197 results about "Mathematical simulation" patented technology

A semi-physical simulation testing system of moon soft-land guidance, navigation and control consists of a three-dimensional translation analog module, a three-dimensional turning analog module, a control computer, a simulation computer and a ground survey and master-control computer. The three-dimensional translation analog module and the three-dimensional turning analog module adopt a practicality modeling. Wherein, the three-dimensional translation analog module is used to imitate an orbit motion of a lander relative to the moon surface. A sand table of the moon surface is used to imitate ground features of the moon. The three-dimensional turning analog module is used to imitate an attitude motion of the lander. And other well-developed regular sensors, executing agencies, lander dynamics and kinematics can be replaced by accurate mathematical models built up by the computer. Compared with mathematical simulation, the system can make a GNC proposal and algorithm more effectively and truly verified. Compared with full-practicality analogue system, the system has advantages of low development costs and easy operation.

A test bench for testing a shield machine control system comprises a shield machine function simulation system and a sensing device arranged in the function simulation system, wherein the sensing device is communicated with the shield machine control system to be tested, and the function simulation system can be a physical simulation system, a mathematical simulation system or a combination of the physical simulation system and the mathematical simulation system. The test bench for testing the shield machine control system can completely simulate various functions of various types of shield machines, so as to test the correctness of the shield machine control system in design, assembly and debugging, avoid the risk arising from direct communication with the shield machine when the design of the control system is faulty, and shorten the circle of developing a new machine. Meanwhile, the invention is helpful for optimization and modification of the shield machine control system and remote fault diagnosis on the shield machine operated in a tunnel.

A force feedback and interactive system is provided in the present invention, wherein the force feedback and interactive system utilizes a mechanism for detecting weight or center of gravity and reacted force from an operator on a multi-axis motion platform, and a main controller which is a kernel of data processing and motion simulating of the multi-axis motion platform. Besides having complete mathematical simulation model for calculating reaction force variation according to the received operating command, force status and weight of the operator and having algorithm for simulating the motion of multi-axis motion platform so as to calculate the motion and instantaneous position of the multi-axis motion platform in space, the system can also provide function of force feedback for enhancing the virtual reality while being applied in various Human-Machine Interaction simulating field.

A system with automatic positioning controls for the holographic display of three-dimensional objects interacting in real time with objects of the real world. The person observing the screen (18) has the sensation that the objects are real, which is achieved thanks to a real time perspective correction system (1). The system is used in particular to simulate bowling pins (9). It is positioned on the lane required by means of a dolly (6). The system determines a relation between the information received from the sensors: video cameras (1) (3), dimensions (26), weight (14) (27) and the mathematical simulation models. When the ball is bowled, its physical features are measured and when it hits the pin deck, some holographic pins are displayed on the screen (19). The screen holographically arranges the projected objects over what the bowler (18) sees behind the screen (19). The simulated movements of the pins and the physical interactions with the real objects are determined by exploiting the theory of mechanics in three-dimensional space.

The invention discloses a system of satellite attitude control integrated simulation and an implement method. The system comprises a simulation computer and an interface expansion board; simulation application under five working modes of complete mathematical simulation, component-level semi-physical simulation, component-level semi-physical simulation, whole-spacecraft semi-physical simulation, satellite-ground united simulation and in orbit attitude visualization can be realized through the combining connection of the simulation system and tested hardware; the system integrates a number of functions in one set to reduce the repeated simulation software development work to achieve the universality and generalization of the simulation system; the visualization and operability of a simulation process is enhanced; the whole flow comparison simulation analysis from scheme design to in orbit test of the satellite attitude control system is supported.

The invention discloses a method for optimizing reliability and maintenance strategy of a piece of chemical refining equipment. The method comprises the following steps of collecting the historical testing and maintaining data of equipment inside a chemical refining device; carrying out the regression analysis by a failure distribution function for the historical data to obtain the characteristic parameters of the reliability and maintenance of single equipment; establishing a mathematical simulation model of system reliability of the chemical refining device, and collecting the relevant economic parameters of the device; carrying out the system simulation analysis for the chemical refining device by using the mathematical simulation model of system reliability, then obtaining the characteristics parameters of system reliability, usability and maintenance of the device, and then further obtaining the testing and maintaining scheme of the optimized system equipment, such as inspecting and maintaining order, frequency and cost; and obtaining the spare part stock scheme of the optimized system equipment, such as purchasing quantity, purchasing cycle and spare part stock, thus adjusting the equipment managing strategy of the device. The method for optimizing the reliability and maintenance strategy of the chemical refining equipment reduces the unplanned fault rate of the chemical refining equipment, and provides guarantee for long-period safety operation of the chemical refining equipment.

The invention relates to a force analysis method of a single point buoy mooring system of an extra-large ship under the coupling action of stormy waves and provides a mooring force mathematical model suitable for a single point buoy anti-typhoon mooring system of the extra-large ship, which are used for performing identification modeling on a non-steady motion strained condition under a typhoon environment and performing a mathematical simulation test and actual measurement verification on the force motion of the ship without power and interference effects of the typhoon environment. Required input and output data are provided for the identification modeling of the mathematical model through a ship motion physical model test of a single point mooring ship model under the action of wind, currents and waves; and a mooring curve of a buoy type anti-typhoon single point mooring system is deduced and the influence of all component parts on the mooring curve is analyzed by researching a ship-buoy motion law based on catenary and cubic parabola theories, so that the key technical problem of the design of the single point buoy anti-typhoon mooring system is solved.

The invention relates to a radio altimeter signal simulation system. The radio altimeter signal simulation system comprises a mathematical simulation calculation subsystem used for simulation to generate a model database required by simulation conditions and realizing conversion and management of the model database, and control and treatment of simulation process; an echo simulation subsystem which is connected with the mathematical simulation calculation subsystem, and is used for receiving model data and control instructions, and realizing conversion and output of model data into intermediate frequency signals; an altimeter equivalent unit which is connected with the echo simulation subsystem and the mathematical simulation calculation subsystem, and is used for simulating an actual altimeter, evaluating simulation capacity of the radio altimeter signal simulation system, and realizing retroconversion of signals into height values. The radio altimeter signal simulation system has flexible, economical, lifelike, and complex function simulation capacity, is capable of realizing real-time simulation operation and experimental verification of radio altimeters on total work environment, and is capable of providing support for testing experiments and performance evaluation of radio altimeters, and especially navigation control systems.

The invention relates to a control method for realizing an overload autopilot by using an accelerometer. The control method comprises the following steps of: firstly, calculating a functional relation between the attitude angular rate and the overload of a missile body under an inertial coordinate system; secondly, obtaining a damping circuit grain Kg and a stable circuit gain KA of the overload autopilot at a characteristic point of a missile track by adopting a root locus method of a classical control theory; and finally, constructing a damping circuit by using an accelerometer signal under the missile body coordinate system according to the result obtained in the first step and realizing the overload autopilot by using the accelerometer. According to the control method disclosed by the invention, aiming at the dynamic characteristic of a guide missile, by using the function relation between the overload and the angular rate and using a method of constructing the damping circuit by repeatedly using the accelerometer through the overload autopilot, the mathematical simulation validation can be carried out and a corresponding engineering realization scheme is provided.

The invention relates to a flexible mechanical arm control simulation platform and a working method thereof. The simulation platform comprises a flexible mechanical arm mathematical model, a simulation platform main interface, a control scheme selection and implementation module, a desired trajectory setting module, a control parameter setting module and a parameter status display module. A human-computer interaction interface of the simulation platform is designed by utilizing the GUI language of constructing a graphical interface, and a data interaction channel is established with a controlsimulation system based on Simulink. A user inputs various control parameters and model parameters of the simulation platform on the human-computer interaction interface, and clicks each function button to achieve parameter setting, mathematical simulation running and simulation image display.

The method relates to the field of hydraulic fracturing of subsurface formations. A mathematical simulation model of a pressure pulse propagation inside a wellbore and inside a fracture is created. Pressure pulses are sent to the wellbore, and the response of the well to the pressure pulses is registered. Then, a bottom-hole pressure corresponding to each pulse is determined. An average fracture width is derived by using the mathematical simulation model of pressure pulse propagation inside the wellbore and inside the fracture, and a ratio between the simulated average fracture width and the determined bottom-hole pressure is determined. The said ratio is extrapolated to a zero-width point, and the closure pressure is determined as the bottom-hole pressure corresponding to the zero width.

Provided is a switch reluctance motor memory inductor equivalent model. Two second-generation current transmitters AD844-U1 and AD844-U2, two operation amplifiers TL084-U3 and TL084-U4, and a multiplying unit AD633-U5 are used for forming a memory inductor which does not comprise a memristor passive two-terminal element, so that the switch reluctance motor equivalent model is quick in real simulation and control and can reflect the non-linear relationship of magnitude of phase currents and the position angles of a switch reluctance motor flux linkage and a rotor thereof in real time, quick direct mathematical simulation of a switch reluctance motor system can be achieved, important application value is achieved on real-time simulation and real-time control of a switch reluctance motor, and the switch reluctance motor memory inductor equivalent model can be effectively used for real-time simulation and real-time control of the switch reluctance motor. The equivalent model lays a solid foundation for real-time simulation and real-time control of the switch reluctance motor system and has wide application prospect.

The invention relates to an AODV protocol wireless intelligent network-based satellite attitude control simulation system. The satellite attitude control simulation system includes a physical simulation system and a mathematical simulation system; the mathematical simulation system is provided with an optical fiber gyroscope mathematical mode and a reaction flywheel mathematical model; the physical simulation system performs physical simulation of satellite pitching channel attitude control; the mathematical simulation system performs mathematical simulation of satellite rolling and yaw channel satellite control; the physical simulation system includes a single-axis air bearing table, wireless intelligent network nodes, a spaceborne computer, an optical fiber gyroscope, a reaction flywheel and a power source; and the optical fiber gyroscope, the spaceborne computer, the reaction flywheel and a simulation computer are respectively with one or a plurality of wireless intelligent network nodes and can communicate with each other through the wireless intelligent network nodes. The AODV protocol wireless intelligent network-based satellite attitude control simulation system of the invention has the advantages of high simulation flexibility, low cost and high implementation performance, and can improve the flexibility and the feasibility of a small satellite attitude control simulation test.

The invention discloses a semi-physical simulation method and a simulation device for the aerodynamic effect in a high-altitude and high-speed environment. The method comprises the following steps: in a high-altitude and high-speed working environment of an airborne camera, pressure and temperature data of the surface of an optical window is calculated through a mathematical method, and the optimal thickness of the optical window is optimized; then, the pressure and temperature data and the optimal thickness of the optical window directly act on an aerodynamic effect physical simulation device, differential pressure and temperature adjustment is carried out directly on the surface of the optical window, and physical simulation experiment is carried out; and finally, feedback to a mathematical simulation model is formed based on the physical experiment result. By adjusting pressure and temperature systems of inside-cabin and outside-cabin environment simulation chambers, a differential pressure environment and a high-temperature environment are established on the surface of the optical window, and an aerodynamic effect caused by high-altitude and high-speed air flowing across the surface of the optical window is simulated. Scientific experiment basis and conditions are created for the ground research of the influence of aerodynamic pressure and aerodynamic heating effect in a high-altitude and high-speed environment on the performance of the optical window.

An anti-blocking design method based on two-phase stream simulation for the drip irrigator features that according to the mathematical simulation about the two-phase stream in the flow field of said drip irrigator, the region in the flow channel, where the solid is easily deposited, is analyzed out and the influence of the flow channel structure to the delivery and deposition of solid is further analyzed. On this basis, the structure parameters of flow channel are modified and said simulation is repeated until no obvious deposition of solid.

The invention provides a semi-physical simulation method of an inertially stabilized platform control system. Pure mathematics simulation is real difficultly in the design of the inertially stabilized platform control system, the cost of real object experiments is high, and models are difficult to change. A digital model portion and a real object portion are used in the method, wherein the digital model portion is used for modeling detection feedback links of a kinetic model, a posture control law, revolving speed and an angular position of a stabilized platform and converting the detection feedback links into real-time procedures; a current value measured by the real object portion is corrected into output torque of an executing mechanism; the output torque is substituted into a digital model to obtain an armature voltage expected value of the next moment; the armature voltage expected value is transmitted to a hardware portion; and the real object portion comprises a controller, a driving circuit and a current detecting circuit. The problem that a real effect is difficult to achieve when mathematical simulation is carried out by the real object portion is solved. The semi-physical simulation method of the inertially stabilized platform control system has advantages of high instantaneity of the real object experiments, high degree of confidence and convenience, flexibility and economy in mathematical simulation. A design period of the inertially stabilized platform control system can be shortened, and the cost is reduced.

The invention relates to a rapid prototype design and semi-physical simulation method and system for a flight control system and belongs to the field of flight control. The rapid prototype design and semi-physical simulation system comprises a flight dynamic model operation module, a three-axis rotating table, an attitude sensor, a pressure conversion device, a pressure sensor, an analog computer, a lifting steering engine, an auxiliary wing steering engine, a direction steering engine and a balancing steering engine. By designing and building a prototype and semi-physical simulation system for the flight control system, flight control system design, mathematical simulation and a prototype system can be realized on the basis of the model, performance testing and software verification carried out on the flight control system can be finished in real time through semi-physical simulation, and integration of flight control system design, mathematical simulation, the prototype system and semi-physical simulation can be realized.

The invention relates to a method for representing the component and isotope fractionation effect in the natural gas adsorption and desorption process of shale and belongs to the technical field of instruments used for analyzing materials by aid of measuring physical properties of the materials. The problem that in the prior art, due to the fact that a large amount of gas is lost in the drilling and sampling process, the experiment result cannot completely reflect the desorption process of shale gas is solved. According to the method, a competitive adsorption experiment is carried out in the shale gas adsorption and desorption process under high temperature and high pressure conditions, qualitative analysis is conducted on component fractionation in the process, qualitative analysis is conducted on isotope fractionation, and meanwhile a Langmuir model and an adsorption model are adopted for conducting numerical simulation on the adsorption quantity and the isotope value. Thus, elaborate description of the competitive adsorption effect in the shale gas adsorption and desorption process is realized, and it is beneficial for guiding gas-driven exploitation of the shale gas. The method can be widely applied to mathematical simulation research, gas-driven exploitation of the shale gas and other occasions.

The invention discloses a comprehensive test system of failure satellite control in space. The comprehensive test system comprises a central control unit, a measurement and control unit, a motion andenvironment simulation unit, a control mechanical arm unit, a remote operation unit and a scene simulation unit, wherein the measurement and control unit is a central link of each unit information interaction, the central control unit is used for developing and downloading a dynamics and control and control model of the space failure target operation, and data storage and monitoring are carried out in the simulation process; and the measurement and control unit is used for operating various dynamics and control software, data acquisition and processing software and measurement and control software, and completing the real-time generation and transmission of the control instructions; the motion and environment simulation unit is used for simulating the motion of a serving satellite and a target satellite in the space; the control mechanical arm unit is used for simulating the space capture of the failure target satellite; the remote operation unit is used for controlling an operation platform and mechanical arms to move through remote operation to complete a specified task; and the scene simulation unit is used for driving a scene model according to the mathematical simulation and the actually-measured data to reproduce a spatial operation process.

The invention relates to a method for the continuous casting of a metal strand in a continuous casting plant, a strand being withdrawn from an in-line die, supported in a strand support unit, cooled by a coolant and optionally metallurgically reduced, thermodynamic changes in the entire strand being calculated in a mathematical model containing a thermal conduction equation. The aim of the invention is to provide a method which can be used to improve the product quality of a metal strand, for example by reducing the porosity and/or liquation and by improving the surface quality and form stability. Said aim is achieved by a method, according to which the natural shrinkage of the strand is calculated in real time in the mathematical simulation model, taking into consideration the physical parameters of the metal, the temperature in the casting distributor, the frequently measured withdrawal speed, the cooling of the strand and the thickness of the strand and strand guide rollers of the strand support unit, said rollers being placed against the strand, are set by taking into consideration the natural shrinkage of the metal strand.