一种直升机涡轴发动机加速自适应控制研究

AN ACCELERATION ADAPTIVE CONTROL FOR TURBOSHAFT ENGINE OF HELICOPTER

提出一种直升机涡轴发动机加速自适应控制方案，它是在ＮＧＧ／ｐ＊２ＰＩＤ控制的基础上加自适应控制律。当发动机性能老化或损伤时，加速时可能引起压气机喘振，这种自适应加速控制方案能适应对象这种性能变化，自动调整方案以消除加速过程出现的喘振现象。这种加速控制比传统的ｗｆ／ｐ＊２开环加速控制具有较高的控制精度，也具有类似高度补偿和喘振恢复项ｐ＊２。这种自适应加速控制只需对原有ＦＡＤＥＣ控制的硬件稍作修改，主要依靠微机控制软件修改就可以将ＦＡＤＥＣ控制提高到自适应控制水平。

A scheme of an acceleration adaptive fuel control is put forward for helicopter turboshaft engine.The scheme is based on GG/P*2 closed loop control with adaptive control rule,which corrects the demand of og/P*2 closed loop control PID with surge flag detected by sensed compressor discharge pressure during the engine acceleration,since the engine performance deterioration or damage will initiate the surge in this time.This scheme also provides altitude compensation and surge recovery P*2.It requires only modifying a litte the hardware of an existing FADEC,but mainly the fuel control microcomputer software,so it is easy to upgrade an existing FADEC to the adaptive control level.