无喷管助推器内弹道数值仿真及性能优化  

Numerical Simulation and Performance Optimization of the Internal Trajectory of Nozzleless Booster

作　　者：赵永涛[1] 牛楠[1] 杨玉新[1] 曾庆海[1] ZHAO Yongtao;NIU Nan;YANG Yuxin;ZENG Qinghai(The 41st Institute of the Forth 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》2017年第6期62-64,84,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：利用Fluent软件提供的动网格技术、UDF编程技术,结合无喷管助推器的侵蚀燃烧规律,建立了无喷管助推器内流场数值仿真模型。为验证数值仿真模型精度,进行了两发无喷管助推器的地面验证试验,发动机的推力曲线和压强曲线与数值仿真结果基本一致,预示精度在误差范围之内。最后,研究了不同扩张半角以及不同装药造型等对无喷管助推器性能的影响。结果表明,扩张半角为24°时,其性能最优;串装及层装药型均可有效提高无喷管助推器比冲。Dynamic mesh technology and UDF programming technology provided by Fluent software were used to build the numerical simulation model of the inner flow field of nozzleless booster combined with the erosion and combustion law of nozzleless booster.In order to check the precision of the numerical simulation model,two ground verification experiment of two nozzleless booster was carried out and the thrust curve and pressure curve of the engine were basically agreed with the numerical simulation result,which indicated that the accuracy was within the error range.Finally,the effects of different half angle and different charge molding on performance of nozzleless booster were studied.The results show that the performance achieves optimization when the half angle is 24 degrees.Series and layer charge type can improve the specific impulse of nozzleless booster effectively.

关 键 词：整体式固体火箭冲压发动机 无喷管助推器 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]