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基于辅助进气门的进气道/发动机一体化控制

叶东鑫 张海波 陈浩颖

叶东鑫, 张海波, 陈浩颖等 . 基于辅助进气门的进气道/发动机一体化控制[J]. 北京航空航天大学学报, 2020, 46(3): 608-615. doi: 10.13700/j.bh.1001-5965.2019.0259
引用本文: 叶东鑫, 张海波, 陈浩颖等 . 基于辅助进气门的进气道/发动机一体化控制[J]. 北京航空航天大学学报, 2020, 46(3): 608-615. doi: 10.13700/j.bh.1001-5965.2019.0259
YE Dongxin, ZHANG Haibo, CHEN Haoyinget al. Inlet/engine integrated control based on auxiliary door[J]. Journal of Beijing University of Aeronautics and Astronautics, 2020, 46(3): 608-615. doi: 10.13700/j.bh.1001-5965.2019.0259(in Chinese)
Citation: YE Dongxin, ZHANG Haibo, CHEN Haoyinget al. Inlet/engine integrated control based on auxiliary door[J]. Journal of Beijing University of Aeronautics and Astronautics, 2020, 46(3): 608-615. doi: 10.13700/j.bh.1001-5965.2019.0259(in Chinese)

基于辅助进气门的进气道/发动机一体化控制

doi: 10.13700/j.bh.1001-5965.2019.0259
基金项目: 

国家自然科学基金 51576096

江苏省研究生科研与实践创新计划 KYCX18_0323

中央高校基本科研业务费重大人才培育项目 NF2018003

详细信息
    作者简介:

    叶东鑫 男, 硕士研究生。主要研究方向:航空发动机建模与控制

    张海波 男, 博士, 教授, 博士生导师。主要研究方向:航空发动机建模与控制

    通讯作者:

    张海波.E-mail: zh_zhhb@126.com

  • 中图分类号: V221+.3;TB553

Inlet/engine integrated control based on auxiliary door

Funds: 

National Natural Science Foundation of China 51576096

Postgraduate Research & Practice Innovation Program of Jiangsu Province KYCX18_0323

Major Talents Cultivation Project of Fundamental Research Funds for the Central Universities NF2018003

More Information
  • 摘要:

    针对进气道与发动机的耦合问题,研究了低速大迎角状态下,基于辅助进气门的进气道/发动机一体化控制。首先,建立了飞行条件、迎角、辅助进气门开度与出口总压恢复系数和流量相关联的进气道实时模型,进而将进气道出口流量和发动机进口流量相匹配,建立了进气道/发动机一体化模型的控制仿真平台。其次,为了解决大机动过程中发动机进口流量不足和压力不均的问题,提出了一种带有辅助进气门调节的进气道/发动机一体化控制方法,即通过调节辅助进气门开度实现进气道出口总压恢复系数控制,在保证进气道出口性能稳定的情况下,基于H鲁棒控制方法实现对发动机转速和压比的控制。研究结果表明,在整个大机动过程中,所提出的进气道/发动机一体化控制可以使得发动机各项性能保持稳定,在典型任务工况下,推力提高了16%,耗油率下降了6%。

     

  • 图 1  辅助进气门的影响

    Figure 1.  Effect of auxiliary door

    图 2  辅助进气门典型结构

    Figure 2.  Typical structure of auxiliary door

    图 3  进气道模型

    Figure 3.  Inlet model

    图 4  含辅助进气门的进气道模型

    Figure 4.  Inlet model with auxiliary door

    图 5  网格划分

    Figure 5.  Mesh generation

    图 6  标准H控制原理

    Figure 6.  Standard H control principle

    图 7  发动机部件截面

    Figure 7.  Engine component section

    图 8  发动机部件

    Figure 8.  Components of engine

    图 9  大机动状态下进气道/发动机一体化控制仿真结果

    Figure 9.  Simulation results of integrated inlet/engine control in large maneuvering state

    表  1  不同状态下的总压恢复系数

    Table  1.   Total pressure recovery coefficients in different states

    辅助进气门开度/(°) 总压恢复系数
    α=0° α=15° α=30° α=45° α=60°
    0 0.937 7 0.932 8 0.926 6 0.919 9 0.915 5
    10 0.945 0 0.939 3 0.932 6 0.924 7 0.919 5
    20 0.950 0 0.943 9 0.936 2 0.928 7 0.923 1
    30 0.953 2 0.947 3 0.939 9 0.933 7 0.928 5
    下载: 导出CSV

    表  2  不同状态下的出口流量

    Table  2.   Exit flow rates in different states

    辅助进气门开度/(°) 出口流量
    α=0° α=15° α=30° α=45° α=60°
    0 1 0.973 2 0.932 2 0.877 7 0.830 3
    10 1.079 1 1.059 9 1.024 4 0.983 2 0.929 6
    20 1.116 6 1.102 1.073 1.030 1 0.986 2
    30 1.138 3 1.128 8 1.107 0 1.071 6 1.034 7
    下载: 导出CSV
  • [1] CONNOLLY J W, KOPASAKIS G, PAXSON D E, et al.Nonlinear dynamic modeling and controls development for supersonic propulsion system research: AIAA-2011-5635[R].Reston: AIAA, 2011.
    [2] 杜瑶, 张海波, 刘明磊.基于正激波位置计算的进气道/发动机系统实时仿真模型[J].航空动力学报, 2018, 33(1):247-256. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkdlxb201801030

    DU Y, ZHANG H B, LIU M L.Real-time simulation modeling for integrated inlet and engine system based on forward shock position calculation[J].Journal of Aerospace Power, 2018, 33(1):247-256(in Chinese). http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkdlxb201801030
    [3] 李中华.Su-27飞机眼镜蛇机动及其战术意义[J].飞行力学, 2000, 18(1):54-57. doi: 10.3969/j.issn.1002-0853.2000.01.015

    LI Z H.Su-27 cobra maneuver and its tactical application[J].Flight Dynamics, 2000, 18(1):54-57(in Chinese). doi: 10.3969/j.issn.1002-0853.2000.01.015
    [4] 艾宇.飞行器大攻角流场数值模拟研究[D].南京: 南京理工大学, 2015.

    AI Y.Study on numerical simulation of aircraft at high angle of attack[D].Nanjing: Nangjing University of Science and Technology, 2015(in Chinese).
    [5] WALSH K, STEENKEN W, WILLIAMS J.Summary of inlet characteristics of the F/A-18A high alpha research vehicle[C]//34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Reston: AIAA, 1998: 3713.
    [6] MOSES P L, RAUSCH V L, NGUYEN L T, et al.NASA hypersonic flight demonstrators-overview, status, and future plans[J].Acta Astronautica, 2004, 55(3):619-630. http://d.old.wanfangdata.com.cn/NSTLQK/NSTL_QKJJ029806107/
    [7] SAMUEL B A, MUKHERJEE R.A study of the unsteady aerodynamics of a wing at high angles of attack using decambering to model separated flow[J].Sādhanā, 2018, 43(8):121. doi: 10.1007/s12046-018-0894-y
    [8] WASSERBAUER J F, CUBBISON R W, TREFNY C J.Low speed performance of a supersonic axisymmetric mixed compression inlet with auxiliary inlets: AIAA-1983-1414[R].Reston: AIAA, 1983.
    [9] TINDELL R H, HILL W G.CFD analysis of the X-29 inlet at high angle of attack[J].Journal of Aircraft, 2015, 30(4):480-487. doi: 10.2514/3.56892
    [10] MARK J L, MCGARRY M A, REAGAN P V.Research on a two-dimensional inlet for a supersonic V/STOL propulsion system: NASA CR-174945[R].Washington, D.C.: NASA, 1984.
    [11] 翁小侪, 郭荣伟.一种腹下S弯进气道低速大攻角下气动特性实验[J].航空动力学报, 2008, 23(9):1573-1578. http://d.old.wanfangdata.com.cn/Periodical/hkdlxb200809004

    WEN X C, GUO R W.Investigation of pneumatic characteristics for a ventral S-shaped inlet at high incidence and low speed[J].Journal of Aerospace Power, 2008, 23(9):1573-1578(in Chinese). http://d.old.wanfangdata.com.cn/Periodical/hkdlxb200809004
    [12] 孔德英, 邓文剑, 方力.一种背负式S弯进气道辅助进气门设计[J].航空科学技术, 2016, 27(12):1-7. doi: 10.3969/j.issn.1007-5453.2016.12.001

    KONG D Y, DENG W J, FANG L.Design of an auxiliary air intake for the dorsal S-shaped inlet[J].Aeronautical Science and Technology, 2016, 27(12):1-7(in Chinese). doi: 10.3969/j.issn.1007-5453.2016.12.001
    [13] 田金虎, 乔渭阳, 彭生红.飞机快速机动过程中进气道/发动机一体化计算分析[J].航空动力学报, 2013, 28(8):1818-1827. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkdlxb201308020

    TIAN J H, QIAO W Y, PENG S H.Calculation and analysis on air inlet/engine integrated in fast maneuvering flight[J].Journal of Aerospace Power, 2013, 28(8):1818-1827(in Chinese). http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkdlxb201308020
    [14] 巫朝君.战斗机进气道低速特性试验研究[D].长沙: 国防科技大学, 2007.

    WU C J.The test investigation of inlet properties for fighter at low speed[D]Changsha: National University of Defense Technology, 2007(in Chinese).
    [15] 姚照辉.考虑飞/推耦合特性的超燃冲压发动机控制方法研究[D].哈尔滨: 哈尔滨工业大学, 2010.

    YAO Z H.Control strategy design for scramjet engine with flight/propulsion coupling properties[D].Harbin: Harbin Institute of Technology, 2010(in Chinese).
    [16] 孙丰勇, 张海波, 叶志锋.超声速进气道/发动机一体化控制[J].航空动力学报, 2014, 29(10):2279-2287. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkdlxb201410002

    SUN F Y, ZHANG H B, YE Z F.Integrated control for supersonic inlet/engine[J].Journal of Aerospace Power, 2014, 29(10):2279-2282(in Chinese). http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkdlxb201410002
    [17] 卢燕, 樊思齐, 马会民.超声速进气道与发动机的匹配[J].推进技术, 2003, 24(4):323-325. doi: 10.3321/j.issn:1001-4055.2003.04.010

    LU Y, FAN S Q, MA H M.Matching between supersonic inlet and aero-engine[J].Journal of Propulsion Technology, 2003, 24(4):323-325(in Chinese). doi: 10.3321/j.issn:1001-4055.2003.04.010
    [18] 马志超, 唐海龙.某型飞机推进系统建模及超音速巡航优化分析[C]//中国航空学会推进系统气体热力学专业学术交流会, 2005.

    MA Z C, TANG H L.The building of model for the propulsion supersonic flight system and the analyse of supersonic flight[C]//Academic Symposium on Gas Thermodynamics of Propulsion System of China Aviation Society, 2005.
    [19] SUN F, DU Y, ZHANG H.A study on optimal control of the aero-propulsion system acceleration process under the supersonic state[J].Chinese Journal of Aeronautics, 2017, 30(2):698-705. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=hkxb-e201702021
    [20] HONG W, KIM C.Numerical study on supersonic inlet buzz under various throttling conditions and fluid-structure interaction[C]//29th AIAA Applied Aerodynamics Conference.Reston: AIAA, 2011: 27-30.
    [21] 周文祥.航空发动机及控制系统建模与面向对象的仿真研究[D].南京: 南京航空航天大学, 2006.

    ZHOU W X.Research on object_oriented modeling and simulation foe aeroengine and control system[D].Nanjing: Nanjing University of Aeronautics and Astronautics, 2006(in Chinese).
    [22] 王健康.航空发动机模型基优化控制技术研究[D].南京: 南京航空航天大学, 2013.

    WANG J K.Research on model-based optimal control for aero-engines[D].Nanjing: Nanjing University of Aeronautics and Astronautics, 2013(in Chinese).
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出版历程
  • 收稿日期:  2019-05-28
  • 录用日期:  2019-10-27
  • 网络出版日期:  2020-03-20

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