1302 results about "Output feedback" patented technology

An input control method and an electronic device supporting the same are provided. The method includes activating a plurality of input signal collection units supporting a multi-modal input, collecting at least one input signal from the input signal collection units, and outputting feedback information corresponding to the at least one input signal.

A switching power supply device for a ripple control system that can obtain the ripple component with the necessary amplitude without using discrete elements. On capacitor Ci of CR integrator 11, a voltage is generated corresponding to the integration value of the voltage applied to inductor Lo. The ripple voltage generated on capacitor Ci has a waveform similar to that of the ripple current flowing through inductor Lo. The voltage of capacitor Ci is converted into current Iq by voltage / current converter 12, and the current is injected in resistor R3 arranged on the transmission path of output feedback voltage VFB in comparator 2. Resistor R3 generates ripple voltage (Iqxr3) corresponding to the ripple current flowing through inductor Lo. The synthetic voltage of the ripple voltage and output feedback voltage VFB is compared to reference voltage Vref.

A power system having a phase locked loop (PLL) with a notch filter for synchronous reference frame sequence separation. The notch filter includes a generalized integrator tuned to the notch frequency. The output of the generalized integrator is summed with the filter input signal and the output of the summer is fed back to the integrator input. In one embodiment, the notch filter is programmable by a control signal generated in response to the filter output signal, thereby causing the filter to self-regulate to a frequency related to the PLL input signal. Illustrative power systems include active VAR generators and active rectifiers. One or more additional notch filters may be used to remove harmonic components from derived synchronous reference frame sequence components.

A semiconductor storage device according to one embodiment of the present invention, comprising: FBCs (Floating Body Cells) which store data by accumulating a majority carrier in a floating channel body; and sense amplifiers which perform control reading out data stored in said FBC, wherein each of said sense amplifier includes: a pair of sense nodes provided corresponding to a bit line pair to which said FBC is connected; a pair of load which flow currents through said pair of sense nodes; latch circuits which latch potentials of said pair of sense nodes when a potential difference between said pair of sense nodes reaches a predetermined value; and an output control circuit which outputs latched outputs of said latch circuits at a predetermined timing and feeds back the latched outputs to said bit line pair side to again write it into said FBC.

The invention provides a method realizing automatic client service using human-computer interaction technique, and an equipment realizing the method. The method includes: receiving problem imported with nature language from the user, converting the nature language into information identified by the computer using human-computer interaction technique; outputting feedback information according withthe information identified for the computer. In addition, the invention also provides the equipment realizing the method.

The deciphering of fragmented enciphered IP packets is perfomed without requiring reassembly of the fragments fragmented packets. When a first frame is deciphered a characteristic poly-tuple is saved against the state of the cipher, particularly an output vector. When the next frame comes in, the cipher would continue on from that previously saved state after a look-up of the poly-tuple. Each frame would then be sent on, deciphered, but still representing a fragment of the original packet. The poly-tuple employed for the look-up includes the identity and protocol fields from the IP header and at least one of the source IP address and the destination IP address. The deciphering process may commence with the combination of input data with an initialising vector and proceed by combining input data with a vector fed back from the output of the deciphering engine. The saved cipher state is employed as the initialising vector for the next frame.

The invention discloses a nonlinear output feedback flight control method for a quad-rotor unmanned aerial vehicle. The nonlinear output feedback flight control method for the quad-rotor unmanned aerial vehicle comprises the following steps of: (1) determining a kinematic model of the quad-rotor unmanned aerial vehicle under an inertial coordinate system and a kinematic model of the quad-rotor unmanned aerial vehicle under a body coordinate system; (2) designing an attitude control system of the quad-rotor unmanned aerial vehicle; defining tracking errors of the attitude angle and the angular speed of the quad-rotor unmanned aerial vehicle; designing a filter to perform online estimation on an angular speed signal and obtain an open loop dynamic equation of the tracking errors; and estimating unknown functions in the open loop dynamic equation by adopting neural network feedforward, and designing attitude system control output of the quad-rotor unmanned aerial vehicle; and (3) designing a height control subsystem of the quad-rotor unmanned aerial vehicle; defining height tracking errors and defining auxiliary filtering tracking errors; and designing a height subsystem controller. According to the nonlinear output feedback flight control method for the quad-rotor unmanned aerial vehicle disclosed by the invention, the polarity problem is effectively avoided, a wide-range stable control effect is achieved, the robust performance of the system is greatly improved, and the dependence of a flight controller on an airborne sensor is greatly reduced.

The invention relates to a regenerative braking control method of an electric car and a device thereof, which are characterized in that a throttle signal, a braking signal, the current speed of the car and the SOC (state of charge) value of a battery are acquired during the running process of the car, when the current speed of the car is larger than the preset minimum feedback speed of the car, and the throttle opening is smaller than the preset feedback threshold value or the braking signal, the feedback moment is calculated according to the current speed and the braking depth; when the SOC value of the battery is smaller than the preset upper limit, the feedback moment is output to charge the battery pack; and when the SOC value of the battery reaches the preset upper limit, an electricmachine controller controls an electric machine not to generate braking feedback charge current, and braking is carried out according to the traditional braking method. The method and the device can increase the utilization rate of battery energy, the car can be kept smooth during the travelling, the regenerative braking can be also realized, and in addition, the SOC value of the battery can be real-timely monitored, too, so the battery is prevented from being damaged when the battery is over charged downhill.

A method and system for keeping endpoints such as speakers and displays synchronized via feedback based on the actual output of the endpoints. A source of audiovisual content transmits corresponding digital data to one or more endpoints, such as over a home network, where it may be buffered and / or decoded for playback. Microphones or the like sense actual (post-buffering / decoding) output from one or more endpoints and feed it back to a synchronization mechanism. The synchronization mechanism employs pattern matching or similar techniques to determine whether and how to adjust the timing of endpoints to synchronize their actual outputs. Synchronization may be accomplished by controllably delaying transmission and / or other processing, by controllably changing the rate of advancing in a buffer, and / or by jumping ahead in a buffer. The synchronization mechanism may adjust multiple endpoints, e.g., when limited buffer size limits the amount of adjustment a single device can provide.

A composite anti-jamming attitude control method for a flexible spacecraft, which is characterized in that it includes the following steps: First, by considering the vibration of the flexible attachment, the change of the spacecraft moment of inertia caused by the expansion of the flexible attachment and the space environment disturbance torque on the attitude In order to control the influence of control, a flexible spacecraft dynamics model including neutral uncertain dynamic items and external equivalent disturbance variables is established; secondly, in view of the serious influence of structural vibration on the stability of the spacecraft, and the large existence of flexible accessories such as sailboards, With the characteristics of flexibility and low damping, the PPF active vibration controller is constructed to reduce the impact of vibration modes on the spacecraft body; thirdly, the H∞ anti-jamming controller is designed to suppress vibrations from flexible mechanisms such as sailboards and extension rods. The disturbance caused by the change of the spacecraft rotational inertia caused by the deployment and the bounded disturbance such as the space environment disturbance moment; finally, based on the convex optimization algorithm, the composite anti-jamming output feedback attitude and the vibration composite controller are solved; Design and other advantages, can be used for high stability control of flexible spacecraft.

Provided are a touch screen and a method of operating the same. The touch screen includes a detecting part, a control part, and a tactile feedback part. The detecting part detects object's approach or contact. The control part receives a signal of the detecting part to output a feedback signal. The tactile feedback part receives the feedback signal of the control part to provide a tactile feedback to a contact position using a magnetic force. The tactile feedback uses the magnetic force of a magnetic dipole.

One embodiment is a system adapted to encrypt one or more packets of plaintext data in cipher-block chaining (CBC) mode. The system includes a plurality of digital logic components connected in series, where respective components are operative to process one or more rounds of a block cipher algorithm. A plurality of N bit registers are respectively coupled to the plurality of digital logic components. An XOR component receives blocks of plaintext data and blocks of ciphertext data, and XORs blocks of plaintext data for respective plaintext packets with previously encrypted blocks of ciphertext data for those plaintext packets. The XOR component iteratively feeds the XOR'd blocks of data into a first of the plurality of the digital logic components. In addition, a circuit component is operative to selectively pass blocks of ciphertext data fed back from an output of a final logic component to the XOR component.

The present invention relates to a circuit layout of a switch type regulator and control method thereof. The switch type regulator according to one embodiment of the invention includes: (1) a filter network connected to the output terminal, wherein the output voltage of the output terminal is generated by an input source; (2) an active switch connecting the input source to a wave filter circuit, wherein the active switch is periodically connected and disconnected, and the conducting duty cycle of the switch period is modulated by a PWM control signal; (3) a comparator, which receives output feedback signals, a delay signal and a reference delay, and provides the PWM control signal; (4) a delay programming circuit for generating the delay signal and a ramp control signal, wherein the delay signal is set up based on the status of the input source and the output voltage, to obtain an operating status with fundamentally constant frequency.

Simulation test equipment for validating the reliability of satellite attitude control and a test method thereof belong to the field of satellite attitude control. The test equipment comprises a ground simulation support module, a fault injection module and a satellite-born module, wherein, the ground simulation support module includes a monitoring terminal, a satellite model, a signal exciting source and a moment reverse-solution unit; the fault injection module includes an analog-to-digital converter, a signal transfer circuit, a fault injection processor, a man-machine interface unit and a digital-to-analog converter; and the satellite-born module includes a sensor, a satellite-born controller and an actuator. The test method comprises the following steps of: fault model setting; satellite initialization; orbit and attitude information renewal; the satellite-born controller collects signals of the sensor and outputs actuator command signals to the fault injection module; the actuator receives actuator pseudo command signals and outputs feedback signals to the fault injection module; the moment reverse-solution unit collects the pseudo feedback signals output by the fault injection module and outputs moment control signals to the satellite model. The equipment and the method of the invention have high feasibility and high performance-price ratio.

A power amplifier, supplied by a supply voltage, to drive an antenna to output a magnetic field, comprising a differential stage configured to output an output signal to drive the antenna, and a feedback stage configured to receive a common mode output voltage from the differential stage and to output a feedback voltage to regulate the output common mode signal to be proportional to the supply

A load driving device disclosed in the specification includes a power supply circuit for supplying to a load an output voltage converted from an input voltage, a detection voltage generation circuit for generating a detection voltage which varies depending on a magnitude of a voltage drop which across the load, and a control circuit for controlling the power supply circuit so that it performs output feedback control of the output voltage, on the basis of the detection voltage.

Embodiments of the invention include an integrated circuit including a phase-locked loop (PLL). The integrated circuit includes a phase detector, a frequency detector, a loop filter, a digitally-controlled oscillator and a corresponding plurality of frequency dividers. The phase detector generates a first binary output based on a phase comparison of a reference clock signal to a plurality of clock phase inputs. The frequency detector generates a second binary output based on a frequency comparison of the reference clock signal to the clock phase inputs. The loop filter generates a third binary output based on the first binary output and the second binary output. The DCO feeds back the clock phase inputs, via the frequency dividers, to the phase detector based on the third binary output, and feeds back one of the clock phases to the frequency detector based on the third binary output.

The invention provides an endoscopic minimally invasive surgery simulation training method which comprises the following steps of: (1) constructing and editing an endoscopic minimally invasive surgery medical model; (2) constructing a system foundation component library by using a fundamental algorithm; (3) constructing a core algorithm by using the system foundation component library to realize the core function of a 3D platform system; (4) constructing a medical model description language; (5) calling the medical model, constructing a medical scene, and simulating various actions of an endoscopic minimally invasive surgery; and (6) simulating various operations by using endoscopic minimally invasive surgery instruments in a driving virtual environment of an operating table, and outputting a feedback force through an operating rod of a data receiving and feedback signal processing driving operating platform to realize force feedback and virtual touch, so that the simulation training is more vivid. Meanwhile, the invention provides an endoscopic minimally invasive surgery simulation training system. By using the method and the system, force feedback and virtual touch effects can be provided, and high fidelity and a good simulation training effect can be achieved.

In an ADPLL composed of a digital circuit, a technique improving phase difference detection in a vicinity of a phase difference of 0 (zero) is provided. A feedback loop comprises a PFD comparing phases and frequencies of a reference signal and a feedback signal, a TDC converting an output of the PFD into a digital value, a DLF removing a high frequency noise component from an output of the TDC, a DCO controlled based on an output of the DLF and a DIV frequency-dividing an output the DCO and outputting the feedback signal. An offset value is added at any portion of the feedback loop, a phase of the feedback signal is controlled and a value other than 0 is inputted to the TDC even when the ADPLL is locked.

Methods and systems are used for monitoring a global position or location of a prosthetic or orthotic device and to provide feedback control of the device. Certain methods may employ remote transmitting devices and receivers to recognize when a prosthetic or orthotic device user is in a moving vehicle and, therefore, initiate automatic shut-off, driving mode, or relaxed mode. Other methods may employ remote transmitting devices and receivers to identify the global position of the prosthetic or orthotic device, compare the global position to a stored terrain mapped database and output feedback control instructions and / or alerts to the prosthetic or orthotic device based at least in part on the stored terrain mapping information.

The present invention is a method and apparatus for reading education. In one embodiment, a method for recognizing an utterance spoken by a reader, includes receiving text to be read by the reader, generating a grammar for speech recognition, in accordance with the text, receiving the utterance, interpreting the utterance in accordance with the grammar, and outputting feedback indicative of reader performance.

The present invention relates to an AC / DC converter (1) of the type having an AC / DC conversion stage (2) and a DC / DC conversion stage (3), the AC / DC conversion stage (2) comprising an input filter stage (4), an input rectifier stage (5) and a tracking boost converter stage. The boost converter stage in turn comprises an input choke (10), a boost diode (16) and a bulk capacitor (17). The bulk capacitor (17) is arranged to store a range of voltages substantially proportional to the input voltage of the converter. The DC / DC stage (3) is arranged to receive the range of voltages from the bulk capacitor (17) and is controllable to provide a desired DC output regardless of the voltage received from the bulk capacitor (17). This is achieved through careful combination of components and use of output feedback control to control the voltage applied to an isolated transformer (41) in the DC / DC stage.

The invention discloses a quad-rotor UAV fault tolerance control method based on an adaptive fault estimation observer, and belongs to the field of aviation aircraft control. The method comprises thata fault model of a quad-rotor attitude system is established according to a dynamic model of a quad-rotor UAV by considering a performer fault of a UAV system; a performer of the UAV includes four rotor motors in practicality, faults correspond to the four rotor motors, the fault model is processed, the faults are divided into two groups decoupled mutually, and a final attitude fault model is obtained; according to the provided fault model, the adaptive fault estimation observer is designed, corresponding adaptive laws are provided, the performance fault is estimated, and an H(infinite) method and an interval matrix method are used on external disturbance and parameter nondeterminacy respectively in the design process; and an attitude system error fault model is obtained on the basis of the fault model, a dynamic output feedback fault tolerance controller is designed on the basis of a fault estimated value, and fault tolerance control of the quad-rotor UAV is realized. Influence of the performer fault on performance of the quad-rotor UAV can overcome, and the safety and reliability of the UAV in the flight process are ensured fully.

The invention discloses a semi-supervised image instance segmentation method based on stepwise adversarial learning. The semi-supervised image instance segmentation method comprises the steps of 1, constructing Mask R-CNN instance segmentation model; 2, Training FPN in a Mask R-CNN Based on DCGAN; 3, adopting labeled data to perform preliminary training on other modules in the Mask R-CNN; 4, constructing a discriminant convolutional network, and forming an adversarial learning network with the Mask R-CNN, and optimizing parameters of the adversarial learning network through adversarial training; 5, feeding back the output of the discriminative convolutional network to Mask R-CNN for retraining the instance segmentation model; And 6, segmenting the to-be-segmented image by using the instance segmentation model. According to the method, the sample set only partially labeled with the image is used for model training, the workload of sample processing is reduced, and a segmentation model with high precision can be obtained.

The invention discloses a mechanical arm trajectory tracking control method based on a high-order sliding-mode observer. The method comprises the following steps of 1, establishing a dynamical model of an n-degree-of-freedom rotary joint rigid mechanical arm system; 2, acquiring measurement information of joint angles q of a mechanical arm by utilizing a photoelectric encoder, and calculating a mechanical arm trajectory tracking error e = q - qd according to a set expected joint angle qd; 3, establishing a global integral fast terminal sliding mode surface according to e; 4, determining control torque tau of joint driving motors of the mechanical arm according to the sliding mode surface and establishing a control gain self-adaptive rate capable of being dynamically adjusted; and 5, establishing the output feedback high-order sliding mode observer according to the control torque tau and the joint angles q of the mechanical arm, and estimating current angular velocity of joints and lumped disturbance. According to the method, under the situation that nonlinear uncertain items such as system parameter perturbation, external torque interference and damping friction exist in the mechanical arm system, the trajectory tracking control of the mechanical arm is realized only based on the measurement information of all the joint angles, and robustness of whole control process is ensured.

A system and method for the iterative detection and demodulation of M-ary orthogonal signals (MOK) and signals modulated using Complementary Code Keying (CCK) is described. An important feature of these methods is the good performance of noncoherent detectors in AWGN channels. However, the performance of these detectors in fast fading channels degrades considerably compared to that of coherent detectors. Iterative detection algorithms that significantly improve the performance of the demodulators with minimal additional complexity are presented The methods use soft decoder output feedback and iterative demodulation and decoding to achieve performance close to that of coherent detection. For MOK, significant performance enhancement is possible even without any loss of throughput due to insertion of pilot symbols. For CCK pilot symbols are necessary but the throughput loss remains low.

The invention belongs to the field of spacecraft control and relates to a fuzzy singular perturbation modeling and robust attitude control method for complex flexible spacecraft, namely a robust combined control method for fusing static output feedback control and output integration. The method comprises the following steps of: establishing an uncertain continuous fuzzy singular perturbation model and a standard discrete fuzzy singular perturbation model according to a dynamic model and a kinematic model of the spacecraft in combination with fuzzy logic and singular perturbation technology; and designing a robust controller combined by a static output feedback controller and an output integrator by a spectral norm and linear matrix inequality (LMI) method and resolving a group of LMIs which are unrelated to a perturbation parameter so as to obtain a controller parameter and solve an ill-conditioned problem caused by the perturbation parameter and the problem of difficulty in selection of an initial value in an LMI resolving static output feedback controller gain method. Through the method, flexible vibration and external interference can be overcome effectively, and control effects such as high response speed, high attitude control accuracy, high anti-jamming capability and high robust performance are achieved.

The invention relates to a method for controlling an index time-varying slide mode of flexible spacecraft characteristic shaft attitude maneuver, and belongs to the technical field of spacecraft control. The method comprises the steps that firstly, a system dynamically equivalent model, a dynamic model and a flexible vibration model are established under a spacecraft system, then, the vibration frequency and the damping ratio parameter of a closed loop system with the index time-varying slide mode control law are calculated, and a single-shaft multi-modality filtering input shaping device with a characteristic shaft as a rotary shaft is designed according to the designing method of the single-shaft input shaping device to restrain flexible vibration in three-shaft motion. Meanwhile, a state observer is designed to estimate flexible modal information in real time, and the method for controlling an output feedback index time-varying slide mode is formed. At last, saturability analysis is conducted on control torque so as to satisfy the physical saturation constraint of the control torque. By means of the method, the application range of existing input shaping is expanded, the input shaping technology is expanded from single-shaft maneuver to three-shaft maneuver, the self-robustness of filter input shaping is enhanced, and the purpose that the attitude maneuver path of the spacecraft is the shortest is achieved.