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
严长凯 1周骁 1张海波1
作者信息
- 1. 南京航空航天大学能源与动力学院,南京210016
- 折叠
摘要
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.
Abstract
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.
关键词
涡轴发动机/直升机/自旋训练/燃油流量/导叶角/鲁棒控制Key words
turbo-shaft engine/helicopter/autorotation training/fuel mass flow/guided vanes angle/robust control引用本文复制引用
出版年
2014
NETL
NSTL
维普
万方数据