switching control method, switching control is achieved through three FPGA logic processing modules including an FPGA 1, an FPGA 2 and an FPGA 3, the FPGA 1 controls main and standby control boards, the FPGA 2 controls three main driving boards, the FPGA 3 controls three standby driving boards, and the situation that overall work is abnormal due to the fact that one device breaks down is avoided. And the full duplex 422 bus and the CAN bus are used for feeding back the control current and voltage, the power current and voltage, the temperature signal, the position signal and the overcurrent signal acquired by the signal feedback circuit. The main drive control circuit and the standby drive control circuit share states and check each other through dual-computer communication 422, and can detect each other and automatically switch when a fault occurs in a certain redundancy.

The invention relates to a high-altitude cabin air inlet system active-disturbance-rejection control method based on an improved rapid super-spiral sliding mode and differential flatness, and belongs to the technical field of aero-engine high-altitude simulation control. The method comprises the following steps: establishing a high-altitude cabin air inlet system model; according to the established system model, the temperature and pressure coupling control problem is solved by using the differential flatness characteristic of the system; designing an improved rapid super-spiral sliding mode controller for the active disturbance rejection temperature and pressure decoupling control system to obtain an improved rapid super-spiral sliding mode active disturbance rejection temperature and pressure decoupling control system; the improved rapid super-spiral sliding mode active disturbance rejection temperature and pressure decoupling control system generates control input signals according to system temperature and pressure environment parameter output signals. The control input signal is input into the high-altitude cabin air inlet system, the high-altitude cabin air inlet system operates, and temperature and pressure environment parameter output signals are obtained. According to the invention, the problem of strong airflow interference in the rapid transition state test of the high-altitude cabin air inlet environment simulation system can be solved.

The invention discloses a path tracking control method suitable for crawler-type agricultural equipment. The method comprises the following steps: S1, building a navigation hardware control system on crawler-type equipment; s2, designing a Kalman filtering algorithm to filter the course angle of the crawler-type equipment; s3, correcting an equipment positioning error caused by the attitude angle; s4, a fusion algorithm of the Stanley algorithm and the Pure Pursuit algorithm is designed; s5, designing an enhanced SPP algorithm; s6, performing secondary optimization on the control law output by the SPP algorithm by using a fuzzy PID control algorithm; and S7, fitting a total control law equation in combination with the control algorithm, and converting the control law into the linear speed of the left and right tracks of the crawler-type equipment so as to realize steering and straight movement of the crawler-type equipment. According to the invention, a complex agricultural environment is regarded as a black box system, and item-by-item optimization is carried out by superposing an algorithm with high interpretability, so that the adaptability of a control system to the black box system is improved, and finally, the equipment path tracking precision is improved step by step.

The application belongs to the field of integrated permanent magnet synchronous motor control system design, and particularly relates to an integrated permanent magnet synchronous motor open loop-closed loop switching control method and a control system. The open loop control is designed at the same time as starting the closed loop calculation. When the open loop output speed reaches the open loop-closed loop switching speed and the closed loop control output target speed reaches the open loop-closed loop switching speed, the open loop control is switched to the closed loop control, and the motor is controlled in the closed loop mode, so that the motor control speed fluctuation is small, the speed following property is good, and the switching process is smooth.

The invention discloses a thermal control comprehensive practical training system based on DCS control, and relates to the technical field of thermal control comprehensive practical training, and the system comprises a DCS control practical training unit which is used for building an intelligent DCS control skill practical training room and is developed based on a domestic autonomous controllable DCS control system from the four aspects of decoration layout, a control system, an entity process object and a virtual process object. The thermal control maintenance training unit realizes the multifunctional operation of DCS hardware and system maintenance, DCS software configuration and debugging, control system design and optimization, on-site actual equipment adjustment and calibration and fault diagnosis and analysis, and is used for constructing a professional thermal control maintenance training room covering all thermal control maintenance contents. On the basis of practical training room construction, the intelligent level of the practical training room is comprehensively improved, the training function is expanded, the artificial intelligence technology is introduced into the practical training room construction process, deep recognition and learning of training equipment are completed through the intelligent technology, and intelligentization, real-time performance and scoring autonomy of the training process are achieved.

The invention discloses a reinforcement learning-based PID (Proportion Integration Differentiation) coupling anti-swing control method for a tower crane, and belongs to the technical field of intelligent control of tower cranes. The method comprises the following steps: designing a coupling signal to enhance under-actuated state control; establishing a discrete state space model of the tower crane; designing a discrete PID controller and constructing a reinforcement learning parameter adaptive mechanism; and controlling the tower crane system to operate. The method is designed for a discrete control system and is completely compatible with a digital controller. Swing angle information is introduced and fed back through a coupling signal, coupling between states is enhanced, and load swing is actively restrained. An Actor-Critic reinforcement learning framework based on a single RBF neural network is adopted to set PID parameters on line, state pre-prediction is not needed, the calculation burden is small, the learning efficiency is high, and the controller can be adaptive to load change and external disturbance. The method is clear in structure and good in real-time performance, the positioning and anti-swing performance of the tower crane is remarkably improved, and engineering implementation is easy.

The invention belongs to the field of flight control system design, and particularly relates to a human-in-the-loop flight control system MBIT detection method and device. The method comprises the steps that a three-axis control instruction is loaded to a cockpit display interface; controlling the three-axis control instruction to change, and synchronously obtaining a control surface deflection angle reference value which is preset in the MBIT equipment, is given by a constraint relation and corresponds to the three-axis control instruction reference value; a three-axis control instruction manual value generated when a driver operates a steering column and pedals and a control surface deflection angle actual value under the three-axis control instruction manual value are obtained; and when the deviation between the three-axis control instruction reference value and the three-axis control instruction artificial value is within a first specified range and the deviation between the control surface deflection angle reference value and the control surface deflection angle actual value is within a second specified range, the test is passed, otherwise, the test is not passed. On the premise of ensuring the safety and reliability of the system, the design complexity and cost input of a hardware circuit are effectively reduced, and the economic benefit of the system is improved.

The application provides a kind of super low orbit satellite moment of mass control technology full physical simulation test method and system, wherein the method comprises: step M1, through ground gravity moment simulation on-orbit mass moment torque characteristics;Step M2, build super low orbit satellite moment of mass control technology full physical simulation system;Step M3, design mass moment control full physical test method, for verifying super low orbit satellite moment of mass control technology.The application can truly simulate the on-orbit working state of the mass moment control system, effectively verify the attitude control process and index of the mass moment control technology, thereby providing a strong basis for the design of the mass moment control system of the super low orbit satellite.

The invention relates to the field of design of a precision control system combining automatic control and power electronics, in particular to a virtual load power source adjusting method based on improved self-feedback PID (Proportion Integration Differentiation) adjustment. The method comprises the following steps: carrying out feedforward gain calibration and phase pre-compensation quantity calibration before closed-loop control formal operation, and generating a feedforward compensation signal; setting a target reference signal, and collecting an output signal in real time to obtain an instantaneous tracking error; inputting the instantaneous tracking error into an improved self-feedback PID controller to obtain a feedback control output signal, and combining the feedback control output signal with a feedforward compensation signal to form an initial driving signal; and adding hard amplitude limiting protection to the initial driving signal to obtain a final driving signal. The problems that a traditional virtual load power source adjusting method does not consider the dynamic characteristics of a power amplifier channel, a real-time sensing and adjusting mechanism for tracking errors is lacked, the adjusting performance is limited due to the fact that PID parameters are fixed, and control signals are prone to overrun or overload risks are solved.

The invention belongs to the technical field of aircraft flight control system design, and relates to an aircraft landing grounding point prediction and alarm method based on a real-time flight trajectory. According to the method, the position of the aircraft landing grounding point is predicted and iteratively updated in real time by judging the actual landing stage of the aircraft and combining the actual position information, height information and speed information in the flight of the aircraft. And further judging whether the aircraft has the risk of rushing out of the runway or not by using the position of the grounding point, the landing runway information and the required skating distance information in the flight management system, and if so, performing rushing-out alarm. According to the method, the position of the aircraft grounding point can be rapidly and iteratively predicted in the actual flight process of the aircraft, and the method can adapt to complex uncertainty in the flight process; and then the landing runway information and the required sliding distance information in the flight management system are combined to judge whether the airplane has the risk of rushing out of the runway or not, and the runway rushing-out alarm is correspondingly carried out.

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 discloses a control system design method for space gravitational wave detection. The method first performs modeling on a problem domain of the control system, constructs a first mapping matrix from a functional requirement to a behavior element, performs decoupling verification on the first mapping matrix until the first mapping matrix is in a lower triangular structure. Then, modeling is performed on a solution domain of the control system, a second mapping matrix from the behavior element to a design parameter is constructed, and independence verification is performed on the second mapping matrix until the second mapping matrix is in a lower triangular structure. Finally, a composite equivalent mapping matrix of the two-level matrix is calculated, and is used for change management of the control system. The application can realize formalized design and quantitative evaluation of a strong coupling control system architecture, identify coupling problems in an early design stage, improve design iteration efficiency and change management accuracy, and is mainly applied to control system design for space gravitational wave detection, and can also be applied to design scenes of various high-coupling high-precision space control systems.

system, exhibiting - a container matrix (510, 700, 1130) having a first level and a second level, the first level having a first plurality of container niches (880, 950, 960, 970, 980, 1200) configured to hold individual containers (730, 820, 920, 1210), and the second level having a second plurality of container niches (880, 950, 960, 970, 980, 1200) configured to hold individual containers (730, 820, 920, 1210); - a rack track (556); - a first track (550, 552, 554, 740, 870, 872, 874, 940) arranged in the first level; - a first ramp (560, 562, 564) coupled to the assembly track (556) and the first running track (550, 552, 554, 740, 870, 872, 874, 940); - a second track (550, 552, 554, 740, 870, 872, 874, 940) arranged on the second level; - a second ramp (560, 562, 564) coupled to the assembly track (556) and the second running track (550, 552, 554, 740, 870, 872, 874, 940); - a first movable carrier unit (580, 710, 850, 930, 1020) having a conveyor belt, wherein the first movable carrier unit (580, 710, 850, 930, 1020) is configured to move along the first track (550, 552, 554, 740, 870, 872, 874, 940) and the second track (550, 552, 554, 740, 870, 872, 874, 940) and (i) deposit articles in containers (730, 820, 920, 1210) on the first level or the second level using the conveyor belt, and (ii) transfer full containers (730, 820, 920, 1210) of container niches (880, 950, 960, 970, 980, 1200); and - a control system designed to control the operation of the first movable carrier unit (580, 710, 850, 930, 1020), wherein - the first movable carrier unit (580, 710, 850, 930, 1020) furthermore - at least two side walls on opposite sides of the first movable support unit (580, 710, 850, 930, 1020); and - a first door arranged transversely to the at least two side walls, wherein the first door in an open position forms a slide angled towards a container (730, 820, 920, 1210); and - the first movable carrier unit (580, 710, 850, 930, 1020) is set up for this purpose, - to reach the first track (550, 552, 554, 740, 870, 872, 874, 940) using the first ramp (560, 562, 564), - to reach the second track (550, 552, 554, 740, 870, 872, 874, 940) using the second ramp (560, 562, 564), - to move along the assembly track (556) between the first track (550, 552, 554, 740, 870, 872, 874, 940) and the second track (550, 552, 554, 740, 870, 872, 874, 940), and - to automatically open and close the first door.

The application discloses a nuclear power device control system and method coupled with a heat pipe reactor and an sCO2 Brayton cycle, including a rotating shaft rotating speed control system and method, which maintains the rotating shaft rotating speed constant by adjusting the working medium flow entering the turbine, so as to ensure the power supply quality of the whole system; a compressor inlet temperature and inlet pressure control system and method, which respectively maintains the compressor inlet temperature and inlet pressure constant by adjusting the seawater flow and the pressure tank pressure, so as to ensure that the temperature and density of the working medium at the compressor inlet are in a supercritical state; and an intermediate heat exchanger outlet temperature control system and method, which adjusts the reactor power by controlling the core reactivity, and then maintains the intermediate heat exchanger outlet temperature constant. The application can provide a reference for the control system design of a high-efficiency compact nuclear power device coupled with a heat pipe reactor and a supercritical carbon dioxide Brayton cycle.

A SOFC-PV / T-HP semi-physical simulation system design method, comprising a physical device; a running monitoring software of the physical device; a simulation model; comprising the following steps: firstly, a SOFC-PV / T-HP system basic structure and a steady-state model of the device are established; on the basis of the capacity of the PV / T-HP physical device, the capacity of the virtual device is configured based on the steady-state model; a device mechanism model is established, a dynamic simulation model of the cogeneration system is built according to the device capacity, the virtual device parameters and the simulation initial parameters are initialized; a communication interface of the physical device and the virtual device is built, the data transmission of the physical device and the virtual device is realized, and the semi-physical simulation is carried out; according to the dynamic characteristics of the system, the control system is designed, and the semi-physical simulation system is controlled according to the device control parameters. The application reduces the research cost, improves the safety and efficiency of the control experimental research, and has higher credibility compared with the control research using simulation model.

The application belongs to the field of control system design, and discloses a thrust estimation method based on a time domain convolution network, and proposes a thrust estimator based on a multilayer residual time domain convolution network. On the one hand, a Gaussian error linear unit activation function is used to replace the correction linear unit in the residual block to solve the neuron death problem. On the other hand, the overall structure of the multilayer convolution network is adjusted by using residual connection, so that the network training speed and the thrust estimation effect are further improved. The comparison results with the traditional seven methods show that the method has significant advantages in convergence speed and estimation accuracy. In addition, the application also applies the method to an actual control system of an aero-engine, and further verifies the real-time performance and feasibility of the control scheme through a micro turbojet engine test bed test.

The invention discloses an experimental platform and a test method for simulating plateau train combustion in a plain, and relates to the technical field of tunnel fire safety, the experimental platform comprises a railway tunnel model, the railway tunnel model comprises a tunnel model body and two sealing doors, and the two sealing doors are respectively located at two opposite ends of the tunnel model body to form a sealed space; the plateau environment simulation system comprises a vacuum pump, a flow uniformizing plate, an air inlet system and a pressure gauge, and the combustion and control system is arranged to trigger the train to combust in a low-pressure environment and adjust the combustion intensity. According to the invention, by integrating plateau low-pressure environment simulation, controllable combustion triggering and multi-parameter synchronous measurement systems, a train combustion characteristic full-scale test platform and a standardized test process are constructed; the purposes of solving the problem that train combustion basic data is deficient in a high-altitude low-pressure environment and supporting plateau railway tunnel fire prevention and control system design and emergency plan making are achieved.

The invention relates to a construction and control method of an input-output control system for industry. The construction and control method comprises the steps that an input-output model between the equipment manufacturing industry and the petrochemical industry in a single region is established based on an input-output model; expanding the established input-output model to a multi-region input-output model; establishing a multi-region input-output diffusion model and an input-output control system; designing a pulse controller of the actuator fault; and analyzing the index tolerance of the input-output control system to obtain the gain of the pulse observer and the gain of the pulse controller for the designed pulse observer and the pulse controller to complete the control of the input-output control system. Compared with a continuous time observation and control method, the method provided by the invention can realize the balance between supply and demand of industrial production by regulating and controlling the product demands of the equipment manufacturing industry and the petrochemical industry with lower cost and time consumption.

The aircraft propulsion system comprises: - a turboshaft engine; - a starter; - a freewheel clutch system; - a control system designed to, with the turboshaft engine at idle: - receive a standby request (Rv); and - in response to the standby request (Rv), shut down the turboshaft engine. The control system is designed to, in response to the standby request (Rv): - before the turboshaft engine shuts down, command the starter so that the starter speed (ND) becomes non-zero; and - after shutdown, command the starter to maintain the starter speed (ND) non-zero while the gas generator speed (NGG) decreases to the standby speed (NGGv). Figure for the abbreviation: Fig. 3

Hair styling appliance with rotating head, automatic selection of the head's direction of rotation, and detangling assistance. The invention relates to a hair styling appliance (1) comprising a head (4) with a rotating part (15) provided with a mechanical hair engagement element (7), a drive module for the rotating part, and a control system for the drive module, which includes a device for detecting a direction of forced rotation of the rotating part by interaction between the hair and the mechanical hair engagement element, and a manual control member (34) for triggering rotation of the rotating part in a direction opposite to the detected direction of forced rotation. The control system is designed to automatically trigger rotation in the detected direction of forced rotation if the control member is not activated. Hair styling appliances. Figure for the abstract: Fig. 1

The utility model belongs to the technical field of liquefied hydrocarbon storage tanks, and particularly relates to an automatic water injection device of a full-pressure liquefied hydrocarbon storage tank. Comprising a full-pressure type liquefied hydrocarbon storage tank, a feeding pipeline is connected to the bottom of the full-pressure type liquefied hydrocarbon storage tank, a first manual valve, a liquid level emergency cut-off valve and a material emergency cut-off valve are sequentially arranged on the feeding pipeline from the end close to the full-pressure type liquefied hydrocarbon storage tank, a water injection pipeline is connected between the liquid level emergency cut-off valve and the material emergency cut-off valve, and a second manual valve is connected between the water injection pipeline and the full-pressure type liquefied hydrocarbon storage tank. A second manual valve is arranged at the position, close to the water injection point by the minimum distance, of the water injection pipeline, a first remote control valve, a first check valve, a third manual valve, a fourth manual valve, a second remote control valve, a second check valve and a special water injection pump are sequentially arranged behind the water injection pipeline, and an electric heating belt is wound on the outer wall of the water injection pipeline. By optimizing the water injection mode and the design of the control system, the safety and the quick response capability of the full-pressure liquefied hydrocarbon storage tank in emergency are remarkably improved, and the accident risk is reduced.

The invention relates to a method for determining the spatial position of a conveying unit (1) for conveying load carriers (2) relative to a load carrier (2) under which the conveying unit (1) passes, comprising the following steps: - Detecting at least one distance between at least one reference point (3A-3D) assigned to the conveying unit (1) and at least one surface (4A-4C) assigned to the charge carrier (2); - Acquisition of model data which includes an assignment of at least one acquired distance to a cross-sectional section (6A-6E) of the charge carrier (2); - Determine, based on at least one recorded distance and the recorded model data, a spatial position of the conveying unit (1) relative to the load carrier (2). The invention further relates to a corresponding conveying unit with at least one sensor (3A-3D) designed to detect at least one distance and a control system connected to the at least one sensor (3A-3D) for controlling the conveying unit (1), wherein the control system is designed to carry out the method according to the invention.

The application discloses a global finite time convergence permanent magnet synchronous motor control method based on a backstepping method framework, comprising the following steps: 1) on a MATLAB platform of an upper computer, a permanent magnet synchronous motor control system is designed based on model-based design by using MATLAB / Simulink software; 2) a hardware circuit of a permanent magnet synchronous motor vector control system is built; 3) a finite time nonlinear extended state observer NLESO is designed; and 4) under a recursive control framework of the backstepping method, a super-spiral sliding mode algorithm with a second-order sliding mode characteristic is fused, and a globally finite time stable compound controller is designed. By integrating the observer convergence and the double closed loop stability, the application effectively suppresses the 'chattering' phenomenon of the traditional sliding mode control, and significantly improves the dynamic response speed, the steady state tracking accuracy and the anti-interference robustness of the motor in the whole working condition range.

The application discloses a space helium recycling control system, method and equipment, relates to the technical field of space rare gas recycling system control, and comprises four detection devices, four adjusting devices and a control device. Based on the actual concentration of a first purified target impurity in the space helium output by a recovery device, the actual concentration of a second purified target impurity in the space helium output by an adsorption device, the actual concentration of a third purified target impurity in the space helium output by a low-temperature device, the actual temperature of the space helium output by the low-temperature device, the actual concentration of a fourth purified target impurity in the space helium output by a dehydrogenation device and the actual pressure of the space helium output by the dehydrogenation device, the flow, temperature and pressure of the space helium are adjusted, and the space helium recycling system is controlled. The application can well control the space helium recycling system and further reduce resource waste.

The application discloses a drive system (1) having a plurality of drive units (2), wherein the drive units (2) each comprise a converter (3) and preferably a motor (4), an energy supply system (5) designed to supply electrical energy to the drive units (2), and a control system (6) comprising a control computer (8) and at least one control line (9), wherein the control system (8) is designed to transmit control commands to the drive units (2). The drive system (1) is characterized in that the energy supply system (5) and the drive units (2) are connected to one another in a detachable manner via first connectors, preferably via plug connections, and the control system (6) and the drive units (2) are connected to one another in a detachable manner via second connectors, preferably via plug connections.

The utility model discloses a fire prevention and control system which comprises a power supply module and a control module. The power supply module comprises a power supply control unit, a voltage conversion unit, a voltage output unit, a first switch and a second switch. The first switch is used for controlling connection and disconnection between the storage battery and the voltage conversion unit, and the second switch is used for controlling connection and disconnection between the second input voltage and the voltage conversion unit. The voltage conversion unit is used for converting a first input voltage, a second input voltage or a storage battery voltage into a first power supply voltage and a second power supply voltage, and controlling the connection and disconnection between the first input voltage and the second end of the first switch based on a second control signal. And on-off between the second power supply voltage and the voltage output unit is controlled based on the first control signal. The voltage output unit controls connection and disconnection between the second power supply voltage and the control module based on the third control signal. According to the fire prevention and control system, the stable power supply module is designed, so that the system can still work normally when the main power supply fails.

This invention provides a multi-power vector thruster and aircraft based on a staggered layout, comprising two or more basic thruster units stacked longitudinally. Adjacent thruster units are connected by connectors, with a first interface and a second interface on opposite sides of the connectors. Each adjacent thruster unit is connected to both the first and second interfaces via a stator. The axes of the thruster units connected to the first interface and those connected to the second interface are parallel and spaced apart. This longitudinal stacking of multiple thruster units reduces the complexity of the control system design. Direct vector thrust control can be achieved through differences in thruster rotation speeds, avoiding the complex design and vulnerability of swashplate mechanisms. This design has fewer moving parts, making production and assembly more convenient. Furthermore, the multi-layered stacking design further utilizes longitudinal space, resulting in a smaller overall size after storage.

The invention relates to a big language model data conversion method and system based on model structure analysis, and belongs to the technical field of automatic data processing and artificial intelligence. Aiming at the problem that a simulation model is stored in a binary format and is difficult to directly understand by a large language model, the invention provides a conversion method for automatically analyzing structural data of the simulation model and generating a structured text. The method comprises the steps of reading a model file, analyzing a component structure and a connection relation in a model, tracking variable references and replacing the variable references with corresponding actual values, and further generating a structured document adaptive to a context window of the large language model. Through the technical scheme, the large language model can understand and reasone the simulation model, the simulation analysis efficiency is improved, manual intervention is reduced, and the method is suitable for application scenes such as power electronics, control system design and fault diagnosis.