大长径比固体发动机侵蚀燃烧影响研究  

Research on Erosive Burning Property of Solid Rocket Motor with Large Length-to-Diameter Ratio

作　　者：杨喜军[1] 程慧[1] 张涛[1] Yang Xijun;Cheng Hui;Zhang Tao(The 41st Institute of the Fourth Academy of CASC, Xi＇ an 710025,)

机构地区：[1]中国航天科技集团公司四院41所,西安710025

出　　处：《战术导弹技术》2018年第2期102-106,共5页Tactical Missile Technology

摘　　要：针对大长径比固体发动机可能出现的侵蚀燃烧现象,通过燃烧室一维准定常流场计算,获得了以流速和压强为参数的侵蚀燃烧规律,建立了轴向各部位侵蚀比函数,采用分步燃面退移数值方法,模拟了药柱燃面退移过程,实现了发动机侵蚀燃烧条件下的内弹道精确预示。研究结果表明:大长径比发动机药柱中孔气流流速沿轴向逐渐增大,静压逐渐减小;工作初始阶段会出现侵蚀燃烧,且越靠近出口侵蚀效应越明显,随着药柱退移,各部位侵蚀效应逐渐减弱;燃面曲线和压强曲线会出现前高后低的趋势,与实测结果吻合。The phenomenon of erosive burning usually exists in the working process of solid rocket motor with large length-to-diameter ratio.Variation laws of erosion transfer with velocity and pressure is obtained by one dimensional semi-steady flow field simulation.The change laws of the burning area considering erosion is formulated from segmented numerical simulation,based on which the internal ballistics can be predicted accurately.Our study shows that the center hole flow velocity will increase gradually with the increasing of the axial length,while the static pressure will decrease gradually.Erosive burning effect is obvious in the initial working stage,the closer to the exit,the more obvious the erosive burning property.The erosion diminishes with burning surface passing.The burning surface profile and the pressure curve show a first post-high-low trend,which are in good agreement with the experimental data.

关 键 词：固体火箭发动机 侵蚀燃烧 燃面退移 内弹道 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]