文档介绍：南京航空航天大学
硕士学位论文
带矢量喷管发动机建模与短距起飞控制研究
姓名:蒋达福
申请学位级别:硕士
专业:动力机械及工程
指导教师:孙健国;张海波
20081201
南京航空航天大学硕士学位论文
中文摘要
本文首先阐述了航空发动机风扇、压气机进口可调导叶的建模思想和过程,完善了矢量喷
管数学模型,解决了以往模型慢车状态下不收敛的问题,剔除了理想发动机模型,直接计算各
参数理想值来求得各性能参数,然后与其他部件级模型组成带矢量喷管的涡扇发动机模型,最
后通过仿真数据,分析了各变量变化趋势是否合理,通过与三维流场计算值比较,对模型进行
验证,在模型里对差异较大的尾喷管性能参数,进行了修正。
在上述带矢量喷管发动机数学模型的基础上,构成了带矢量喷管的飞机/发动机综合仿真模
型,对飞机简要模型及其子控制系统进行了必要的阐述,在带推力矢量的综合飞行/推进控制系
统基础上,采用一种增广 LQR(ALQR)方法,设计了 ALQR 控制器,实现了飞机起飞阶段推力矢量
控制与气动舵面控制的融合,通过与 PID 常规单独气动舵面控制数值仿真效果的比较,较大程
度地缩短了起飞距离,验证了此控制器的有效性与优越性。另外为了比较在相同控制变量下,
不同控制器的效果,设计了 PID 双变量控制器,最后对这两种控制器优劣作了评价并提出相关
建议。
关键词:可调导叶,喷管,推力矢量,短距起飞,综合飞行/推进控制,PID,ALQR
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南京航空航天大学硕士学位论文
ABSTRACT
In this thesis, the modeling process of the adjustable guide vanes for aero-engine fan -
pressor is firstly expounded. Secondly, after solving non-convergent problems of the existing model at
the throttling state and obtaining the performance parameters through puting the ideal
value of the parameters without the ideal aero-engine model, the mathematical model of the
thrust-vectoring nozzle is pleted. Thirdly, bining it with po-
nent level model, a turbofan engine model with thrust-vectoring nozzle is obtained. Finally, the ex-
periments on the simulation examples show that the varying tendency of several parameters is in ac-
cordance with the theoretical tendency, and pared with putational results of the
three-dimensional flow field, this turbofan engine model with thrust-vectoring nozzle is validated.
Besides, the performance parameters of the nozzle are corrected due to their large differences.
Based on the mathematical model of engine with thrust-vectoring nozzle, the integrated model of
aircraft/engine is constructed. Then the aircraft model including a control system is depicted briefly.
First of all, on basis of the Integrated Flight/Propulsion Control (IFPC) system, an augmented LQR
(ALQR) controller, bines the thrust vector control with aerodynamic elev