[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]

Journal of Projectiles, Rockets, Missiles and Guidance >

2022 , Vol. 42 >Issue 3: 78 - 84

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2022.03.016

Influence of Module Gas Pressure Difference on Ejection of Multistage Piston Cylinder Ejection

  • WANG Jinghui ,
  • JIANG Yi ,
  • YANG Changzhi ,
  • NIU Yusen
Expand
  • School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China

Received date: 2021-12-14

  Online published: 2025-02-03

Fold

Abstract

The effect of module synchronization on the performance of ejection device and the dynamic response of rocket is studied for the problem of synchronization of ejection module due to gas pressure difference during multi-module and multistage piston cylinder cold ejection. The mathematical model is established to analyze the relationship between kinematic synchronization and power synchronization of multistage piston cylinder. A three-module eight-stage piston cylinder dynamic model is established. The motion synchronization, structural safety of the ejection device and dynamic response of the rocket are investigated considering the power out of sync caused by gas pressure difference. The result shows that since the mass of the rocket is about 20 times that of the power module actually, which meets the quality condition of motion synchronization, and the motion of the rocket and the ejection module always keeps synchronization. The effective displacement and ejection time of each module is different due to the accumulation of compression deformation of the buffer device. The larger the difference of power synchronization between the three modules, the more disadvantageous the safety of the multistage piston cylinder and the attitude of rocket. It is found that the maximum stress of multistage piston cylinder increases, the time of rocket deorbit increases and the pitch velocity and yaw velocity increase.

Key words： ejection technology; multistage piston cylinder; module synchronization; gas pressure difference; launch dynamics

Cite this article

WANG Jinghui , JIANG Yi , YANG Changzhi , NIU Yusen . Influence of Module Gas Pressure Difference on Ejection of Multistage Piston Cylinder Ejection[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2022 , 42(3) : 78 -84 . DOI: 10.15892/j.cnki.djzdxb.2022.03.016

[an error occurred while processing this directive]

References

Publishing order | Descend order by publishing year | Descend order by cited within
[1]
李广裕. 战略导弹弹射技术的发展[J]. 国外导弹与航天运载器, 1990, 3(7):38-49.

[2]
张筱, 刘宝龙, 郑夏, 等. 导弹井下冷弹射动力学仿真研究[J]. 导弹与航天运载技术, 2018(4):85-90.

[3]
赵克转, 张高峰. 导弹冷弹射过程建模及动力学仿真研究[J]. 弹箭与制导学报, 2012, 32(4):45-48.

[4]
胡晓磊, 乐贵高, 马大为, 等. 水下燃气-蒸汽弹射气-液两相流场数值研究[J]. 航空动力学报, 2015, 30(1):164-172.

[5]
WANG B Q, WANG C, HUANG H L, et al. Analysis of underwater projectile experiment using one stage light gas gun and numerical[J]. Applied Mechanics and Materials, 2012, 226: 776-779.

[6]
谢磊, 高钦和, 邵亚军. 压缩空气弹射内弹道影响因素作用规律研究[J]. 火力与指挥控制, 2019, 44(3):116-119.

[7]
颜凤, 史少岩, 姜毅. 燃气蒸汽式弹射内弹道研究[J]. 舰船科学技术, 2017, 39(3): 118-122.

[8]
江坤, 王浩, 郭锦炎, 等. 拉杆活塞式发射装置内弹道建模与仿真[J]. 弹道学报, 2011, 23(1):13-17.

[9]
李伟波, 马贵军, 曹延杰, 等. 导弹电磁弹射器电磁兼容性研究[J]. 海军航空工程学院学报, 2015, 30(4):383-386.

[10]
白鹏英, 乔军. 双级气缸式弹射装置内弹道分析[J]. 现代防御技术, 2007, 35(4): 44-49.

[11]
柳忠彬, 肖守讷, 王欢. 非爆破柔性气缸弹射器研究[J]. 兵工学报, 2017, 38(2):389-395.

DOI

[12]
孟艳, 王玺, 郭锦炎, 等. 多级活塞缸式发射装置结构安全性分析[J]. 弹道学报, 2020, 32(2):56-61.

DOI

[13]
魏冬冬, 姜毅, 赵良玉, 等. 液体火箭冷弹射系统推进剂晃动研究[J]. 弹箭与制导学报, 2021, 41(3):34-38.

[14]
高钦和, 黄先祥. 多级缸起竖系统运动过程的建模与仿真[J]. 系统仿真学报, 2005, 17(7):1563-1565.

[15]
唐垚, 姜毅, 王成德, 等. 多级活塞缸式燃气弹射内弹道的研究[J]. 固体火箭技术, 2018, 41(4):126-133.

Options
Outlines

/

〈 〉

[an error occurred while processing this directive]