基于QPSO的非壅塞固体冲压发动机一体化优化

王昭; 田小涛; 汤祥; 黄萌; 张博; 陈俊屹

doi:10.13224/j.cnki.jasp.20220520

基于QPSO的非壅塞固体冲压发动机一体化优化

doi: 10.13224/j.cnki.jasp.20220520

王昭^{1, 2},
田小涛^{1, 2},
汤祥^{1, 2},
黄萌^{1, 2,*, ,},
张博^{1, 2},
陈俊屹^{1, 2}

1.
中国兵器工业集团有限公司西安现代控制技术研究所，西安 710065
2.
中国兵器工业集团有限公司现代控制技术重点实验室，西安 710065

详细信息

作者简介:
王昭（1992-），男，高级工程师，博士，主要从事人工智能在发动机中的应用研究

通讯作者:
黄萌（1985-），男，高级工程师，博士，主要从事冲压发动机方面的研究。E-mail：hotmoon2000@qq.com

中图分类号: V435.5
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- 被引次数: 0
出版历程
- 收稿日期: 2022-07-20
- 网络出版日期: 2023-06-20

Integrated optimization of unchoked solid ramjet based on QPSO

WANG Zhao^{1, 2},
TIAN Xiaotao^{1, 2},
TANG Xiang^{1, 2},
HUANG Meng^{1, 2,*
, ,},
ZHANG Bo^{1, 2},
CHEN Junyi^{1, 2}

1.
Xi’an Modern Control Technology Research Institute， China North Industries Group Corporation Limited，Xi’an 710065，China
2.
Key Laboratory for Modern Control Technology， China North Industries Group Corporation Limited，Xi’an 710065，China

摘要

摘要:
为了对非壅塞固体冲压发动机性能进行充分优化，建立了相应的内外弹道一体化优化设计数学模型。首先构造了新的非壅塞固体冲压发动机性能预示框架。而后在此基础上，采用量子粒子群优化方法（quantum particle swarm optimization, QPSO），以巡航段和无动力下降段的总射程为优化目标，在满足推力约束的前提下，对冲压发动机的喷管喉径、进气道入口和喉部面积以及飞行攻角进行一体化优化。仿真结果表明：采用QPSO方法优化后的弹道射程较仅优化飞行攻角的方案提升18.65%，证明了一体化优化的有效性，为非壅塞固体冲压发动机的设计提供了理论基础。
- 非壅塞固体冲压发动机 /
- 一体化优化 /
- 弹道射程 /
- 量子粒子群 /
- 推力约束
Abstract:
In order to fully optimize the performance of unchoked solid ramjet, the mathematical model of integrated optimization design of interior and exterior ballistics was established. Firstly, a new frame for performance prediction of unchoked solid ramjet was constructed. On this basis, quantum particle swarm optimization (QPSO) with the total range of cruise and unpowered descent stages taken as optimization targets was adopted to optimize the nozzle throat diameter, inlet area and inlet throat area, as well as the flight angle of attack of the ramjet under premise of satisfying the thrust constraint. The simulation results showed that the ballistic range optimized by QPSO method was 18.65% higher than that of the scheme merely optimizing the flight angle of attack, so the superiority of the integrated optimization was proved, providing a theoretical basis for the design of unchoked solid ramjet.
- unchoked solid ramjet /
- integrated optimization /
- ballistic range /
- quantum particle swarm /
- thrust constraint

HTML

图 1 非壅塞固体冲压发动机截面示意图

Figure 1. Section diagram of unchoked solid ramjet

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图 2 补燃室出口参数求取流程图

Figure 2. Flow chart for calculating outlet parameters of supplementary combustion chamber

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图 3 性能预示流程图

Figure 3. Flow chart of performance prediction

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图 4 一体化优化流程图

Figure 4. Flow chart of integrated optimization

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图 5 求解收敛过程

Figure 5. Solution convergence process

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图 6 方案1和2所对应的弹道曲线

Figure 6. The corresponding ballistic curve of scheme 1 and 2

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图 7 方案1和2所对应的推力随时间变化曲线

Figure 7. The corresponding variation of thrust with time of scheme 1 and 2

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图 8 方案1和2所对应的飞行马赫数随时间变化曲线

Figure 8. The corresponding variation of flight Mach number with time of scheme 1 and 2

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图 9 方案1和2所对应的弹道倾角随时间变化曲线

Figure 9. The corresponding variation of flight path angle with time of scheme 1 and 2

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图 10 方案3和4所对应的弹道曲线

Figure 10. The corresponding ballistic curve of scheme 3 and 4

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图 11 方案3和4所对应的推力随时间变化曲线

Figure 11. The corresponding variation of thrust with time of scheme 3 and 4

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图 12 方案3和4所对应的飞行马赫数随时间变化曲线

Figure 12. The corresponding variation of flight Mach number with time of scheme 3 and 4

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表 1 方案1和2优化结果对比

Table 1. Comparison of optimization results between scheme 1 and 2

参数	数值
参数	方案1	方案2
飞行攻角/（^o）	6	6
喷管喉径	1.56	1.50
进气道入口面积	0.88	1.17
进气道喉部面积	0.68	0.65
飞行时间	1.0	0.9085
射程	1.0	0.9519
终端高度	0.0834	0.0909
终端马赫数	2.88	3.21

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表 2 方案3和4优化结果对比

Table 2. Comparison of optimization results between scheme 3 and 4

参数	数值
参数	方案1	方案2
巡航段飞行攻角/（^o）	6.0	6.0
无动力下降段飞行攻角/（^o）	12.0	8.86
喷管喉径	1.33	1.50
进气道入口面积	1.33	1.17
进气道喉部面积	0.54	0.65
飞行时间	1.0	0.8810
射程	1.0	0.8428
终端马赫数	0.46	0.55
巡航段工作时间	0.2182	0.2543
巡航段结束射程	0.3763	0.3957
巡航段结束高度	0.0502	0.0378
巡航段结束马赫数	3.71	3.21

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参考文献(26)

[1]	方丁酉, 张为华, 杨涛. 固体火箭发动机内弹道学[M]. 长沙: 国防科技大学出版社, 1997.
[2]	胡建新, 张为华, 夏智勋, 等. 冲压推进技术[M]. 长沙: 国防科技大学出版社, 2013.
[3]	刘兴洲. 飞航导弹动力装置: 上[M]. 北京: 宇航出版社, 1992.
[4]	刘兴洲. 飞航导弹动力装置: 下[M]. 北京: 宇航出版社, 1992.
[5]	方丁酉,夏智勋,张炜,等. 非壅塞固体火箭冲压发动机自适应调节特性[J]. 弹道学报,2000,12(4): 31-34. FANG Dingyou,XIA Zhixun,ZHANG Wei,et al. The adaptive control characteristics of unchoked solid rocket ramjet engine[J]. Journal of Ballistics,2000,12(4): 31-34. (in Chinese)
[6]	施雨阳,万自明,徐敏. 冲压发动机导弹爬升轨迹∕发动机一体优化设计[J]. 计算机仿真,2013,30(10): 138-142. SHI Yuyang,WAN Ziming,XU Min. Integrate optimization design of climb trajectory and motor for ramjet powered missile[J]. Computer Simulation,2013,30(10): 138-142. (in Chinese)
[7]	YANG S,CUI T,HAO X. Trajectory optimization for ramjet-powered vehicle in ascent phase via the Gauss pseudo spectral method[J]. Aerospace Science and Technology,2017,67: 88-95. doi: 10.1016/j.ast.2017.04.001
[8]	杨志红,徐宝华,姚德清. 基于高斯伪谱法的吸气式高超声速飞行器爬升弹道优化研究[J]. 导航定位与授时,2018,5(3): 35-40. YANG Zhihong,XU Baohua,YAO Deqing. Research on climbing trajectory optimization of air-breathing hypersonic vehicle based on Gauss pseudo spectral method[J]. Navigation Positioning and Timing,2018,5(3): 35-40. (in Chinese)
[9]	明超,孙瑞胜,梁卓,等. 吸气式超声速导弹弹道优化设计与分析[J]. 固体火箭技术,2016,39(6): 833-838. MING Chao,SUN Ruisheng,LIANG Zhuo,et al. Trajectory optimization design and analysis for air-breathing supersonic missile[J]. Journal of Solid Rocket Technology,2016,39(6): 833-838. (in Chinese)
[10]	王治宇,李高春,韩永恒,等. 冲压发动机导弹爬升段和巡航段轨迹优化[J]. 航空动力学报,2021,36(5): 1103-1112. WANG Zhiyu,LI Gaochun,HAN Yongheng,et al. Ascent and cruise trajectory optimization for ramjet powered missile[J]. Journal of Aerospace Power,2021,36(5): 1103-1112. (in Chinese)
[11]	张帆,张会强. 超燃冲压动力高超声速飞行器巡航弹道分析[J]. 宇航学报,2017,38(8): 797-806. ZHANG Fan,ZHANG Huiqiang. Cruise trajectory analysis of scramjet-powered hypersonic vehicle[J]. Journal of Astronautics,2017,38(8): 797-806. (in Chinese)
[12]	张磊扬,孙振华,贺永杰. 固冲发动机导弹方案弹道设计与优化[J]. 弹箭与制导学报,2016,36(3): 90-93. ZHANG Leiyang,SUN Zhenhua,HE Yongjie. Solid ramjet powered missile project trajectory design and optimization[J]. Journal of Projectiles, Rockets, Missiles and Guidance,2016,36(3): 90-93. (in Chinese)
[13]	罗文彩,罗世彬,王振国. 基于多方法协作优化方法的非壅塞式固体火箭冲压发动机导弹一体化优化设计[J]. 国防科技大学学报,2003,25(2): 14-18. LUO Wencai,LUO Shibin,WANG Zhenguo. Multimethod collaborative optimization algorithm applied to integral optimal design of missile propelled by unchoked solid rocket ramjet[J]. Journal of National University of Defense Technology,2003,25(2): 14-18. (in Chinese)
[14]	吉秋平. 弹用固体燃料冲压发动机性能研究[D]. 南京: 南京理工大学, 2006. JI Qiuping. Research on performance of solid fuel ramjet for missile[D]. Nanjing: Nanjing University of Science and Technology, 2006. (in Chinese)
[15]	谢爱元,武晓松,于栋梁. 固体燃料冲压发动机性能预示[J]. 推进技术,2014,35(1): 8-14. XIE Aiyuan,WU Xiaosong,YU Dongliang. Prediction model of performance for solid fuel ramjet[J]. Journal of Propulsion Technology,2014,35(1): 8-14. (in Chinese)
[16]	蒋波. 固体燃料冲压增程弹内外弹道一体化计算研究[D]. 南京: 南京理工大学, 2009. JIANG Bo. Integrated calculation of internal and external ballistic of solid fuel ramjet for extended range projectile[D]. Nanjing: Nanjing University of Science and Technology, 2009. (in Chinese)
[17]	于栋梁. 固体燃料冲压增程弹弹道特性研究[D]. 南京: 南京理工大学, 2013. YU Dongliang. Study on ballistic characteristics of solid fuel ramjet for extended range projectile[D]. Nanjing: Nanjing University of Science and Technology, 2013. (in Chinese)
[18]	李琦. 增程固体燃料冲压发动机的性能分析[D]. 南京: 南京理工大学, 2007. LI Qi. Performance analysis of extended range solid fuel ramjet[D]. Nanjing: Nanjing University of Science and Technology, 2007. (in Chinese)
[19]	陈昭明, 邹劲松, 王伟, 等. 改进粒子群神经网络融合有限元分析的铸锻双控动态成型多目标优化[EB/OL]. [2021-04-29]. https://doi.org/10.13229/j.cnki.jdxbgxb20210108. CHEN Zhaoming, ZOU Jinsong, WANG Wei, et al. Multi-objective optimization of casting-forging dynamic forming based on improved particle swarm neural network and finite element analysis[EB/OL]. [2021-04-29]. https://doi.org/10.13229/j.cnki.jdxbgxb20210108. (in Chinese)
[20]	王永华,杨欣毅,李本威,等. 基于免疫粒子群算法的涡扇发动机性能仿真[J]. 机械工程学报,2013,49(12): 153-160. doi: 10.3901/JME.2013.12.153 WANG Yonghua,YANG Xinyi,LI Benwei,et al. Immune particle swarm optimization algorithm for turbo-fan engine performance simulation[J]. Journal of Mechanical Engineering,2013,49(12): 153-160. (in Chinese) doi: 10.3901/JME.2013.12.153
[21]	SUN Jun,FANG Wei,WU Xiaojun,et al. Quantum-behaved particle swarm optimization: analysis of individual particle behavior and parameter seletion[J]. Evolutionary Computation,2012,20(3): 349-393. doi: 10.1162/EVCO_a_00049
[22]	王新月. 气体动力学基础[M]. 西安: 西北工业大学出版社, 2006.
[23]	向敏. 固体燃料冲压增程炮弹工作过程仿真及性能分析研究[D]. 长沙: 国防科学技术大学, 2006. XIANG Min. Working process simulation and performance analysis for solid fuel ramjet projectile[D]. Changsha: National University of Defense Technology, 2006. (in Chinese)
[24]	尚腾,谷良贤,赵吉松,等. 冲压发动机导弹爬升轨迹与推力调节规律优化[J]. 飞行力学,2012,30(3): 280-283. SHANG Teng,GU Liangxian,ZHAO Jisong,et al. Integrated optimum design for ramjet missile climb trajectory and thrust regulation[J]. Flight Dynamics,2012,30(3): 280-283. (in Chinese)
[25]	王利锋,白瑞林. 求解约束优化问题的一种新方法: 基于量子粒子群优化算法[J]. 计算机工程与应用,2005,34: 124-126. WANG Lifeng,BAI Ruilin. A new method for solving constrained optimization problems based on particle swarm optimization with quantum behavior[J]. Computer Engineering and Applications,2005,34: 124-126. (in Chinese)
[26]	鲍福廷, 黄熙君, 张振鹏, 等. 固体火箭冲压组合发动机[M]. 北京: 中国宇航出版社, 2006.