基于变尺度寻优混合求解算法的航空发动机状态变量模型建立方法  

A Mixture Solution Method Based on Variable Scale Method for Aeroengines State Variables Model

作　　者：杨征山[1,2] 仇小杰[1] 王铁[3] 黄金泉[2] 

机构地区：[1]中航工业航空动力控制系统研究所,江苏无锡214063 [2]南京航空航天大学能源与动力学院,南京210016 [3]总参陆航部驻上海地区军事代表室,上海200233

出　　处：《航空发动机》2014年第2期70-75,共6页Aeroengine

基　　金：航空科学基金(20120652013)资助

摘　　要：为了克服小扰动方法精度不高、稳态终值响应法动态过程不一致以及传统拟合法的随着维数增加精度下降和拟合时间长等缺点,综合了3种算法(小扰动法、稳态终值响应法和传统拟合法)的优点,设计了基于变尺度法的混合求解方法建立了航空发动机状态变量线性模型。仿真结果表明:建立的航空发动机状态变量线性模型与非线性部件级模型在动态过程响应中吻合良好,而且具有较高的稳态精度,能够保证航空发动机最终稳定值的一致性。In order to avoids the disadvantages such as less accuracy of small perturbation method,inconsistent of dynamic process of steady-state value of response,and less accuracy and longer time of traditional fitting method with the increase of the matrix dimensions,the advantages of small perturbation method,steady-state value of response method and traditional fitting method were integrated,a mixture solution method based on variable scale method is proposed to establish state variables linear model for aeroengines.The simulation shows the aeroengines state variables linear model is in good agreement in the dynamic response,and steady accuracy with the nonlinear component level model.

关 键 词：航空发动机 状态变量模型 变尺度寻优 混合求解法 

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]