火箭推进2025，Vol.51Issue(5)：93-101,110,10.DOI:10.3969/j.issn.1672-9374.2025.05.010
喷管喉径对火药点火器点火性能影响仿真分析
Simulation analysis of nozzle throat diameter effect on ignition performance of powder igniter
摘要
Abstract
In order to ensure that the ignition performance of the main charge of the propellant igniter of a carrier rocket gas generator meets the requirements under low temperature conditions,the interior ballistic combustion model and simulation model of the propellant igniter based on classical interior ballistic theory were established.The Simulink module of MATLAB software was utilized to solve the interior ballistic simulation model,and obtain ignition pressure-time curves in the combustion chamber of the propellant igniter when the nozzle throat diameters are 3.2,3.4,3.6,3.8 and 4.0 mm under low temperature conditions,respectively.The ignition impulse and pressure peak under different nozzle throat diameters were calculated using Origin software to determine the trend of ignition impulse and pressure peak with nozzle throat diameter.By considering the critical ignition impulse required for normal ignition of the main charge of the igniter and the maximum pressure that the igniter shell can withstand,the optimal range for nozzle throat diameter design of the generator gunpowder igniter is determined to be 3.4-3.6 mm.Experimental results demonstrate that the simulation results are in good agreement with experimental verification,with an error rate of less than 5%.关键词
发生器火药点火器/喷管喉径/点火冲量/压力峰值Key words
generator gunpowder igniter/nozzle throat diameter/ignition impulse/peak pressure引用本文复制引用
朱珂,柳洋,何昆,李雪飞,张靖宇,董海平..喷管喉径对火药点火器点火性能影响仿真分析[J].火箭推进,2025,51(5):93-101,110,10.基金项目
国家自然科学基金联合基金(U1530135) （U1530135）
