660 results about "Control system design" patented technology

A robotic system for overlapping radiofrequency ablation (RFA) in tumor treatment is disclosed. The robot assisted navigation system is formed of a robotic manipulator and a control system designed to execute preoperatively planned needle trajectories. Preoperative imaging and planning is followed by interoperative robot execution of the ablation treatment plan. The navigation system combines mechanical linkage sensory units with an optical registration system. There is no requirement for bulky hardware installation or computationally demanding software modules. Final position of the first needle placement is confirmed for validity with the plan and then is used as a reference for the subsequent needle insertions and ablations.

This invention is related to so-called combined cycle co-generation installations, and it addresses present concerns of the industry. Among these, combustion stability, corrosion (due to large water content in the flue gases), large heat transfer areas, and the like. In some embodiments, an additional heat exchanger is added to heat combustion air with a portion of the exhaust gases resulting from an engine, preferably a gas turbine. As a result, the efficiency of the cycle will improve, the oxidant will be enriched by above 50% oxygen, the combustion process will be enhanced, and the dimensions of the boiler may be reduced. It is considered that the combustion air will require between 10% and 80% of the total flue gas volume, more preferably between 20% and 40%. This is the portion of the flue gases sent through the heat exchanger. A control system designed to optimize the flow of the different streams is also presented. Other inventive embodiments forego heat exchanges in lieu of precise control of two flows of exhaust gas, with preferred addition of additional oxidant to the boiler bumers.

A synchronized control method for a three-phase three-level boost-type rectifier with reduced input current ripple and balanced output voltages is disclosed. The proposed control allows simplifying the control circuit as much as possible without compromising the rectifier performance. In fact, besides simplicity, the control method featured synchronized command signals to de switching devices, minimized input current ripple, full controllability of the output voltage, dynamic balance of the output center point, constant switching frequency, simplified design of EMC filters, good transient and steady state performance, and low cost. The invention described first the most important configurations that the three-phase three-level boost-type rectifier may assume and studied the converter's operation. The concept involved for output voltage, input current, neutral point balance and control system design was presented.

The invention provides a design and realization method of a redundant and fault-tolerant safety instrument control system based on a fieldbus and ARM (advanced RISC machines), comprising the following steps: by virtue of redundant and fault-tolerant configuration of a system power supply, input modules, a CPU (central processing unit) and output modules, four core processors communicate with respective and corresponding I/O (input/output) modules by a CAN (controller area network) bus so as to carry out field signal acquisition and control command output, and hardware 2oo4 redundant and fault-tolerant voting is carried out on the output signals of four channels on an output voting module, so that mis-stop of the system caused by single-channel hardware failure is avoided, the function safety level of the redundant and fault-tolerant safety instrument control system is ensured to reach SIL3 (safety integrity level 3), in-time and fast response and protection are carried out on dangerous states of protected field equipment, further a production device enters a predefined working condition of safe stopping, and the safety of staffs, equipment, production and the device is guaranteed.

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.

The invention provides a control method and a system thereof for a biaxial gas-steam combined cycle unit; the method includes that: the actual power value and the target power value of a biaxial gas-steam combined cycle unit are acquired; the load of a gas turbine is controlled according to the deviation of the actual power and the target load value to enable the actual power value to accord with the target load value. The invention fulfills the domestic control technique gap of the biaxial gas-steam combined cycle unit and has great reference value on the coordinated control system design of the multi-axial gas-steam combined cycle unit. Besides, the invention also proposes a control strategy of the gas-steam combined cycle unit according to the control characteristics of a gas turbine, an exhaust-heat boiler and a steam turbine, realizes the integral control function requirements of the combined cycle unit, guarantees the quick load increasing and decreasing demands of the whole combined cycle unit, and also meets the requirements of the power grid dispatching department. The control method and the system have clear control strategy and logistics, strong controllability, higher generality and practicality.

A suspension control system designed to impart a variable supplemental resistive force to control vehicle body roll and to improve suspension performance through the use of magnetic rheologic force devices. Each of the force devices impart rheologically adjustable amounts of force and resistance to the vehicle suspension system based on a variable magnetic/electrical field created within the force devices. The control system further includes a plurality of sensors that monitor vehicle components and performance parameters, and send signals to a logic unit. The logic unit processes input from the sensors and sends electrical commands to the force devices, which take the appropriate action to optimize suspension system performance. The use of the magnetic rheological force devices supplants traditional stabilizer bars and the associated linkages, fasteners, brackets and insulators.

The invention discloses an unmanned aerial vehicle autonomous formation evaluation index and model prediction control (MPC) formation control method and belongs to the technical field of flight control. According to the method, a definition relevant to unmanned aerial vehicle autonomous formation, a computing method of the collision prevention probability of unmanned aerial vehicle autonomous formation and an unmanned aerial vehicle autonomous formation evaluation index are provided, and the MPC formation control method applicable to unmanned aerial vehicles is provided. The method solves the problem how to give out the collision prevention quantitative index which should be followed by design of an autonomous formation flight control system when it is known that the unmanned aerial vehicle autonomous formation scale is M, the average expectation distance between unmanned aerial vehicles in formation is dr, and the collision probability of the whole formation is required to be smaller than Pc. The method provides a quantitative index basis for engineering design of the unmanned aerial vehicle autonomous formation control system, and the collision problem the unmanned aerial vehicles in dense formation is solved.

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.

A control system for mixing at least two materials in a physical system having two or more tanks comprises at least two actuators, each actuator being operable to introduce a material into a first tank to form a first mixture, the first mixture flowing into a second tank to form a second mixture and a controller operable, based on a commanded input, to control the at least two actuators to obtain a density of either the first mixture or the second mixture and a volume flow rate of the second mixture out of the second tank, wherein the density is controlled independently from the volume flow rate.

A spa control system designed to reduce maintenance cost by providing modular construction for major control functions, with built-in diagnostic capabilities for isolating defective spa components. Multi-colored LEDs on the spaside panel constantly report the status of each component of the spa as well as the status of the functional modules themselves. Each time a component is activated, measurements of operational parameters, such as load currents, are instantly made and evaluated so that the proper LED color can be presented at the spaside. Since major functions such as audio, LED control, wireless, and spa logic are separated into removable modules, repair of the control system requires less time and less skilled personnel. Other design improvements, such as direct monitoring of heater element temperature and the purging of pumps on an as required-basis, enhance the spa's overall reliability and thus reduce the need for maintenance.

This invention relates to an automated control system and method that furnishes viewers with individualized automated editing and retrieval capabilities over the contents and length of a variable content video program in order to produce a transparently continuous and complete show. The system capabilities include an automated flexible control system design that enables an operator to selectively apply different editing criteria to the variety of subject matters that may be contained within the program. The system controls also include an automated capability for efficiently previewing program scenes of pre-identified categories and classes of subject matter and a capability for determining their inclusion in the program seen by the viewer. Finally, the control system provide a keyword/menu segment/program retrieval facility from an existing program and program database, and a requesting capability for programs to be produced according to viewer-specified requirements.

Based on a neural network technology and an instruction filtering inversion method, the invention discloses a robust fault tolerance control system design structure based on instruction filtering inversion. Firstly, a mathematical model of an NSV attitude control system is given out, uncertainties and external disturbance caused by modeling errors are considered based on the mathematical model, a state equation of the NSV attitude control system under the fault of a control surface is also considered. The method mainly includes the two design parts including design of an auxiliary system and design of a controller based on the auxiliary system. The auxiliary system is introduced into the neural network to ensure robustness of the auxiliary system, and stability of a closed-loop system is strictly proved through Lyapunov theorem. Meanwhile, simulation is carried out on an attitude control system of a corresponding air vehicle, and a result shows that the method enables the uncertain flight control system with the external disturbance to have the ideal fault tolerance tracking performance under damage to the control surface.

The invention discloses a design method for a photovoltaic microgrid supply-demand control system containing distributed energy sources, aiming at improving system stability, scheduling response capability and economy. A 24-hour operation plan of a photovoltaic microgrid is calculated by predicting photovoltaic and local load power values and after fully considering the running cost of distributed power supplies, during running, the operation plan is revised in real time by the supply-demand system according to the latest photovoltaic and load prediction results, finally, the operation plan and grid-connected point power serves as input of the control system, and the output power of each distributed power supply is controlled. By the design method, the operation plan can be adjusted in real time, supply-demand stability in the system and response to high grid are effectively guaranteed, and meanwhile, maximum running benefit of the photovoltaic microgrid is achieved

The invention discloses a design method of a concept prototype of a flight control system, which belongs to the technical field of design of the control systems. The method comprises the following steps: step 1) carrying out demand analysis, management and confirmation on the flight control system; step 2) carrying out system analysis and confirmation on the flight control system, and carrying out structural and functional division on the system; step 3) designing all member simulators of the flight control system; and step 4) carrying out system level design and simulation on the flight control system, and establishing the concept prototype of the flight control system. The seamless butt joint between Rhapsody software and Matlab software can be realized by utilizing the point-to-point way, and design data in the two types of software can be organically combined. Compared with the prior art, by adopting the method, the correctness of the design of the flight control system from a top layer can be ensured, and the design efficiency of the whole flight control system can be greatly improved.

The invention discloses a guidance method with terminal restraint based on a virtual target point and belongs to the technical field of aircraft guidance and control systems. By using a target virtualization method, an aircraft can fly in the optimum height to attack a target; a virtualized target is positioned, above a real target, in the height, namely a detonation height which is required for a damage element; by designing a guidance law, when the aircraft reaches an imaginary target, a warhead detonates; and the conventional mode of attacking the real target by flying is changed into a guidance mode of flying to the virtualized target and detonating according to a required attitude angle. By adoption of the guidance law of the method, the aim that the aircraft with the explosion-formed damage element flies and attacks in an expected height can be fulfilled, the requirement of the optimum detonation height of the damage element is met, the problem of the attitude angle of the aircraft with the explosion-formed damage element during end attacking can be solved, and the requirement of the detonation moment of the damage element on the attitude angle of the aircraft is met.

A design and control method for the optimizing control system of intermediate rolling mill and heating furnace in order to improve the heating quality of billet in the heating furnace and save energy features that the heating furnace and intermediate rolling mill constitute a closed loop system, the information (rolling force, temp, etc) is fed back to heating furnace for dynamically changing the heating temp, and the optimizing control strategy and control algorithm are used in the billet heating process.

The invention relates to the technical field of single levitation chassis testing for a maglev train, in particular to an electromechanical coupling vibration test device for the maglev train. The device comprises a primary platform for simulating ground support, a secondary platform which is positioned above the primary platform and simulates a track beam, and a track beam rigidity adjusting system for connecting the primary platform and the secondary platform, wherein the track beam rigidity adjusting system and the secondary platform supported by the track beam rigidity adjusting system form simulated maglev train track beam characteristics; and a hydraulic shock excitation system which applies excitation to the primary platform so as to simulate geometrical irregularity of track ground is fixed under the primary platform. The defects of the simplified single-point test or complete-vehicle debugging test for the conventional maglev train are overcome, the complex laboratory simulation of levitation control, elastic beam and coupling vibration environment of a levitation chassis mechanism for the maglev train is realized, the gap in research of key technology for domestic and overseas maglev trains is filled, and a scientific test means is provided for design of a levitation control system of the maglev train, the track beam characteristics and design of the mechanical structure of the levitation chassis.

The invention discloses a spacecraft attitude stability control method by using a biasing tether. The method comprises: a system dynamics model is established; a nonaffine non-linear system model is converted into an affine non-linear system model; speed information is used as a virtual control value and a controller is designed; the designed virtual control value is used a control instruction and a speed/angular speed controlled is designed; and an anti-saturation module is added into the controller and an influence caused by movement limitation of a tether connecting point can be suppressed. According to the invention, on the basis of movement of a biasing tether point, an attitude of a capture mechanism is controlled, thereby substantially reducing fuel consumption of the capture mechanism during the operation task process. In addition, the nonaffine non-linear system model is converted into the affine non-linear system model by means of first-order taylor expansion and that the similarity and error meet the Lipschitz condition is demonstrated; and when the system design is controlled, an adaptive compensation item compensation module error is designed. The method is simple and the practicability is high.

The invention discloses a five-phase permanent magnet synchronous motor model prediction torque control method, and belongs to multi-phase motor alternating current control system design and manufacture in the field of power electronics and power drive. The main steps are as follows: first a sector where a dead-beat voltage vector is is calculated, and only four voltage vectors (two medium vectors plus two large vectors) in the sector are selected as an input set of model prediction torque control, thereby realizing real-time updating; and then a prediction model is utilized to perform prediction calculation on the four voltage vectors in the input set, and combined with an objective function, an optical voltage vector is selected as an input of a system at the next moment. The method provided by the invention adopts model prediction torque control, has excellent dynamic response performance, and is relatively small in calculation amount, digital realization is relatively easy, and the pressure of a digital chip is relieved.

The invention provides a track following method based on a neural network and a PID algorithm, and is mainly used for a tracking scheme of an intelligent driving automobile on a driving map. Normal PID control is combined with neural network control to give play to respective advantages thereof to form so-called intelligent PID control. The method can enable the intelligent driving automobile to follow an expected track; a control system designed through adoption of a neural network method has better real-time performance, stronger adaptability and higher robustness. Computer simulation experiments and real automobile experiments show that the control based on the neural network and the PID algorithm has better real-time performance, stronger adaptability and good control results compared with normal PID control.

The invention relates to a method for designing a Terminal sliding mode controller of a hypersonic vehicle. The Terminal sliding mode control has an advantage that a system on a sliding mode surface can be converged within limited time. In order to keep the nonlinearity of a model and to facilitate the design of a control system, an input-output linearization method is used for processing the model in the paper, after that, state variables are reselected according to the design requirements of the Terminal sliding mode control, and a nonlinear sliding mode surface is designed; a sliding mode control law is designed for the designed Terminal nonlinear sliding mode surface, to ensure that the system can reach the sliding mode surface, and to prove the stability of the system; finally, the given control law is subjected to simulation verification, and the results show that the designed sliding mode controller can realize the effective control of the hypersonic vehicle.

The invention relates to a control method for a photovoltaic grid-connected inverter on the basis of back-stepping sliding-mode control. The control method is technically characterized in that direct current voltage Udc of a photovoltaic side bus is collected, a mathematical model of a photovoltaic grid-connected single-phase voltage full-bridge inverter is set up, a tracking error of a control variable uac is set, a back-stepping sliding-mode control model of the photovoltaic grid-connected single-phase voltage full-bridge inverter is set up, and the single-phase photovoltaic grid-connected inverter is controlled according to the mathematical model and the back-stepping sliding-mode control model of the photovoltaic grid-connected single-phase voltage full-bridge inverter. The control method is reasonable in design, a back-stepping method and a sliding-mode control method are combined, the stable state and the dynamic property are good, and the control method is suitable for linear and non-linear loads and adapts to engineering application reality, provides a new thought for the inverter control system design and has the good engineering application prospect.