| 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)
|
Aiming at the coupling problem between the inlet and the engine, the integrated control of inlet/engine based on auxiliary door at low speed and high angle of attack is studied. Firstly, a real-time inlet model is established, which is related to the flight conditions, angle of attack, auxiliary door and the total pressure recovery coefficient and flow rate at the outlet. Then, the inlet mass flow is matched with the engine mass flow, and the control simulation platform of the integrated inlet/engine real-time model is established. Secondly, in order to solve the problem of insufficient inlet flow and uneven pressure in the process of large maneuver, an integrated control method of inlet/engine with auxiliary door regulation is proposed. That is, the control of total pressure recovery coefficient at the outlet of inlet is realized by adjusting the auxiliary door. Under the condition of ensuring the stability of inlet, the control method is based on robust control. Under the condition of stable performance of inlet exit, the control of engine speed and pressure ratio is realized based on
| [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).
|
Figures(9) / Tables(2)
Copyright © Journal of Beijing University of Aeronautics and Astronautics
Address: Editorial Department of Journal of Beijing University of Aeronautics and Astronautics, 37 Xueyuan Road, Haidian District, Beijing Post Code: 100191 Email: jbuaa@buaa.edu.cn
Supported by:
Beijing Renhe Information Technology Co., Ltd.
DownLoad:
