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结合最优化理论和线性系统理论,对控制问题中航空发动机飞行包线区域划分方法展开了研究。分析了发动机线性状态空间模型与进气道出口气流总温总压参数有关特性。在此基础上定义了飞行包线内任意两飞行点间的广义距离,提出将飞行包线区域划分与标称点设计问题转化为一个基于该广义距离的最大覆盖优化问题,即选择尽量少的标称点实现对飞行包线区域的覆盖。以涡扇发动机及其进气道为例,采用文中方法对其包线区域进行了划分计算,并对标称点与其覆盖区域内最远点处发动机线性化模型进行了比较。结果表明,该区域划分和标称点选择的优化方法的有效性。
Combining the optimization theory and the linear system theory, the method of dividing the aero-engine flight envelope in the control problem is studied. The relationship between the linear state space model of the engine and the total temperature and total pressure parameter of the airflow at the outlet of the air intake is analyzed. On this basis, the generalized distance between any two flight points in the flight envelope is defined. It is proposed to convert the flight envelope region and nominal point design problem into a maximum coverage optimization problem based on the generalized distance, that is, to select as few as possible The nominal point covers the flight envelope area. Taking the turbofan engine and its inlet as an example, the envelope area of the turbofan engine is calculated by the method of the article and the linearization model of the engine at the farthest point in the coverage area is compared with the nominal point. The results show the effectiveness of the method of optimization for the division of zones and nominal points.