摘要
针对小流量发动机,以发动机进气流量作为反馈输入来控制发动机进气调压系统。首先,对进气系统进行了高空台半物理仿真试验。其次,建立了阀门上调、下调与PID补偿模型,并使用上下调试验数据对各种模型参数进行高阶多项式优化。最后,把各个模型在各调整工况下结合起来,对进气调压进行全过程模拟。其动态误差在0.471%内波动,而稳态误差在0.096%范围内。
This research tackles with the small flow rate aeroengine air-inlet system using the feedback control of air-intake flow rate.Firstly,carry out the high altitude platform semi-physic simulated test on air-inlet system.Secondly,establish the air-inlet gate upward regulation,downward regulation and PID compensation models,then optimize the model parameters by higher order polynomial using simulated test data.Finally,all control models are combined under different work states to carry out the full process simulation.Its dynamic error is fluctuating within 0.471%,while its stable error is fluctuating within 0.096%.
出处
《武汉理工大学学报》
CAS
CSCD
北大核心
2011年第5期142-146,共5页
Journal of Wuhan University of Technology
基金
中国燃气涡轮研究院项目(JJHK-2010-01-09)
中国航空科学基金(2008ZD24012)
金川科技预研基金(H04010801W080421)
关键词
小流量发动机
半物理仿真
多项式优化
进气调压
small flow rate aeroengine
semi-physic simulation
polynomial optimization
air-inlet pressure
