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依据发动机非线性模型求取喷口的动态模型时,存在未建模动态对线性动态模型的建模误差,由此设计的喷口控制器较难达到设计要求,尤其在大范围飞行包线内喷口控制的动态性能将会变坏;同时由于传感器噪声问题、喷口执行机构的位置饱和限制、速率饱和限制的问题,以及PI控制中的积分饱和问题的存在,这些饱和限制等干扰将会影响PI控制器的设计性能。针对上述问题提出了一种带执行机构的喷口控制器的设计方法和抑制饱和限制干扰的喷口控制逻辑设计方法。首先获取了带执行机构的线性动态增广模型,然后针对该增广模型利用迭代线性不等式方法计算了喷口的鲁棒PI控制器,并对控制器输出进行抗饱和修正,从而提高了喷口控制器的鲁棒性。引入所述方法在发动机半物理仿真中进行了验证,在全飞行包线内获得了满意的喷口控制鲁棒性能。
When the dynamic model of the spout is obtained according to the nonlinear model of the engine, the modeling error of the unmodeled dynamic linear dynamic model exists. Therefore, the designed spout controller is hard to meet the design requirements, especially in the wide-area flight envelope The dynamic performance of the PI controller will be deteriorated. At the same time, due to the sensor noise, the position saturation of the nozzle actuator, the limit of the rate saturation and the problem of integral saturation in the PI control, the interference such as the saturation limit will affect the PI controller Design performance. In view of the above problems, a design method of nozzle controller with actuator and a method of design of nozzle control logic to suppress the interference of saturation limit are proposed. First of all, a linear dynamic augmentation model with actuator is obtained. Then the robust PI controller of nozzle is calculated by iterative linear inequality method for the augmented model, and the output of the controller is corrected for anti-saturation, which improves the performance of the nozzle controller Robustness. The proposed method was validated in the semi-physical simulation of the engine and satisfactory nozzle control robustness was achieved within the full flight envelope.