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4797 results about "Dynamic models" patented technology

Method for islanding microgrid control and optimization based on rotating coordinate virtual impedance

The invention discloses a method for islanding microgrid control and optimization based on rotating coordinate virtual impedance. Aiming to a fact that the actual microgrids have complicated impedance characteristics, the method for islanding microgrid control and optimization based on the rotating coordinate virtual impedance includes utilizing the coordinate rotation orthogonal transformation to design the coordinate rotation virtual impedance, improving the impedance characteristics of the microgrid, compensating errors of power distribution and improving power decoupling performance; establishing a complete small-signal dynamic model of the microgrid, wherein the small-signal dynamic model comprises distributed energy sources, power converters, loads and power grids, and guiding the selection of an optimal value on the basis of the small-signal dynamic analytical method; and simultaneously, providing a theoretical basis for the optimization selection of islanding microgrid control parameters by using the small-signal dynamic analytical method, wherein the islanding microgrid control parameters comprise droop control coefficients of the power distribution, process identifier (PI) parameters of a voltage current feedback controller, feedforward control coefficients and the like. The microgrid after being subjected to optimization design in an islanded operational mode is capable of effectively achieving power decoupling and improving the accuracy of the power distribution, the stability of the system and the dynamic performances.
Owner:SHANDONG UNIV

Large high-rise building indoor fire urgent evacuation indication escape method and system

The invention discloses a large high-rise building indoor fire urgent evacuation indication escape method and system, and belongs to the field of high-rise building fire safety. The large high-rise building indoor fire urgent evacuation indication escape method comprises the following steps: step 1, a fire source is located; step 2, a dynamic module of fire spread is set up; step 3, according to the dynamic module of fire spread in combination with the structural information of a building, the spatial position of an ignition point and the spatial position of fire-fighting equipment in a large high-rise building are determined, predictions are made over fire spread paths, and evacuation escape routes are planned; step 4, according to the designed escape routes, site equipment is controlled in a selective mode for assisting people in evacuation. According to the large high-rise building indoor fire urgent evacuation indication escape method and system, the fire control escape routes are made based on specific fire behavior, so that evacuation time is shortened; the existing problems that when a fire breaks out, a fire control evacuation escape way is crowded , low in efficiency and disorderly and stampedes easily occur are solved fundamentally; the practical significance of improving the safe evacuation performance of the large high-rise building and reducing the property loss and casualties caused by the fire in the large high-rise building is quite high.
Owner:天津安博瑞尼科技股份有限公司

Spacecraft attitude integral sliding mode fault tolerance control method taking consideration of performer fault

ActiveCN105843240AEasy to satisfy control torque limited constraintsSatisfy the control torque limited constraintCosmonautic vehiclesCosmonautic partsActive faultDynamic models
The invention relates to a spacecraft attitude integral sliding mode fault tolerance control method taking consideration of a performer fault and provides a robustness attitude active fault tolerance control method based on an integral sliding mode surface for problems of the performer fault, external disturbance and control moment amplitude limits in a spacecraft attitude control process. The method comprises steps that firstly, a spacecraft attitude dynamics model taking consideration of the performer fault and containing external disturbance is established; secondly, on the condition that a performer is not in fault, a designed nominal controller can guarantee system stability, and input saturation amplitude limits can be easily satisfied through adjusting controller parameters; lastly, the fault information is introduced to design an integral sliding mode controller, robustness of external disturbance and the performer fault can be effectively improved, system stability is analyzed on the basis of an Lyapunov method. The method is advantaged in that stability of the attitude control system is guaranteed when a spacecraft operating on orbit generates the performer fault, and relatively strong fault tolerance capability and external disturbance robustness are realized.
Owner:BEIHANG UNIV
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