带执行机构的航空发动机喷口控制器设计方法

Controller Design Methodology for Aeroengine Nozzle with Actuator

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。

In order to build a nozzle dynamic model based on aeroengine non-linear model,it will induce an error between the nnmodeling dynamics and linear model dynamics resulting in the nozzle controller hard to meet its design requirement and even worse dynamics performance in nozzle control in large range flight envelope. The PI controller design performance can be affected by the sense noise, the position and velocity saturation of the actuators and the integrator wind-up of PI controller. This paper describes a design method for nozzle controller with actuators and a method of controlling logic design to surpass the saturation limitation disturbance to address all the problems above. To improve the robustness of nozzle controller, firstly, a linear dynamic augmented model with actuator should be built. Secondly, by using iterative linear inequality the robust nozzle PI controller can be obtained through augmented model calculation and saturation correction will be applied to control output. This has been verified in hardware in loop of acroengine and achieved high performance of nozzle robust control in overall flight envelop.