[an error occurred while processing this directive] [an error occurred while processing this directive] [an error occurred while processing this directive]
[an error occurred while processing this directive]

A Method for Predicting Interior Ballistic Performance Based on LSTM Network

  • FENG Weiye ,
  • CHEN Linquan ,
  • WU Qiu ,
  • CHEN Linjun
Expand
  • Institute of Xi’an Aerospace Solid Propulsion Technology,Xi’an 710025,Shaanxi,China

Received date: 2023-12-01

  Online published: 2024-12-28

Abstract

Zero-dimensional internal ballistic analysis is a commonly used internal ballistic performance analysis method with simple calculation and high efficiency, and has a good performance in the study of internal ballistic performance. However, it often adopts the method of treating throat diameter change as linear ablation to simplify the throat area. A large number of analyses and tests show that throat diameter ablation is not linear, and throat liner ablation mainly occurs in the middle and late stages of engine operation. Therefore, a prediction method of internal trajectory performance based on genetic algorithm and LSTM neural network is proposed in this paper. Firstly, genetic algorithm and zero-dimensional internal trajectory calculation equation are used to identify the throat diameter change curve from the pressure data obtained from the test. Then LSTM neural network is used to establish a throat diameter change prediction model to predict the throat diameter change curve of the engine. On this basis, the ballistic performance in the working section is predicted. The method is verified by a real case.The mean square error between the predicted curve and the actual curve is 0.118 MPa, and the relative error is 1.35%. The predicted results verify that the method can accurately predict the pressure change curve of solid rocket motor.

Cite this article

FENG Weiye , CHEN Linquan , WU Qiu , CHEN Linjun . A Method for Predicting Interior Ballistic Performance Based on LSTM Network[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2024 , 44(1) : 57 -62 . DOI: 10.15892/j.cnki.djzdxb.2024.01.009

[an error occurred while processing this directive]
[1]
蒲晓航, 李冬, 李富贵, 等. 固体火箭发动机内弹道精准预示自修正方法[J]. 固体火箭技术, 2021, 44(6): 767-772.

PU X H, LI D, LI F G, et al. Self-correction method of internalballistic for solid rocket motor[J]. Journal of Solid Rocket Technology, 2021, 44(6): 767-772.

[2]
来平安, 项建杏. 固体火箭发动机内弹道性能工程预示方法[J]. 固体火箭技术, 2003(3): 11-13.

LAI P A, XIANG J X. Engineering prediction method of internal ballistic performance of solid rocket Motor[J]. Journal of Solid Rocket Technology, 2003(3): 11-13.

[3]
张鸿涛, 王文平, 冯晓柏. 固体火箭发动机性能分析及预示[J]. 固体火箭技术, 1993(2): 1-6.

ZHANG H T, WANG W P, FENG X B. Performance analysis and prediction of solid rocket motors[J]. Journal of Solid Rocket Technology, 1993(2): 1-6.

[4]
王磊, 代义, 李宏. 基于Pro/E软件进行固体火箭发动机内弹道计算的方法初探[J]. 中国新技术新产品, 2009(10): 8-9.

WANG L, DAI Y, LI H. Preliminary study on the method of internal ballistic calculation of solid rocket motor based on Pro/E software[J]. China New Technology and New Products, 2009(10): 8-9.

[5]
田忠亮, 李军伟, 黄刚, 等. 横向过载下固体火箭发动机内弹道特性研究[J]. 固体火箭技术, 2022, 45(4): 512-521.

TIAN Z L, LI J W, HUANG G, et al. Study on internal ballistic characteristics of solid rocket motor under transverse overload[J]. Solid Rocket Technology, 2022, 45(4): 512-521.

[6]
刘赟, 王浩, 陶如意, 等. 点火过程对小型固体火箭发动机内弹道影响[J]. 含能材料, 2013, 21(1): 75-79.

LIU Y, WANG H, TAO R Y, et al. Effect of ignition process on ballistics in small solid rocket engine[J]. Energetic Materials, 2013, 21(1): 75-79.

[7]
张凌, 王德友, 李世鹏, 等. 固体火箭发动机内弹道多参数辨识及精准预示方法[J]. 固体火箭技术 2023, 46(4): 514-520.

ZHANG L, WANG D Y, LI S P, et al. Multi-parameter identification and prediction method of internalballistic for solid rocket motor[J]. Journal of Solid Rocket Technology, 2023, 46(4): 514-520.

[8]
何景轩, 余贞勇, 孙利清, 等. 固体火箭发动机内弹道性能仿真[J]. 固体火箭技术, 2004, 27(1): 20-21.

HE J X, YU Z Y, SUN L Q, et al. Simulation of internal ballistic performance of solid rocket Motor[J]. Journal of Solid Rocket Technology, 2004, 27(1): 20-21.

[9]
王磊, 代义, 李宏. 一种固体火箭发动机针对喷管喉径变化的辨识方法[J]. 中国新技术新产品, 2008(8): 4-5.

WANG L, DAI Y, LI H. A identification method for nozzle throat diameter variation of solid rocket motor[J]. China New Technology and New Products, 2008(8): 4-5.

[10]
方丁酉, 张为华. 固体火箭发动机喉径变化辨识[J]. 推进技术, 1997, 18(2): 27-30.

FANG D Y, ZHANG W H. Identification of throat diameter variation of solid rocket Motor[J]. Journal of Propulsion Technology, 1997, 18(2): 27-30.

[11]
刘伟. 基于Pro/E和Qt平台的固体火箭发动机内弹道性能计算[D]. 哈尔滨: 哈尔滨工程大学, 2014.

LIU W. Calculation of ballistic performance of solid rocket motor based on Pro/E and Qt platform[D]. Harbin:Harbin Engineering University, 2014.

[12]
樊超, 张为华. 基于遗传算法的固体火箭发动机参数辨识[J]. 固体火箭技术, 2008, 31(4): 321-324.

FAN C, ZHANG W H. Parameter identification of solid rocket motor based on genetic algorithm[J]. Journal of Solid Rocket Technology, 2008, 31(4): 321-324.

[13]
杨喜军, 程慧, 张涛. 大长径比固体发动机侵蚀燃烧影响研究[J]. 战术导弹技术, 2018(2): 102-106.

YANG X J, CHENG H, ZHANG T. Research on erosive burning property of solid rocket motor with large lenth-to-diameter ratio[J]. Tactical Missile Technology, 2018(2): 102-106.

[14]
刘中兵, 汪亮, 胡春波. 以静态燃速预示固体发动机燃速[J]. 固体火箭技术, 2008, 31(2): 149-153.

LIU Z B, WANG L, HU C B. Using static burning rate to predict burning rate of solid motor[J]. Journal of Solid Rocket Technology, 2008, 31(2): 149-153.

[15]
刘中兵, 汪亮, 胡春波. 固体发动机燃速相关性[J]. 推进技术, 2008, 29(6): 716-720.

LIU Z B, WANG L, HU C B. Solid engine burning rate correlation[J]. Journal of Propulsion Technology, 2008, 29(6): 716-720.

[16]
张小平, 代志龙. 基于遗传神经网络的高能固体推进剂高压燃烧性能计算[J]. 固体火箭技术, 2007, 30(3): 229-232.

ZHANG X P, DAI Z L. Calculation of high pressure combustion performance of high energy solid propellant based on genetic neural network[J]. Journal of Solid Rocket Technology, 2007, 30(3): 229-232.

[17]
刘佩进, 吕翔, 何国强. 基于人工神经网络的燃速相关性研究[J]. 推进技术, 2004, 25(2): 156-158.

LIU P J, LYU X, HE G Q. Burning rate relativity investigation using artificial neural network[J]. Journal of Propulsion Technology, 2004, 25(2): 156-158.

Outlines

/

[an error occurred while processing this directive]