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1297 results about "Output feedback" patented technology

In cryptography, output feedback (OFB) is a mode of operation for a block cipher. It has some similarities to the ciphertext feedback mode in that it permits encryption of differing block sizes, but has the key difference that the output of the encryption block function is the feedback (instead of the ciphertext ).

Nonlinear output feedback flight control method for quad-rotor unmanned aerial vehicle

ActiveCN103365296ASolving Polarity ProblemsSolve the problem that it is difficult to accurately measure the speedPosition/course control in three dimensionsDynamic equationInertial coordinate system
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.
Owner:TIANJIN UNIV

Regenerative braking control method of electric car and device thereof

ActiveCN102343824AReal-time monitoring of state of charge valueReal-time monitoring of state of charge SOCElectrodynamic brake systemsBraking systemsRegenerative brakeCharge current
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.
Owner:BEIQI FOTON MOTOR CO LTD

A composite attitude and vibration control method for an anti-jamming flexible spacecraft

InactiveCN102298390AEliminate vibrationInterference torque effect eliminationAttitude controlVibration controlSpacecraft attitude control
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.
Owner:BEIHANG UNIV

Simulation test equipment and method for moonlet attitude control reliability validation

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.
Owner:NANJING UNIV OF AERONAUTICS & ASTRONAUTICS

Endoscopic minimally invasive surgery simulation training method and system

ActiveCN102254476ARealize force feedbackRealize the virtual sense of touchEducational modelsSimulation trainingMedical model
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.
Owner:GUANGZHOU SAIBAO LIANRUI INFORMATION TECH

Quad-rotor unmanned aerial vehicle (UAV) fault tolerance control method based on adaptive fault estimation observer

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.
Owner:CENT SOUTH UNIV

Mechanical arm trajectory tracking control method based on high-order sliding-mode observer

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.
Owner:SOUTHEAST UNIV

Fuzzy singular perturbation modeling and attitude control method for complex flexible spacecraft

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.
Owner:UNIV OF SCI & TECH BEIJING

Method for controlling index time-varying slide mode of flexible spacecraft characteristic shaft attitude maneuver

ActiveCN103412491ASuppress residual vibrationAvoid complex coupling relationshipsAdaptive controlDynamic modelsSpace vehicle control
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.
Owner:BEIJING INSTITUTE OF TECHNOLOGYGY
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