航空发动机高空模拟进气压力前馈控制仿真技术研究

Research of Inlet Pressure Forward Feedback Simulation Investigation on Aero-engine Altitude Simulation Test

进气压力的模拟精度是航空发动机高空模拟试验必须考核的一项重要指标,在发动机进行过渡态试验时,发动机空气流量的剧烈变化是进气压力控制系统的强干扰源;在详细分析进气压力动态特性的基础上,结合进气压力数学模型以及干扰通道与控制通道的过程特性,设计了基于发动机空气流量及其变化率作为前馈输入扰动变量的前馈控制器,并构成前馈+反馈复合控制系统;半物理仿真结果表明,所设计的控制系统实现了快速性与稳定性的高效统一。

The high simulation precision of inlet pressure is one of essential and critical targets for aero-engine altitude simulation tests. During the transient test of aero engines, the quick change in air mass flow of tested engines has strong influence on simulation accuracy of the inlet pressure. Through multianalysis, a feed forward controller with air mass flow and its changing rate as input parameters has been designed and further a complex control system including feed forward and back functions has been developed on the basis of the inlet pressure dynamic characteristics, the mathematical model of the inlet pressure and the process characteristic of interference and control channel. The simulation results show that the designed control system is able to achieve the balance between response and stability very well.