一种固体小运载火箭弹道优化研究方法  

A Research Method for Ballistic Optimization of Small Solid Launch Vehicle

作　　者：薛杰 李晓晖 程养民 XUE Jie;LI Xiaohui;CHENG Yangmin(National Key Laboratory of Combustion,Thermo-structure and Flow,Xi’an Aerospace Propulsion Technology Institute,Xi’an 710025,China)

机构地区：[1]西安航天动力技术研究所固体火箭发动机燃烧、热结构和内流场国防科技重点实验室,西安710025

出　　处：《弹箭与制导学报》2020年第5期48-51,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为优化运载火箭弹道,以微小型固体运载火箭为研究对象,通过Simulink建立六自由度仿真模型,开展弹道优化相关问题的研究与分析。结果表明,在运载火箭发动机推力给定的条件下,此运载火箭达到入轨条件的最大有效载荷为218.8 kg,比基本方案提高9.4%。In order to optimize the launch vehicle trajectory,This paper takes the micro-small solid-state launch vehicle as the research object,and establishes a six-degree-of-freedom simulation model through Simulink,and carries out a research and analysis on the issues related to ballistic optimization.The analysis results show that under the condition given by the thrust of the launch vehicle engine,the maximum payload of the launch vehicle reaching the orbital condition is 218.8 kg,which is 9.4%higher than the basic scheme.

关 键 词：运载火箭 六自由度 仿真设计 弹道优化 有效载荷 

分 类 号：TJ760[兵器科学与技术—武器系统与运用工程] V475.1[航空宇航科学与技术—飞行器设计]