不同射击工况下膛内模块装药的热安全性预测

(1.南京理工大学能源与动力工程学院,江苏 南京 210094; 2.中国电子科技集团公司光电研究院,天津 300308)

物理化学; 发射药; 模块装药; 热安全性; 射击工况; 烤燃特性

Thermal Safety Prediction of Modular Charge in the Chamber under Different Firing Conditions
QIAN Huan-yu1,YU Yong-gang1,LIU Jing2

(1.School of Energy and Power Engineering, Nanjing University of Science and Technology,Nanjing 210094, China; 2. Academy of Opto-electronic, China Electronics Technology Group Corporation,Tianjin 300308, China)

physical chemistry; gun propellant; modular charge; thermal safety; firing conditions; cook-off characteristics

DOI: 10.14077/j.issn.1007-7812.201904022

备注

为研究火炮多发连续射击情况下模块装药滞留膛内的热安全性问题,建立了膛内模块装药二维非稳态烤燃模型,采用FLUENT软件对模块装药在膛内的烤燃过程进行了数值模拟,分析了3种射击工况下多发连续射击后继续装填模块装药留膛时的烤燃特性。结果 表明,常温下不同射击工况对膛内模块装药的烤燃响应时间影响较大,对烤燃起始响应位置影响较小,对烤燃响应温度几乎无影响; 采用5发/min射速射击32发后模块装药的烤燃响应时间为399.2s,采用1发/min射速射击43发和采用混合射速射击41发后模块装药的烤燃响应时间分别为176.4s和179.6s。3种射击工况下均是靠近模块盒右侧端面处的单基药最先着火,并形成环形烤燃响应区,单基药的烤燃响应温度分别为459.2、462.7和460.0K。

To study the thermal safety of modular charge in the artillery chamber after continuous fire rounds, a 2D unsteady state cook-off model of modular charge in the chamber was established. The cook-off process of modular charge in the chamber was numerically simulated by FLUENT software, and the cook-off response characteristics of modular charge reloaded in the chamber after three continuous firing conditions was analyzed. The results show that firing conditions have much influence on the cook-off response time of modular charge, while it has little influence on the initial cook-off response position and cook-off response temperature. The cook-off response time of modular charge is 399.2s under the condition of firing 32 rounds at 5 rounds/min, while response times are 176.4s and 179.6s under conditions of firing 43 rounds at 1 round/min and firing 42 rounds at a mixed firing speed. The initial ignition position is near the right end of the cartridge, where the single-base propellant is ignited first and an annular firing response zone is formed for all three conditions. The ignition response temperatures of single-base propellant are 459.2, 462.7and 460.0 K, respectively.