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基于增益调度的航空发动机分散鲁棒控制

潘慕绚 曹良进 黄金泉

潘慕绚, 曹良进, 黄金泉等 . 基于增益调度的航空发动机分散鲁棒控制[J]. 北京航空航天大学学报, 2018, 44(9): 1964-1973. doi: 10.13700/j.bh.1001-5965.2017.0659
引用本文: 潘慕绚, 曹良进, 黄金泉等 . 基于增益调度的航空发动机分散鲁棒控制[J]. 北京航空航天大学学报, 2018, 44(9): 1964-1973. doi: 10.13700/j.bh.1001-5965.2017.0659
PAN Muxuan, CAO Liangjin, HUANG Jinquanet al. Gain scheduling based decentralized robust control for aircraft engines[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44(9): 1964-1973. doi: 10.13700/j.bh.1001-5965.2017.0659(in Chinese)
Citation: PAN Muxuan, CAO Liangjin, HUANG Jinquanet al. Gain scheduling based decentralized robust control for aircraft engines[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44(9): 1964-1973. doi: 10.13700/j.bh.1001-5965.2017.0659(in Chinese)

基于增益调度的航空发动机分散鲁棒控制

doi: 10.13700/j.bh.1001-5965.2017.0659
基金项目: 

国家自然科学基金 51406084

江苏省航空动力系统重点实验室基金 NJ20160020

详细信息
    作者简介:

    潘慕绚  女, 博士, 副教授, 硕士生导师。主要研究方向:航空发动机控制系统设计及仿真

    曹良进  男, 硕士研究生。主要研究方向:航空发动机控制系统设计及仿真

    通讯作者:

    潘慕绚.E-mail:muxuan.pan@nuaa.edu.cn

  • 中图分类号: V233.7

Gain scheduling based decentralized robust control for aircraft engines

Funds: 

National Natural Science Foundation of China 51406084

Foudation of Jiangsu Province Key Laboratory of Aerospace Power System NJ20160020

More Information
  • 摘要:

    针对航空发动机全包线大范围非线性变化动态特性下的跟踪控制问题,设计分散鲁棒跟踪控制器。引入动态响应指数收敛参数,使得控制器在保证系统稳定的同时跟踪误差收敛速率可调。在飞行包线内选择一系列设计点,以油门杆角度(PLA)表征发动机功率水平,每隔5°选取一个PLA作为一个设计功率水平,针对从一个设计功率水平过渡到另一个设计功率水平的设计阶跃过程,采用递进法设计分散鲁棒跟踪控制器。采用线性插值的方法调度非设计阶跃过程分散鲁棒跟踪控制器参数。针对某型涡扇发动机部件级模型进行仿真,仿真结果验证了控制方法的有效性。

     

  • 图 1  航空发动机全包线增益调度控制系统

    Figure 1.  Aircraft engine full envelope gain scheduling control system

    图 2  H=0, Ma=0处, 当PLA从65°拉到60°时, 在控制器式(39)作用下系统仿真结果

    Figure 2.  Simulation results under controller Eq.(39) at H=0 and Ma=0 when PLA being pulled from 65° to 60°

    图 3  H=0, Ma=0处, 当PLA从65°拉到60°时, 在控制器式(40)作用下系统仿真结果

    Figure 3.  Simulation results under controller Eq.(40) at H =0and Ma=0 when PLA being pulled from 65° to 60°

    图 4  存在测量噪声时控制器式(39)与控制器式(40)作用下系统仿真结果对比

    Figure 4.  Comparison of simulation results between controller Eq.(39) and controller Eq.(40) when measurement noise exists

    图 5  飞行包线设计点位置分布图

    Figure 5.  Design point position distribution in flight envelope

    图 6  仿真过程中PLA随时间变化关系

    Figure 6.  Variation of PLA with time in simulation process

    图 7  发动机在不同工作点处大范围阶跃跟踪控制仿真结果

    Figure 7.  Simulation results in wide-range step tracking control at different operating points of engine

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出版历程
  • 收稿日期:  2017-10-24
  • 录用日期:  2018-01-19
  • 刊出日期:  2018-09-20

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