航空发动机全飞行包线稳态划分方法研究  

Study on steady state division method of aircraft engine full flight envelope

作　　者：蒋匀绅 蔡开龙 JIANG Yunshen;CAI Kailong(College of Aircraft Engineering,Nanchang Hangkong University,Nanchang 330063,China)

机构地区：[1]南昌航空大学飞行器工程学院,南昌330063

出　　处：《航空工程进展》2023年第3期77-83,共7页Advances in Aeronautical Science and Engineering

基　　金：江西省双千计划(jxsq2018106057)。

摘　　要：航空发动机在鲁棒控制器设计过程中存在飞行包线区域难以系统划分的问题,为此,提出基于推力耗油率特性和基于动压耗油率特性的航空发动机飞行包线划分法。根据某型涡扇发动机在全包线范围内稳态工作时的推力、耗油率及动压特性,结合大气条件的客观规律,通过两种划分方法将飞行包线划分为65个区域,用每个区域对应标称点的参数代替其周围小偏差区域和边界点参数。通过对该发动机全飞行包线内各区域标称点与边界点参数的对比,证明两种方法均对全飞行包线划分有效,可为后续航空发动机控制器设计提供理论参考。In the process of robust controller design for aircraft engines,it is difficult to divide the flight envelope re-gion systematically.In this paper,the flight envelope division methods for aircraft engines based on thrust fuel con-sumption rate characteristics and dynamic pressure fuel consumption rate characteristics is proposed.According to the thrust,fuel consumption and dynamic pressure characteristics of a turbofan engine during steady-state operation within the full envelope,combined with the objective law of atmospheric conditions,the flight envelope is divided into 65 regions by two division methods,and the parameters of the surrounding small deviation regions and bound-ary points are replaced by the parameters of the corresponding nominal points of each region.By comparing the pa-rameters of nominal points and boundary points within the full envelope of the engine,the results show that both methods are effective for the full flight envelope division,which provides a theoretical basis for the subsequent air-craft engine controller design.

关 键 词：航空发动机 飞行包线划分 推力耗油率特性 动压 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程] V249.4