航空发动机高空模拟试验进气压力复合控制研究  

Research on Aircraft Engine Inlet Pressure Compound Control in Altitude Simulation Test

作　　者：赵涌[1] 侯敏杰[1] 黄振南[2] 张松[1] 彭炬[1] 

机构地区：[1]中国燃气涡轮研究院,四川江油621703 [2]电子科技大学,四川成都610054

出　　处：《燃气涡轮试验与研究》2010年第1期37-41,共5页Gas Turbine Experiment and Research

基　　金：航空基金(20081024001)

摘　　要：针对航空发动机高空模拟试验进气压力控制系统动态特性较差的问题,提出在进气压力常规PID反馈控制的基础上,增加按空气流量补偿的前馈控制,构成压力复合控制系统。试验结果证明,所设计的复合控制系统能实现快速度和高精度的统一。Aiming at the problem that the inlet pressure control system had an inferior dynamic performance in aero engine altitude simulation tests, a compound control system based on the combination of the classical PID control strategy and the feed forward control strategy of flow compensation was presented in this paper. The results from the hardware-in-the-loop simulation tests indicated a reasonable compatibility between the speed and the precision by compound control system.

关 键 词：核心机 高空模拟试验 复合控制 半物理仿真 

分 类 号：V233.7[航空宇航科学与技术—航空宇航推进理论与工程]