超燃冲压发动机模型修正与不起动保护控制-“航空发动机智能控制与健康管理”专栏

  • 曾柏瑜 ,
  • 王冠 ,
  • 李家鑫 ,
  • 杨峰 ,
  • 吴国强 ,
  • 刘凯
展开
  • 1. 大连理工大学
    2. 中山大学航空航天学院
    3. 哈尔滨工业大学 航天学院
    4. 大连理工大学航空航天学院

收稿日期: 2026-01-04

  修回日期: 2026-06-22

  网络出版日期: 2026-06-23

基金资助

国家自然科学基金;中国航空学会青年科学家基金(导航制导与控制领域);国防科技工业技术基础科研项目;数字敏捷飞行器设计全国重点实验室开放基金;辽宁省科学技术计划项目

Model Correction and Unstart Protection Control for Scramjet Engines

  • ZENG Bai-Yu ,
  • WANG Guan ,
  • LI Jia-Xin ,
  • YANG Feng ,
  • WU Guo-Qiang ,
  • LIU Kai
Expand

Received date: 2026-01-04

  Revised date: 2026-06-22

  Online published: 2026-06-23

摘要

针对超燃冲压发动机模型精度不足、预警滞后性强以及运行边界约束严苛等问题,提出一种融合模型修正与自适应保护的控制方法。首先,针对几何降阶模型的精度不足问题,构建离线-在线协同修正机制。离线修正通过前向映射法补偿名义模型系统性偏差,在线修正采用双重扩展卡尔曼滤波实时辨识关键参数以补偿其时变特性。其次,针对传统单一预警方式存在的滞后性问题,提出双通道结合预警方法。以模型通道持续风险估计、传感器通道实时物理验证,通过切换机制实现风险感知。进一步地,针对发动机不起动风险与性能优化的矛盾,设计保护控制策略。将不确定性量化信息融入模型预测控制决策,通过自适应调度机制实现性能与安全的平衡。最后,仿真结果表明所提方法在提升估计精度与预警提前量的同时,实现不起动安全约束下的性能优化,验证了“修正-预警-控制”架构的协同有效性。

本文引用格式

曾柏瑜 , 王冠 , 李家鑫 , 杨峰 , 吴国强 , 刘凯 . 超燃冲压发动机模型修正与不起动保护控制-“航空发动机智能控制与健康管理”专栏[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2026.33314

Abstract

To address insufficient model accuracy, delayed unstart warning, and stringent operating boundary constraints in scramjet engines, a control method integrating model correction and adaptive protection is proposed. First, an offline-online collaborative correction mechanism is constructed to address the insufficient accuracy of the geometrically reduced-order model. Offline correction compen-sates for the systematic bias of the nominal model using a forward-mapping method, while online correction employs a dual extend-ed Kalman filter to identify key parameters in real time and compensate for their time-varying characteristics. Second, to overcome the delay inherent in conventional single-channel warning methods, a combined dual-channel warning method is proposed. The model channel continuously estimates risk, while the sensor channel provides real-time physical verification; a switching mechanism is used to achieve risk perception. Furthermore, to resolve the conflict between engine unstart risk and performance optimization, a protection control strategy is designed. Uncertainty quantification information is incorporated into model predictive control decisions, and adaptive scheduling is used to balance performance and safety. Finally, simulation results show that the proposed method im-proves estimation accuracy and warning lead time while optimizing performance under unstart safety constraints, thereby validating the synergistic effectiveness of the correction-warning-control architecture.

参考文献

[1] XIONG Y, QIN J, CHENG K, et al. Quasi-one-dimensional model of hydrocarbon-fueled scramjet com-bustor coupled with regenerative cooling[J]. International Journal of Aerospace Engineering, 2022, 2022: 9931498.
[2] 袁化成, 梁德旺. 高超声速侧压式模型进气道不起动特性分析[J]. 南京航空航天大学学报, 2004, 36(6): 683-687. YUAN H C, LIANG D W. Analysis of unstart characteristics of hypersonic side-compression inlet[J]. Journal of Nanjing University of Aeronautics & Astro-nautics, 2004, 36(6): 683-687 (in Chinese).
[3] BIRZER C, DOOLAN C J. Quasi-one-dimensional model of hydrogen-fueled scramjet combus-tors[C]//Proceedings of the Australian Combustion Sym-posium. Brisbane: The University of Queensland, 2009: 1-4.
[4] NAM J, BAE G, KANG S H, et al. Reduced-order mod-eling of the dual-mode scramjet combustor with hydro-gen and kerosene combustion[J]. International Journal of Aeronautical and Space Sciences, 2024, 25(1): 147-162.
[5] ANDERSON J D. Hypersonic and high-temperature gas dynamics[M]. 2nd ed. Reston: AIAA, 2006: 358-412.
[6] 丁猛, 梁剑寒, 刘卫东, 等. 碳氢燃料超燃冲压发动机进气道与燃烧室匹配性能试验研究[J]. 航空学报, 2005, 26(1): 27-31. DING M, LIANG J H, LIU W D, et al. Experimental investigation on matching performance between inlet and combustor of hydrocarbon-fueled scramjet[J]. Acta Aeronautica et Astronautica Sinica, 2005, 26(1): 27-31 (in Chinese).
[7] DI STEFANO M A, HOSDER S, BAURLE R A. Effect of turbulence model uncertainty on scramjet strut injector flow field analysis[C]//23rd AIAA International Space Planes and Hypersonic Systems and Technologies Con-ference. Reston: AIAA, 2021: AIAA 2021-2353.
[8] 高嘉豪, 何淼生, 刘成诚, 等. 基于稀疏网格配置方法的超燃冲压发动机高维不确定性量化[J]. 推进技术, 2021, 42(6): 1201-1212. GAO J H, HE M S, LIU C C, et al. High dimensional uncertainty quantification in scramjet performance analysis using sparse grid colloca-tion methods[J]. Journal of Propulsion Technology, 2021, 42(6): 1201-1212 (in Chinese).
[9] HUANG W, DU Z B, YAN L, et al. Flame propagation and stabilization in dual-mode scramjet combustors: A survey[J]. Progress in Aerospace Sciences, 2018, 101: 13-30.
[10] 刘小勇, 王明福, 刘建文, 等. 超燃冲压发动机研究回顾与展望[J]. 航空学报, 2024, 45(5): 529878. LIU X Y, WANG M F, LIU J W, et al. Review and prospect of research on scramjet[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(5): 529878 (in Chinese).
[11] VAN DRIEST E R. Turbulent boundary layers in com-pressible fluids[J]. Journal of the Aeronautical Sciences, 1951, 18(3): 145-160.
[12] IM S, DO H, CAPPELLI M A. Unstart phenomena induced by flow choking in scramjet inlet-isolators[J]. Progress in Aerospace Sciences, 2018, 97: 1-21.
[13] WAGNER J L, YUCEIL K B, VALDIVIA A, et al. Ex-perimental investigation of unstart in an inlet/isolator model in Mach 5 flow[J]. AIAA Journal, 2009, 47(6): 1528-1542.
[14] DO H, IM S, GOYNE C P. The influence of boundary layers on supersonic inlet unstart[C]//46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston: AIAA, 2010: AIAA 2010-6917.
[15] GOEL A. Retrospective cost adaptive control of unstart in a model scramjet combustor[J]. AIAA Journal, 2017, 55(9): 3036-3051.
[16] WANG Q, STENGEL R F. Nonlinear robust control of a hypersonic aircraft[J]. Journal of Guidance, Control, and Dynamics, 2000, 23(4): 577-585.
[17] XU H J, IOANNOU P A, MIRMIRANI M D. Adaptive sliding mode control design for a hypersonic flight vehi-cle[J]. Journal of Guidance, Control, and Dynamics, 2004, 27(5): 829-838.
[18] KODERA M, SUNAMI T, NISHIDA K. Adaptive slid-ing mode control for scramjet engine with flexible struc-ture[J]. Journal of Guidance, Control, and Dynamics, 2007, 30(2): 502-510.
[19] REDDING J, CAVANAUGH E, BRAVO L, et al. High fidelity simulations of unstart phenomena in a scramjet inlet due to angle of attack[J]. Physics of Fluids, 2025, 37(6): 066112.
[20] CAO L, LI Y, XU M, et al. Switching control of thrust regulation and inlet unstart protection for scramjet en-gine[J]. Acta Astronautica, 2015, 114: 29-41.
[21] HUNT R L, GAMBA M. Shock train unsteadiness char-acteristics, oblique-to-normal transition, and three-dimensional leading shock structure[J]. AIAA Journal, 2018, 56(4): 1569-1587.
Options
文章导航

/