一种直升机自旋训练过程涡轴发动机控制规律设计与仿真

Design and simulation of a control scheme for turbo-shaft engine in helicopter autorotation training process

针对直升机自旋训练过程中涡轴发动机快速响应要求,提出了一种以燃油流量和导叶角为控制量的鲁棒控制规律抑制自由涡轮转速瞬态下垂.首先,通过改进UH-60直升机/T700发动机综合模型,使之能够模拟自旋进入及自旋恢复过程动态变化.其次,提出并设计一种基于燃油流量和导叶调节的涡轴发动机鲁棒控制规律,并通过典型的自旋训练过程仿真,验证了该控制规律相比仅以燃油流量为变量的控制规律,自由涡轮转速瞬态下垂量降低至3%以下,且燃油流量变化更加平缓,改善了执行机构的工作条件.

According to the special need of turbo-shaft engines for fast response in helicopter autorotaion training process,a robust control scheme for turbo-shaft engines,including both fuel mass flow and guided vanes angle control,was proposed and designed to reduce the turbine speed transient droop.Firstly,an improved comprehensive model of UH-60 helicopter/T700 engines,which can simulate autorotation decent and autorotation recovery,was presented.Secondly,robust control scheme for turbo-shaft engine based on fuel mass flow and guided vanes adjustment was preset in the simulation cases.The result shows clearly that the turbine speed transient droop,controlled by the proposed robust control scheme,is sharply reduced to 3% than traditional method only exploring fuel mass flow control,while the variation of fuel mass flow is much slower and the operation condition of the actuator is improved.