火箭推进

为了满足采用单一发射系统对不同重量不同初速导弹的发射要求,设计了一套包含多根产气药柱、可自适应点火、可变推力的燃气驱动装置。首先,根据驱动重量和速度要求,初步设计产气药柱对其产气性能及其作用的可靠性进行实验,为后续优化结构设计及仿真模拟提供依据; 其次,采用数值仿真模拟的方法,研究不同作用药柱个数、作用时间及弹体质量,发射系统内部压强和弹体运动随时间的变化情况。仿真结果表明:驱动条件相同,弹体质量越重,其在发射筒出口处的速度越小、所用时间也越长; 同一弹体,作用药柱个数越多,弹体在发射筒出口处的速度越大、所用时间也越短; 为防止作用药柱个数过多导致发射筒内压强过大,采用时序控制装置对其进行时序控制,从不同作用药柱的时序组合中获取最优方案。仿真及实验结果表明,所设计的燃气发生器药柱燃烧性能好、可自适应点火、可为系统提供可变推力,其设计基本合理。

For meeting the launch requirements of a single launch system for missiles with different initial velocities and different weights, a set of gas generator with multiple gas-producing grains, adaptive ignition and variable thrust was deigned.Firstly, according to the missile weight and its velocity requirements, the gas-producing grain was designed preliminarily.Its gas production performance and reliability were tested, providing the basis for the subsequent optimization of structural design and simulation.Then, a numerical simulation method was used to explore the changes of the missile weight, the grain number, the acting time, the internal pressure of launch system and the projectile movement with time.The simulation results show that if the driving conditions are same, the heavier the projectile is, the smaller the velocity is at the exit of the launch tube and the longer the time is.For the same projectile, the more the number of acting grains is, the faster the projectile is at the exit of the launch tube and the shorter the time it takes.In order to prevent the excessive pressure in the launch tube caused by the number of acting grains, the time sequence control device is used to control the time sequence, and the optimal scheme is obtained from the time sequence combination of different acting grains.Simulation and experimental results show that the designed gas generator grain has good combustion performance, adaptive ignition and variable thrust, and its design is basically reasonable.

引言
1 变推力驱动装置设计
2 弹射系统仿真结果与分析
3 结语

图1 燃气发生器装置设计原理图<br/>Fig.1 Design schematic of the gas generator

图1 燃气发生器装置设计原理图
Fig.1 Design schematic of the gas generator

图2 弹射系统仿真模型<br/>Fig.2 Simulation model of the launch system

图2 弹射系统仿真模型
Fig.2 Simulation model of the launch system

表1 弹射系统部分装置尺寸<br/>Tab.1 Parameters of the launch system 单位:mm

表1 弹射系统部分装置尺寸
Tab.1 Parameters of the launch system 单位:mm

表2 药剂燃烧性能<br/>Tab.2 Combustion performance of grain

表2 药剂燃烧性能
Tab.2 Combustion performance of grain

表3 气体参数
Tab.3 Gas parameters

图3 药柱尺寸
Fig.3 Grain parameter

图4 药柱燃烧实验装置<br/>Fig.4 Experimental device of grain combustion

图4 药柱燃烧实验装置
Fig.4 Experimental device of grain combustion

图5 多药柱独立性测试容器<br/>Fig.5 Test container of multi-grains independence

图5 多药柱独立性测试容器
Fig.5 Test container of multi-grains independence

图6 多药柱独立性测试实验的药柱情况<br/>Fig.6 Grain situation in the independence test of multi-grains

图6 多药柱独立性测试实验的药柱情况
Fig.6 Grain situation in the independence test of multi-grains

图7 单根药柱作用于不同质量弹体仿真所得曲线<br/>Fig.7 Simulation curves of a single grain acting on different projectile weights

图7 单根药柱作用于不同质量弹体仿真所得曲线
Fig.7 Simulation curves of a single grain acting on different projectile weights

图8 同一弹体多药柱同时作用仿真所得曲线<br/>Fig.8 Simulation curves of a specific projectile acted by multi-grains

图8 同一弹体多药柱同时作用仿真所得曲线
Fig.8 Simulation curves of a specific projectile acted by multi-grains

图9 同一弹体三根药柱不同作用时序仿真所得曲线<br/>Fig.9 Simulation curves of a specific projectile acted by three columns with different action sequences

图9 同一弹体三根药柱不同作用时序仿真所得曲线
Fig.9 Simulation curves of a specific projectile acted by three columns with different action sequences

[1] 申鹏, 吴新跃, 安晨亮.基于能量调节动力系统的变深度冷发射技术[J].导弹与航天运载技术, 2016(2):72-76.
[2] 白俊华, 胡春波.无冷却式发射动力系统的内弹道研究[J].西北工业大学学报, 2012, 30(6):892-897.
[3] 陈庆贵, 齐强, 王海洋, 等.潜射导弹发射内弹道仿真研究[J].导弹与航天运载技术, 2011(6):40-42.
[4] 陈庆贵, 齐强, 朱保义.某型导弹发射内弹道数值仿真[J].海军航空工程学院学报, 2010, 25(5):501-504.
[5] 陈庆贵, 齐强, 周源, 等.发射动力系统内弹道优化设计计算[J].舰船科学技术, 2011, 33(5):91-93, 97.
[6] 何坤.锥阀式燃气流量调节系统设计与实验研究[D].南京:南京理工大学, 2017.
[7] 鲍文, 牛文玉, 陈林泉, 等.固体火箭冲压发动机燃气发生器及燃气流量调节阀建模及仿真[J].固体火箭技术, 2008, 31(6):569-574.
[8] 王玲玲.固体火箭发动机点火过程数值分析[D].哈尔滨:哈尔滨工程大学, 2008.
[9] IWAKIRI T.Gas generator assembly:US 8567819 B2[P].2013-10-29.
[10] DUNAWAY J D, GARBE D J, SAMPSON W P, et al.Gas generators, launch tubes including gas generators and related systems and methods:US 8967046 B2[P].2015-03-03.
[11] DUNAWAY J D, GARBE D J, SAMPSON W P, et al.Gas generators, launch tubes including gas generators and related systems and methods:US 0131070 A1[P].2017-03-28.
[12] HANANO T, YAMAZAKI M.Gas generator:US 10046727 B2[P].2018-08-14.
[13] 秦新华, 叶力华, 周塞塞, 等.燃气发生器固定连接结构可靠性改进设计[J].火箭推进, 2014, 40(6):31-36.
[14] 王鹏, 李旭昌, 徐颖军.固体火箭发动机总体优化设计[J].火箭推进, 2007, 33(4):16-19.
[15] GANY A, AHARON I. Internal ballistics considerations of nozzleless rocket motors[J].Journal of Propulsion and Power, 1999, 15(6): 866-873.
[16] 赵坚, 张振鹏. 串装双燃速药柱发动机的内流场计算[J].推进技术, 2001, 22(4):315-318.
[17] 周哲, 王国平, 芮筱亭, 等. 固体脉冲推力器内弹道仿真与优化设计[J].弹道学报, 2016, 28(1): 8-13.
[18] 徐学文, 牟俊林, 任建存, 等.固体火箭发动机喷管瞬态流场特性分析[J].火箭推进, 2015, 41(5):49-53.
[19] 杨乐, 余贞勇, 何景轩.基于FLUENT的固体火箭发动机点火瞬态内流场仿真影响因素分析[J].固体火箭技术, 2011, 34(4):474-477.
[20] 唐金兰, 刘佩进.固体火箭发动机原理[M].北京:国防工业出版社, 2013.
[21] 乔宏, 伊寅, 李洪伟, 等.固体火箭发动机水下应用时的燃速特性分析[J].火箭推进, 2008, 34(6):23-26.
[22] 湖北航天化学技术研究所.一种燃气发生剂药柱:CN201310200885.5[P].2013-08-28.
[23] 湖北航天化学技术研究所.一种低燃温低残渣型燃气发生剂及其制备方法:CN201711419551.1[P].2018-06-19.
[24] LV J, ZENG Q X, LI M Y.Metal foil gap switch and its electrical properties[J].Review of Scientific Instruments, 2013, 84(4):045101.
[25] ZENG Q X, LV J, LI M Y.Note:The influence of exploding foil shape on energy deposition[J].Review of Scientific Instruments, 2013, 84(6):066105.

备注

引言

1 变推力驱动装置设计

2 弹射系统仿真结果与分析

3 结语

期刊信息