固体发动机喷管喉径烧蚀辨识技术  

Discrimination Technology for the Nozzle Throat Diameter Erosion Performance of Solid Rocket Motor

作　　者：李媛[1] 周艳青 孙展鹏 孙迪 马亮 LI Yuan;ZHOU Yanqing;SUN Zhanpeng;SUN Di;MA Liang(The 41st Institute of the Fourth Academy,CASC,Xi’an 710025,China)

机构地区：[1]中国航天科技集团公司第四研究院第41研究所,西安710025

出　　处：《弹箭与制导学报》2020年第2期60-62,共3页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为研究固体火箭发动机工作过程中的喷管喉径变化规律,采用宏观分析方法,以固体发动机地面点火试验为基础,获得喷管喉径的实时变化趋势,建立了喷管喉径烧蚀辨识模型。研究结果表明,喷管喉径烧蚀辨识模型可以较好的模拟发动机工作过程中喉径的变化情况,且模型计算值与发动机地面点火试验后的喷管喉径实测值吻合。在工程研制中,当发动机设计状态一定时,该模型可用于计算喷管喉径烧蚀变化情况,进而为发动机内弹道性能预示提供参考。The variation curve of nozzle throat diameter erosion performance of solid rocket motor(SRM)was studied by static ignition testing data to study the change law of nozzle throat diameter erosion performance.Macroscopic analysis method is used basing on the ground ignition test data of SRM in order to obtain the real time change trend of nozzle throat diameter and establish the discrimination model of nozzle throat diameter erosion.The results show that the identification model can be commendably used to simulate the variation of nozzle-diameter during SRM working process,and the model calculation value is in good agreement with the nozzle throat diameter measurement.In engineering development,when the design state of the SRM is certain,the model can be used to calculate the change of nozzle throat diameter erosion,and provide reference for the engine internal ballistic performance prediction.

关 键 词：固体发动机 喷管喉径 烧蚀 辨识 模型 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]