572 results about "Design control" patented technology

This invention enhances the usability of the human-computer interface by disclosing a technique for the display of single and multi-generation pop-up controls at a location that best meets the user's criterion of an optimal display location. The technique determines the minimum size of a rectangle capable of displaying the actual or likely maximum size of pop-up controls requested during any given activation of the subsystem that manages display of requested controls. The invention then identifies a location that assures the said rectangle either has no overlay or a minimum overlay of the screen area of current interest to the user while avoiding display clipping. A fixed-point is now determined within said rectangle based on physical characteristics of the controls to be displayed that permits display of descendant controls in a backward cascade that enables the user to maintain visual focus at a fixed screen location while manipulating successive controls. The invention provides the user with the ability to redisplay any previously displayed control irrespective of control type as well as provide a "Done" capability for appropriately designed controls that permits the user to convert a single selection control into a multi-selection control. As an adjunct to the reverse order the invention provides four capabilities that permit the user to undo and redo arbitrary services via performed via redisplay of ancestor controls.

The invention discloses an automatic-driving intelligent vehicle trajectory tracking control strategy based on deep reinforcement learning. For an intelligent vehicle automatic-driving task, accordingto an action-critics structure in a deterministic policy gradient (DDPG) algorithm, a double-action network is adopted to output a steering wheel angle command and a vehicle speed command. A main reviewer network is designed to guide the updating process of the double-action network, and the stragety specifically comprises the steps of describing an automatic driving task as a Markov decision process: < st,at,Rt, st +1 >; initializing a'double-action 'network in the improved DDPG algorithm by adopting a behavior cloning algorithm; pre-training a'reviewer 'network in the deep reinforcement learning DDPG algorithm; designing a training road containing various driving scenes to carry out reinforcement learning online training; and setting a new road to test the trained deep reinforcement learning (DRL) model. The control strategy is designed by simulating the human driving learning process, and automatic driving of the intelligent vehicle in the simple road environment is achieved.

The invention relates to a spacecraft fault tolerance attitude cooperation tracking control method based on a normalized neural network, and belongs to the technical field of spacecraft formation flight. According to the method, an attitude motion model of a single spacecraft is built, errors are defined, a control law is designed for the model, a sliding mode function is designed, the derivative of the sliding mode function is solved, an error model is obtained, a control law based on an input normalized neural network is designed, and the states of the spacecrafts are cooperative and consistent; each spacecraft calculates the required control torque according to attitude information of itself and the adjacent spacecraft, the calculated control torque is acted on the corresponding spacecraft via an execution mechanism of each spacecraft, the angular velocity is solved via an obtained attitude dynamic equation, a unit quaternion attitude tracks an expected attitude via the attitude dynamic equation, and consistent attitude of the spacecraft formation is finally realized. According to the method, estimation errors of non-linear function approximation are reduced, the calculating time is reduced, and the convergence rate and the control precision of the system are increased.

There are many inventions described and illustrated herein. In one aspect, the present inventions relate to oscillator systems which employ a plurality of microelectromechanical resonating structures, and methods to control and/or operate same. The oscillator systems are configured to provide and/or generate one or more output signals having a predetermined frequency over temperature, for example, (1) an output signal having a substantially stable frequency over a given/predetermined range of operating temperatures, (2) an output signal having a frequency that is dependent on the operating temperature from which the operating temperature may be determined (for example, an estimated operating temperature based on a empirical data and/or a mathematical relationship), and/or (3) an output signal that is relatively stable over a range of temperatures (for example, a predetermined operating temperature range) and is “shaped” to have a desired turn-over frequency.

The invention relates to an RBF neural network adaptive dynamic surface control method based on a flexible joint of a robot arm, belonging to the technical field of artificial intelligence and intelligent control. The invention aims at modeling the flexible joint existing in the robot arm, and designs a controller by combining the RBF neural network and the dynamic surface technology with an adaptive control method. The RBF neural network is used to compensate the uncertainties of system parameters, an adaptive law is used to adjust the weights of the neural network to improve the approximation ability of the RBF neural network to nonlinear functions and eliminate the need for precise dynamic model of the robot arm. A position tracking control algorithm suitable for the light robot arm with flexible joints is studied. At last, the design controller is verified by a simulation example, and the invention can ensure that the joint can effectively track a given signal under the condition that the output torque of the robot arm is limited, the tracking error is unconstrained in a certain range, and all signals are semi-globally bound.

Automated facilities are provided for uploading media program information through a network connection to an automated encoding system. An encoding request is received from a client which requests that the media program information be encoded in one or more encoding formats to produce publication-ready-media information. Automated facilities also provide ancillary services associated with the publication-ready-media information such as organization control, design control and publication control of the publication-ready-media information.

The invention relates to a precise control method of an atom spin SERF (Self-Exchange Relaxation-Free) state for stabilizing an atom spin device, which comprises the following steps that firstly, a precise equation is established for the atom spin SERF state, and a modulation method is adopted to measure the atom spin polarizability to establish a control target; then a control system model as precise as possible is established on the basis of an SERF model, and a parameter identification method is adopted to estimate unknown parameters of the model; and finally, according to the control target, a special structure design control law of the established model is fully used, i.e. the switching time, frequency, orientation and power of laser and the switching time of a modulation magnetic field are optimized, and the atom spin SERF state is precisely controlled in real time in accordance with a quantum control algorithm. By using the precise control method, the atom spin relaxation time is increased, and the problem of instability of scale factors of atom devices such as an atom spin gyroscope and an atom magnetometer based on the atom spin SERF effect is solved. The precise control method can be used for improving the long-time drift precision and the low-frequency sensitivity based on the SERF atom spin device.

A system and method to operate an electronic device, such as a memory chip, with an output driver circuit that is configured to include an ODT (On-Die Termination) mode detector detects whether there is sufficient internal clocking available to operate the ODT portion in the output driver in the synchronous mode of operation or to switch the operation to the asynchronous mode. The clock-sufficiency based determination of internal ODT mode of operation (synchronous vs. asynchronous) avoids utilization of complex and inflexible clock processing logic in an ODT control unit in the output driver. This enables the actual clocking to the ODT circuitry to be changed during various device operational modes (e.g., active, power down, etc.) without re-designing the ODT control logic for each of those modes. The simplicity and flexibility of the ODT mode detector design allows for efficient use of chip real estate without affecting the signal transfer speed of the output driver in the electronic device. Because of the rules governing abstracts, this abstract should not be used to construe the claims.

A spacecraft attitude-track integrated backstepping tracking control method is provided, and aims to solve the problems that an existing method respectively uses separate control modes to track the spacecraft track and attitude, so the tracking effect is poor; the method comprises the following steps: 1, building a spacecraft attitude-track integrated relative kinematics and dynamics model according to dual quaternions; 2, designing a controller according to a backstepping method and the spacecraft attitude-track integrated relative kinematics and dynamics model built in step 1; 3, designing an anti-saturation method based input bounded controller according to the controller designed in step 2. The method considers the input bound problems on the backstepping controller base, and designs the anti-saturation node based input bounded backstepping controller; the method can track the spacecraft and realize the 6-degree of freedom attitude-track cooperation tracking of the target spacecraft, is suitable for practical in orbit conditions, and applied to the spaceflight field.

The invention discloses a subcritical coordinative control method based on multiple model predictive control. The method comprises the following steps: determining a plurality of preset local prediction models according to a non-linear work condition range, as well as dynamic responses of main steam pressure and power of a subcriticla machine set; designing a controller for each local prediction model, selecting a control variable, and obtaining an output increment of each local prediction model through an interpolation formula; and during each control period, obtaining an actual control output increment according to an output increment of each controller in a weighing manner; and correcting a feed-forward channel. By adopting the method disclosed by the invention, control output during a transition period can be smoothed, as a result, load and pressure response characteristics of the machine set can be improved effectively; and the subcritical coordinative control method based on multiple model predictive control can adapt to large-scale change in work conditions.

The invention discloses a voltage control type virtual synchronizing method of a double-feed wind power generator set. Through simulating inertia and a frequency-modulating and voltage-modulating characteristic of a synchronizer, the set can be different from a characteristic of no electric grid frequency change response in a traditional current control type, thereby possessing capability of supporting voltage and frequency of a weak power grid based on the voltage control type through virtual inertia. The method provides and realizes a VCT-DFIC virtual synchronous control structure of which an inner ring is controlled by an improved double-feed generator stator voltage rotor current double-closed-loop structure based on adaptive stator virtual impedance and transmission line sag voltage feedforward compensation in a control manner which includes crossed control between stator voltage and rotor current and furthermore an outer ring is controlled by a virtual synchronous realizing algorithm. The method realizes output power control in VCT-DFIG grid integration operation in a weak grid condition with any actual impedance and effective decoupling, and furthermore a designed control structure realizes higher inertia and frequency supporting capability of the double-feed generator.

The invention relates to a reliquefaction device for boil-off gas from a liquefied natural gas vehicle gas filling station, which belongs to the technical field of low-temperature liquefied gas storage and transportation. The reliquefaction device comprises a storage tank of the gas filling station, a compressor, a cooler, a heat exchanger, a throttle valve, a gas-liquid separator, an expansion machine and a submerged cryogenic pump. The reliquefaction device takes BOG which needs to be liquefied as a refrigerant and adopts the single-stage compression and the single-stage expansion and throttling refrigeration method, thereby leading the BOG to achieve the liquefaction purpose. When the pressure of a system reaches the designed control value, the reliquefaction device is started automatically for liquefying one part of the redundant BOG and further reducing the temperature and the pressure in the system, when the pressure of the system is reduced to the required value, the reliquefaction device is stopped automatically. The reliquefaction device can solve the BOG emptying problem of the LNG filling station through reliquefaction of the BOG. The reliquefaction device can reduce the potential safety hazard caused by BOG emptying, and have significant social benefits and economic benefits for protecting the environment and reducing the waste of resources.

This invention provides an upgrading management method and a system for software of set-top-box, in which, the method includes: after a manufacturer of set-top box provides upgrading materials to an operation runner, which upgrades the management including the steps: 1, uploading and verifying the upgraded materials including one or many upgrading data files and a describing file, 2, adding upgrading tasks to control and design the content of descriptor related to upgraded and localized information of the pre-upgrading set-top box, 3, deriving the localized information of said set-top box to play and upgrade data with an electronic program directory.

The present invention discloses a hypersonic aerocraft neural network composite learning non-backstepping control method. The technical problem is solved that a current hypersonic aerocraft control method is bad in practicality. The technical scheme comprises: performing transformation of an attitude subsystem strict feedback form, obtaining an output feedback form, employing a high-gain observer to perform estimation of newly defined variables, and providing basis for subsequent design of a controller; allowing the controller to consider the lump nondeterminacy of the system, and only requiring one neural network to perform approximation, wherein the controller is simple in design and is convenient for engineering realization; aiming at control of unknown cases of a gain function, designing the controller based on the parameter linearization expression mode; and introducing system modeling errors, and constructing a neural network composite updating rule and a parameter adaptive composite updating rule to realize fast tracking of a hypersonic aerocraft. The effective estimation of unknown states is realized based on the high-gain observer, the repeat design of the virtual controlled quantity is not needed so as to simple the design of the controller. the realization is easy, and the practicality is good.

The invention discloses a multi-joint industrial mechanical arm backstepping finite time sliding mode control method considering system sum disturbance. The multi-joint industrial mechanical arm backstepping finite time sliding mode control method includes the steps: establishing a multi-joint industrial mechanical arm system model; designing a system three-order expansion state observer for accurately estimating the system sum disturbance item; based on system sum disturbance estimation, and for the system model (2), performing system backstepping finite time sliding mode control rule designby combining the backstepping design idea and the finite time sliding mode technology. The multi-joint industrial mechanical arm backstepping finite time sliding mode control method has strong robustness for nondeterminacy factors, such as model parameter perturbation and external bounded disturbance, and can guarantee fast and stable finite time tracking control of the desired trajectory of the system, so that the designed control method is convenient for application in practical engineering.

The invention discloses a mental workload assessment method based on multi-physiological parameter method integration. The method includes the steps of 1, designing controlled variable experiments oriented to five characters of a target complex task, acquiring functional physiological data of the experiments, and preprocessing the acquired functional physiological data; 2, completing the extraction of sensitive physiological characteristics reflecting the changes of different characters on mental workloads from the physiological data; 3, screening the physiological characteristics to remove interference information in the physiological characteristics; 4, integrating physiological indexes under different characters to obtain a comprehensive physiological parameter characteristic system; 5,according to the physiological characteristics under different characters, conducting regression on the physiological data under the task characters by machine learning; 6, according to the comprehensive physiological indexes, describing the mental workload level of a current operator. By means of the method, the operation result can be directly evaluated, and high real-time performance is achieved; besides, the accuracy is high, and the status of task execution personnel can be monitored in real time.

The invention provides a flexible satellite neural network backstepping sliding mode attitude control method, relates to a flexible spacecraft attitude control method, and aims at solving a problem of perturbation generated by plate flexible vibration and antenna rotation and a problem of enhancement of steady state precision and stability of existing attitude control methods. According to the method, a flexible satellite attitude kinetic model is established firstly according to a spacecraft, and then a model formula is processed; a sliding mode attitude controller (which is expressed in the specification) based on a backstepping method is designed; then an RBF neural network approach (eta+htau)sgn(sigma) is adopted; the controller (which is expressed in the specification) is designed; and finally a complete attitude controller (which is expressed in the specification) is obtained. A three-axis attitude controller is designed respectively according to the aforementioned process. The flexible satellite neural network backstepping sliding mode attitude control method is suitable for the field of flexible spacecraft attitude control.

The invention relates to a control method for a micro-grid hybrid energy storage system. The control method comprises the following steps: selecting inductive current i L (lower coordinate) and capacitor voltage u c (lower coordinate) as state variables, and energy storage unit voltage u i (lower coordinate) and load current i Load (lower coordinate) as input variables for a buck/ boost power converter in the micro-grid hybrid energy storage system; building a small signal model of buck/ boost power converter based on PWM (Pulse-Width Modulation) complementary control; respectively designing control circuits for a storage battery and a super capacitor; controlling the charging and discharging of the storage battery and stabilize low-frequency component of synthetic load through a single current loop; stabilizing the difference between the synthetic load power and storage battery power through the upper capacitor; adding power feed-forward to the voltage-current double closed-loop control so as to inhibit the fluctuation of the voltage of a DC bus. According to the control method for the micro-grid hybrid energy storage system, each load power in a micro-grid is taken into full account, a plurality of control methods are carried out to stabilize the high-frequency fluctuation of power, thus the fluctuation of the voltage of the DC voltage is inhibited, and the stability of the voltage of the DC bus in working is maintained.

The invention discloses a micro gyroscope adaptive control method based on model reference, and the method is applied to a controller comprising a gyroscope. The method comprises the following steps: establishing an ideal dynamics model; designing a reference model as two different frequency sine waves, wherein a state space form is X[m]=A[m]X[m]; establishing a micro gyroscope system dynamics model; controlling a micro gyroscope based on a Lyapunov method, wherein a design control law is u=K<T>X+K[f]e, K<T> is an on-line adaptive update controller parameter, and K[f] is a steady matrix, and selecting K[f] and allowing (A[m]+BK[f]) as a stabilization matrix. According to the invention, a model reference adaptive control method is applied to micro gyroscope control in order to compensate manufacture errors and environment interference, and estimate an angle rate correctly. By employing a designed self-adaptive algorithm based on the Lyapunov method, global progressive stability of a whole control system is ensured, and reliability and robustness to parameter change of the system are raised.

The invention uses the idea of hierarchical structure control optimization to provide a manipulator actuator fault tolerant control system based on a double-layer structure and a method thereof, which belongs to the technical field of automatic control. In order to reduce the computational complexity and improve the instantaneity, a discrete system model under an actuator fault is established in an expansion manner through Taylor series. An FDD unit is designed to initiatively deal with a fault problem. The estimated fault information is introduced into a fault model to realize active fault tolerance. Uncertainties of the actual system are considered. A feedback correction mechanism is used for compensation. A manipulator fault tolerant controller is composed of a trajectory planning layer and a tracking control layer. According to different control objectives of each layer, a controller is designed separately, which is more specific to the problem. The fault tolerant control of the double-layer structure can deal with the existing system constraints, has strong robustness, can effectively solve the problem of the constant deviation fault of a complex manipulator actuator, and ensures the stability and the control performance of the whole system.

The invention provides an optimization method of a relative orbit transfer path of a spacecraft based on time-fuel optimum control and relates to the optimization method of the relative orbit transfer path of the spacecraft. The optimization method of the relative orbit transfer path of the spacecraft is used for solving the problem that the finite thrust amplitude is not considered in the existing method and the problem that only time optimum or only the fuel consumption is considered in the existing method when a tracking spacecraft is in a relative orbit coordinate system. The optimization method comprises the following steps: firstly, establishing a kinematics and dynamics model as shown in the specification of the relative orbit, and designing control quantities ux, uy and uz applied along three axes respectively; secondly, decoupling the kinematics and dynamics model of the relative orbit into three subsystems; after decoupling into three subsystems, transforming the total performance index as shown in the specification considering transfer time and fuel consumption of the tracking spacecraft into monoaxial performance index as shown in the specification of each axis, and finally obtaining the time-fuel optimal control law as shown in the specification for controlling the tracking spacecraft. The optimization method is suitable for optimizing the relative orbit transfer path of the spacecraft.