Design of Coal Quality Disturbance Free System for Coordinated Control System Based on Gain Scheduling
The economic and stable operation was affected seriously by coal quality disturbance for power plants. Based on model analysis, influence of the disturbance can be considered as gain change of control system. Power capability coefficient of coal was constructed to inhibit it. Accuracy of the coefficient was verified by operating data. Then coal quality disturbance free system based on gain scheduling was designed for coordinated control system. Simulation showed that, the strategy improved control quality obviously, and inhibited the coal quality disturbance. Keywords—coordinate control system, coal quality disturbance, energy coefficient of coal quality, gain scheduling
Research of coordinated control system based on robust control
It is proposed robust control algorithm for inaccurateness of coordinated control system model. In order to improve performance of robust controller, the dynamic compensation is used for balancing the difference of dynamic between boiler side and turbine side. A loop-shaping H∞ controller is designed for a boiler-turbine unit nonlinear model with adding dynamic compensation. In order to implement the complex H∞ controller, a multivariable controller with PID form can be got by reducing robust controller. Simulation show that the effect of robust controller can be approached by multivariable PID controller, and the controller has better robustness and dynamic is improved after dynamic compensation.
APPLICATION OF THE FINITE ELEMENT METHOD TO ROTARY-WING AEROELASTICITY.
Recent research in rotary-wing aeroelasticity has indicated that all fundamental problems in this area are inherently nonlinear. The non-linearities in this problem are due to the inclusion of finite slopes, due to moderate deflections, in the structural, inertia and aerodynamic operators associated with this aeroelastic problem. In this paper the equations of motion, which are both time and space dependent, for the aeroelastic problem are first formulated in P.D.E. form. Next the equations are linearized about a suitable equilibrium position. The spatial dependence in these equations is discretized using a local Galerkin method of weighted residuals resulting in a finite element formulation of the aeroelastic problem. As an illustration the method is applied to the coupled flap-lag problem of a helicopter rotor blade in hover. Comparison of the solutions with previously published solutions establishes the convergence properties of the method. It is concluded that this formulation is a practical tool for solving rotary-wing aeroelastic stability or response problems.