7 results about "Actuator torque" patented technology

A torque control system and method for a vehicle include a control system configured to calculate a driver demand torque based on a speed of the vehicle and a driver torque request, predict a net driver demand torque based on the calculated driver demand torque and an opposing net torque for a road that the vehicle is traversing, estimate a turbine speed based on measured turbine and wheel speeds and a lumped vehicle inertia state space model with an observer correction algorithm, calculate a target actuator torque based on the calculated driver demand torque and the estimated turbine speed, and control at least one of an engine and an electric motor of the propulsion system based on the calculated target actuator torque.

The present invention relates to a method for controlling the position of a moving element in a vehicle transmission device (1). The method comprises the following steps: (i) angularly moving a control plate (10), (ii) measuring the angular position of a torque output element of an actuator and comparing the measured value with a limiting threshold value (m), (iii) reducing the rotational speed of the actuator's electric motor, (iv) applying a limited current (Ilim) to the actuator's electric motor, (v) stopping the control of the electric motor when, cumulatively, the limited current value (Ilim) is substantially reached, the measured value of the angular position of the actuator's torque output element corresponds substantially to the desired position, and the angular speed of the torque output element is substantially zero. Figure for the abstract: Figure 8

A folding apparatus for folding ends of a wrapping material around a pulp bale, said folding apparatus including: at least two folding arms, each including a contact element at an end thereof; at least two electric actuators, each configured to co-act with a folding arm such as to displace its contact element for making contact with the wrapping material to fold said wrapping material around an edge of the pulp bale; and a control unit configured to: determine, for each electric actuator, at least one operating parameter including a position parameter correlated to a position of one or more contact element and / or a force parameter indicative of actuator torque or force and / or a speed parameter indicative of a speed of rotation or displacement of the electric actuator, and control said at least two electric actuators using said at least one operating parameter.

An aircraft control stick trim control system, comprising a trim controller, a manual trim switch, an autopilot controller, a flap control computer, a trim actuator, a control stick, the trim controller comprising a manual trim control module, an autopilot trim module, a flap trim module, a trim priority level judging module, the manual trim control module generating a manual trim signal according to the state of the manual trim switch and sending the signal to the trim priority level judging module, the autopilot trim module generating an autopilot trim signal according to the autopilot actuator torque sent by the autopilot controller and sending the signal to the trim priority level judging module, the flap trim module generating a flap trim signal according to the change rate of the flap angle sent by the flap control computer and sending the signal to the trim priority level judging module, the trim priority level judging module having a trim priority level judging logic built-in, and outputting a trim rate corresponding to a priority trim signal to the trim actuator according to the trim priority level judging logic.

The invention provides a static instability aircraft actuator moment saturation protection control method and device, and belongs to the technical field of aircraft flight control, and the method comprises the steps: recognizing the moment saturation of an actuator, and judging whether the moment saturation of the actuator occurs or not; when the torque of the actuator is saturated, the torque saturation protection operation of the actuator is executed, and the torque saturation protection operation of the actuator comprises the steps of attenuating a pilot control instruction and disconnecting an integrator control channel, so that the protection setting of the control law is realized. According to the static instability aircraft actuator torque saturation protection control method and device provided by the invention, aircraft divergence caused by static instability aircraft actuator torque saturation can be avoided, any hardware part of a flight control system does not need to be transformed, and an actuator torque saturation protection control law can be designed according to the method; the method is added to a flight control law of a flight control system, so that the transformation cost is saved, and the torque saturation protection of the statically unstable aircraft actuator is realized.

The application discloses a kind of redundant EPS off-hand detection m-HIL test methods for car, comprising: one, redundant EPS off-hand detection function detection: input end torsional actuator and output end linear actuator selection;Output end linear actuator displacement keeps, adjusts input end actuator input torque, detects off-hand detection signal, records "off-hand" state and changes "non-off-hand" state corresponding output end linear actuator load value and input end torsional actuator torque value;Set output end linear actuator load value, adjust input end torsional actuator torque value, make steering gear from middle position start to rotate to both ends limit position and return, detect whether off-hand detection signal output is correct;Set input end torsional actuator initial torque, adjust output end linear actuator load, and rotate steering gear, detect whether off-hand detection signal output is correct;Two. Redundant EPS off-hand detection function fault detection.