120 results about "Closed loop simulation" patented technology

The invention relates to a phased array radar digital simulation system, and belongs to the technical field of radar system simulation. According to the phased array radar digital simulation system, a system framework is divided into a main sub system and three auxiliary sub systems, wherein the main sub system is a radar workbench simulation sub system and the three auxiliary sub systems are a simulation scene control sub system, a radar main control computer sub system and a radar analysis and evaluation sub system. The functions of the radar workbench simulation sub system are perfected by adding a control word interpreting module, a coordinate conversion module, a flight path intersection model and a loopback word delivering module, and therefore the real-time closed loop simulation of the whole phased array radar system can be carried out. The phased array radar digital simulation system has the advantages of being good in generality, good in instantaneity and capable of achieving the closed loop simulation, and can be applied to the design of modern phased array radar systems.

The invention discloses a transformer station simulation training system based on the mixed digital/ analogy simulation technology. The transformer station simulation training system comprises a primary simulation system of an electric power system on the side of trainers and a secondary equipment system of a transformer station on the side of trainees. The primary simulation system of the transformer station is used to simulate running states of primary equipment of the electric power system in normal and failed conditions, and transmit data in normal and failed conditions to the secondary equipment system of the transformer station to drive secondary equipment of the transformer station, the transformer station trainees can monitor entire data of the electric power system through the secondary equipment of the transformer station, and the data reflect the real running states of the primary equipment of the electric power system. The transformer station simulation training system provided by the invention can simulate the running states of a power network, forms a complete real-time closed-loop simulation training scene, and can be used for training transformer station operating personnel on the characteristics of protective equipment in a practical running state, enabling the transformer station operating personnel to practice analyzing and handling power network faults, andtraining the transformer station operating personnel for skill tests.

The invention discloses a rapid prototyping simulation method of an aircraft engine control system and belongs to the technical field of design of aircraft engine control systems. First, a control algorithm model is established, the prototype design of the control system is performed through the virtual instrument technology and a real-time hardware platform, the designed aircraft engine control algorithm model is compiled through the automatic code generation technology and downloaded to the real-time hardware platform, and a control algorithm prototype is established rapidly; second, the rapid control prototype is responsible for collecting output signals of an engine simulator after the engine simulator passes through a signal interface unit, relevant control quantities of an engine are calculated according to control instructions and sent to the engine simulator, and the closed loop control over the engine is achieved; finally, a control system designer observes the control effect in real time through a monitoring computer, keeps modifying the control algorithm model according to the requirements of the designer for performance of the control system and repeats the closed loop simulation process of the rapid control prototype till the requirements of the control system designer are met.

The invention relates to a system and a method for a real-time high-dynamic navigation signal simulator. The system comprises a satellite navigation message generating module, a real-time simulating control module, an observation data generating module, a navigation signal processing module, an intermediate-frequency signal generating module and an up-conversion module. The system provided by theinvention can be used for solving the problem of generating a track real-time navigation signal for an external user, meet the developing demands of real-time closed-loop simulation and navigation half-physical simulation, and support an index test of a flight control system.

The invention relates to a hydraulic pressure ABS test stand based on wheel speed closed loop analog, which comprises an industrial computer, a wheel speed generation device, a tested system, a pressure source, a deflation system, a braking system and a data collection system. Test software operated by the industrial computer comprises a whole vehicle model, a tire model, a road model, a braker model, data processing, wheel speed real-time control and a human-computer operation interface; the wheel speed generation device is composed of a motion controller, an AC (alternating current) servo motor driver, an AC servo motor and a gear ring; the deflation system is composed of an electromagnetic valve; the pressure source is composed of a hydraulic station and an oil cylinder; and the braking system is composed of a brake master cylinder, a wheel braking cylinder and a pressure sensor. The test stand can carry out a performance test to an ABS controller, a pressure regulator and a wheel speed sensor through two proposals of closed loop and open loop, and also can carry out an intensified test to the whole ABS system so as to check the reliability thereof. The test stand is applicable to ABS research and development process and also can be used for the production of ABS test equipment in batches.

The invention relates to a simulation test method for the active thermal control circuit of a space optical remote sensor. A test system consisting of a voltage conditioning circuit, an analog to digital conversion circuit, a computer PCI bus driving circuit, an FPGA, a digital potentiometer synthesis conversion processing circuit and a microcomputer is connected to the active thermal control circuit of the optical remote sensor being tested, which forms an optical remote sensor active thermal control circuit closed loop simulation test system and realizes the aim of simulation test. At first, the heating information of a control circuit is collected, the validity of the information is judged, and then according to a pre-constructed thermal network mathematical model, temperature information after changing is fed back to the active thermal control circuit, therefore, the effect of maintaining heating is simulated. The test method can satisfy the long-term, rapid, convenient and clear test and monitor need of the active thermal control circuit of the optical remote sensor.

The invention provides a satellite flight control closed loop simulation system based on a component simulator, which is applied to a system comprising a dynamics simulation server, a sensor simulator, an actuator simulator and a space-borne computer, wherein the formula of data output by the sensor simulator to the space-borne computer is the same as that of data output by a practical sensor to the space-borne computer, and the format of data received by the actuator simulator from the space-borne computer, i.e., the format of data input by an actuator is the same as that of data input by a practical actuator, so that the simulation reliability of the satellite flight control closed loop simulation system can be enhanced effectively; the component simulator is adopted instead of a real physical device, so that the simulation system has the advantages of low cost and low complexity; and meanwhile, the simulation system has the characteristics of high generality, high flexibility and high automatic degree, so that the research period of a satellite can be shortened effectively, and the research cost of the satellite is reduced.

The invention relates to a novel design method of an intelligent alternating-current and direct-current electromagnetic apparatus. An open type background database including electromagnetic systems and contact systems of different structures, shapes and materials is set up, counter force systems and the contact systems are designed according to the needs of on-off currents for counter force and the shape of contacts, the electromagnetic systems meeting the needs are designed according to the counter force systems, and multi-physic-field coupling simulation analysis and structural optimization design are carried out; through multi-software united calling, a multi-physic-field coupling relation between an electric electronic circuit and an electromagnetic apparatus body is introduced into dynamic calculation, and unit time step length closed-loop simulation of a nonlinear time domain of an intelligent control module and the apparatus body is carried out; an arc magnetic fluid kinetic model is built, arc motion conditions under different breaking control schemes are analyzed by combining a dynamic grid technology according to the motion track of the contacts, meanwhile, a breaking process arc equivalent model is obtained according to the arc parameter distribution conditions under different contact strokes at different moments, and arc energy is analyzed. An integrated simulation system with process control and a multi-field coupling electromagnetic apparatus virtual prototype is really built.

The invention provides a moving die simulation test system and method for an intelligent substation protection device, and relates to a model system capable of being effectively applied to power system real-time simulation analysis. A simulation model is built through an RTDS. The intelligent substation protection device and related secondary devices (a network switch and a merging unit) of the intelligent substation protection device are connected. A closed-loop simulation test is conducted on the intelligent substation protection device. Motion and behaviors under various situations of the protection device are observed, and thus the functions of the protection device are examined.

The invention relates to a virtual vibration test system for a spacecraft. The virtual vibration test system comprises a vibration test closed-loop simulation module for simulating a closed-loop control process of a real vibration test and executing closed-loop simulation calculation of a virtual vibration test, a model correction module for correcting a vibration table model, a fixture model and a spacecraft model, a test condition analysis module for indicating a downwards sunken magnitude and a downwards sunken frequency under a high-magnitude vibration test, a fixture evaluation analysis module for analyzing and evaluating the performance of a test fixture and performing modal analysis and virtual vibration test analysis on the fixture, and a test database for storing and supplying calling parameter data and file data to the functional modules. Due to the virtual vibration test, the conventional value simulation result is improved; an instructive measure is supplied to a real test design; insufficient-test and over-test are avoided; and the technical level of the test is enhanced.

An integration simulation test method of space optical remote sensor belongs to integration simulation test technology. A comprehensive simulation test system composed of a comprehensive analyzing and processing device, a special simulation test device, an auxiliary simulation test device and a synchronous clock device is connected on a tested space optical remote sensor to realize real-time parallel integration closed loop simulation test. Under the reference of unitary time provided by the synchronous clock device, first the special simulation test device simulates the work of a space aircraft, or key parts, units or special functions of the space optical remote sensor, collects state, data and signals of the space optical remote sensor, and transmits to the comprehensive analyzing and processing device; then the comprehensive analyzing and processing device transmits the analyzing result to the auxiliary simulation test device in real time to be displayed, printed and transmitted to the special simulation test device in real time so as to form a closed loop simulation test, thus achieving the aims of predicting, judging and appraising the space optical remote sensor rapidly on the ground.

Provided are direct current isolated island operational stability closed loop simulation detection equipment and a detection method. The equipment is provided with a power station monitoring system, an excitation control system, a governor electrical regulating system, a governor actuator system, an extra-high voltage direct current control protection system, a real-time simulation system, an interface interactive system and a power amplifier. The power station monitoring system, the excitation control system and the governor electrical regulating system collect control observation quantity of the real-time simulation system through the interface interactive system and the power amplifier and input control information to the real-time simulation system, and the extra-high voltage direct current control protection system carries out control operation on a direct current transmission system. The detection method is carried out through the equipment. The direct current isolated island operational stability closed loop simulation detection equipment and the detection method can detect frequency stability, voltage stability, machine-network coordination control characteristics of a high-capacity direct current isolated island system, shorten the period of field tests, avoid risks of the field tests, improve safety stability of electric power system operation, and has the advantages of being flexible in operation control, high in precision of simulation results and the like.

The invention discloses a semi-physical simulation system and method of a hypersonic flight vehicle navigation and control system. The system comprise a guidance combination body, a steering engine, apower supply, an upper computer, a lower computer and a test control computer; before the simulation is started, the upper computer establishes a flight simulation model according to a current simulation object, and is compiled and downloaded to the lower computer; and the guidance combination body is initialized. During simulation, the test control computer sends a launching instruction to the lower computer and the guidance combination body; the lower computer performs flight simulation calculation after being controlled by the launch instruction, so that the aircraft attitude and positioninformation at the current moment are obtained and sent to the guidance combination body; the guidance combination body conducts navigation and control calculation according to a time-of-flight sequence after receiving the launching instruction, a control instruction of the steering engine is obtained, then the steering engine is controlled to deflect, the actual position and the control instruction of a rudder shaft are sent to the lower computer, and closed-loop simulation is achieved; and meanwhile, the rudder shaft information and the navigation control result information are sent to the test control computer. After the simulation is finished, precision analysis is carried out.

The invention discloses an induction heating closed loop simulation method based on finite element model and system identification. The method adopts ANSYS software to build a billet electromagnetic induction heating finite element model, and the simulation of billet induction heating process is realized through solving the model, thus obtaining the simulation data. The system input and output time history which is obtained through the finite element simulation is used for substituting the experimental data, a least square system identification method is adopted to process the input and output time history, and thus, system response characteristic parameters are obtained; then, a proportion integration differentiation (PID) feedback controller is designed on the basis of the model; and finally, an ansys parameter design language (APDL) is adopted to introduce the PID feedback controller into the finite element model, so the simulation process of an induction heating closed loop system is realized. The method takes the advantages of the induction heating finite element model, realizes the coupling of electromagnetic induction heating and a control system, can greatly improve the simulation precision, and facilitates the advanced performance analysis of induction heating closed loop control.

The invention provides an agile satellite mission interpretation closed loop simulation verification system and method. Efficiency of key links of simulation verification and inversion modification of current agile satellite mission planning can be effectively enhanced, and correct implementation of agile satellite mission planning can be guaranteed. With application of the agile satellite mission interpretation closed loop simulation verification system and method, firstly a satellite mission host mission interpretation function is simulated, a conventional satellite mission test bed is replaced, mission blocks are interpreted into instruction sets which can be performed by a satellite mission host and information of instruction names, parameters and performing time can be visually displayed in a form mode, and mission block interpretation results are automatically interpreted and abnormal information is outputted so that noting of error mission blocks on satellites can be avoided; secondly, the parameters in the mission blocks and mission block settings can be modified and the mission blocks can be generated again by the system, and iterative analysis is performed on the mission blocks so that correctness can be guaranteed, the risk caused by manual arrangement of the mission blocks can be avoided, and mission block generation efficiency and reliability can be enhanced; and finally the interpretation results of the finally generated correct mission blocks are compared with action sequences generated by a mission planning system so that correctness and rationality of mission planning can be verified.

The invention discloses a multi-body dynamics parameter determination system based on the distributive time trigger and a method thereof. The method comprises the following steps: firstly, a system architecture model based on a time-triggered data bus is established, wherein each aircraft system simulation node is connected onto the bus and comprises multiple simulation modules; secondly, a system dynamics parameter is subjected to calculation through the guiding of the dynamics simulation modules; thirdly, a single aircraft system inner closed-loop simulation process is implemented through a system inner data receiving and dispatching module; fourthly, data exchange is implemented through an outer receiving and dispatching module and other aircraft system simulation nodes; fifthly, the dynamic parameters in a next time is obtained through calculation via a differential equation or a linearization formula, and the synchronization of a distributed system multi-body dynamics parameter is achieved.

The invention provides a method and device for integration of system software of an aircraft engine. The method comprises the steps that the to-be-integrated control system software runs on a virtualhardware platform to constitute a controller assembly; through an interface adaptive assembly, the controller assembly is connected to a model simulation assembly; on a man-machine interface which runs monitoring and injection of the assemblies and provides software testing, a testing instance is read and sent to a running control assembly, adjustable parameters are read and sent to the controllerassembly, and running data of the control system software is received; testing courses of the control system software is controlled in the running control assembly; and behavior features of a controlled object are simulated in the model simulation assembly, and a closed loop simulation environment is provided for testing of the controller assembly.

The invention provides a T-BOX test system and method. A channel simulator simulates a signal transmission environment when a T-BOX carries out data transmission; a signaling tester simulates a communication link used when the T-BOX carries out data transmission; a navigation signal simulation system simulates a navigation signal output by a navigation device; and a real-time system carries out information interaction of hard wire signals and/or bus signals with the T-BOX, wherein the parts above can form a closed-loop simulation test environment with a service background of the T-BOX to testthe T-BOX. According to the provided T-BOX test system, the channel simulator and the signaling tester provide a signal transmission process close to reality for the T-BOX; the navigation signal simulation system provides the navigation information close to reality for the T-BOX; the real-time system provides an interaction environment close to real vehicles for the T-BOX; and the test system cantest function and performance of the T-BOX through the simulated real vehicle test environment.

The present invention provides a multi-wheel individual drive slip frequency steering vehicle united simulation method and system. The method comprises the steps of: creating a whole vehicle rigid multi-body dynamical model at first software, determining input information and output information of the whole vehicle rigid multi-body dynamical model, and outputting a whole vehicle model submodule, wherein the whole vehicle model submodule comprises the whole vehicle rigid multi-body dynamical model, the input information and the output information; creating a driver model at second software, wherein the driver model is configured to output driving data according to input expected data and feedback data; creating a whole vehicle controller at the second software, wherein the whole vehicle controller is configured to receive the driving data, and generate torque information; creating a steering simulation model at the second software, and leading the whole vehicle model submodule, the driver model and the whole vehicle controller into the steering simulation model; and designing a working condition in the steering simulation model to perform simulation analysis of the work condition and obtain a simulation result. The multi-wheel individual drive slip frequency steering vehicle united simulation method and system can perform closed-loop simulation analysis of different work conditions and can improve the accuracy.

The invention relates to a distributed-type real-time comprehensive simulation system of an avionics system. The distributed-type real-time comprehensive simulation system comprises a simulation model (1), a simulation excitation source (2), an aircraft external model (4) and a simulation monitoring device (3), wherein the simulation model (1) comprises an excitation model (11), a device model (12), a monitoring model (13) and a simulation kernel (14). According to the comprehensive simulation system, logic problems existing in design can be found earlier, so that project cost is reduced, and the whole research and development cycle is shortened. Besides, closed-loop simulation can be achieved, a simulation process can be displayed dynamically, and simulation verisimilitude is promoted. In addition, simulation input and output signals can be defined by users, and therefore man-machine interactivity of simulation is greatly enhanced; under the support of the models, distributed-type multidisciplinary comprehensive simulation of the avionics system can be achieved.

The invention aims to provide a device for locking gain and power in an erbium-doped fiber amplifier (EDFA) by using a digital signal processor (DSP). The conventional closed-loop analog control unit is replaced by the DSP, an analog-to-digital (A/D) converter, and a digital-to-analog (D/A) converter; and a high-efficiency and flexible control algorithm is realized in the DSP by using a software mode. The whole control flow comprises the following steps that: four A/D sampling chips of a 14-bit Texas instrument (TI) sample input and output optical power at two stages respectively; after reading the input and output optical power, the DSP of the TI calculates final output optical power by combining amplified spontaneous emission (ASE) compensating power according to the current control mode and the set value of gain or output optical power; and control voltage for driving pump lasers is calculated through a feedforward compensation proportional-integral-differential (PID) control algorithm, and one D/A chip with a 14-bit TI dual channel controls two pump lasers. The one-time control period of the whole closed-loop control system is about 2mu s. The gain and power can be effectively locked and transient and steady indexes of a user are met by coordinating set control parameters.

The invention relates to a simulated closed-loop test method for the layered distributed wireless network of an intelligent transformer station. A simulation data processing controller is provided; the simulation data processing controller obtains the stable operation state of the power system and the sequential solution of the fault dynamic process, a simulation model of the intelligent transformer station is simulated in the time domain, and simulation data is transmitted to a primary host which is connected with the simulation data processing controller via a wireless network card; the primary host is connected with a second host via a wireless network bridge, the primary host and the secondary host are used for synchronous time service, and the simulation data processing controller makes data interaction with a simulation terminal, which is connected with the secondary host via a wireless network bridge, via the primary host and the secondary host; and the simulation data processing controller receives the analog input amount or GOOSE state quantity uploaded via the simulation terminal, and thus switches the corresponding data and controls output data via a preset state sequence, so that closed-loop simulation test is realized.