临近空间飞行器多体分离气动分析  

Aerodynamic analysis on separation of cluster munition in near space

作　　者：王宏伟[1] 郭建国[1] 林鹏[1] 周军[1] 

机构地区：[1]西北工业大学精确制导与控制研究所,陕西西安710072

出　　处：《飞行力学》2012年第3期250-253,共4页Flight Dynamics

摘　　要：针对临近空间特殊的飞行环境和流场特性,以面对称的子母弹为具体研究对象,采用CFD仿真计算的方法,得到了腹抛分离发射方式下分离速度、高度、子弹气动力与姿态角之间的关系,在研究和分析多者之间变化规律和趋势的基础上,提出了适用于临近空间腹抛分离发射的分离方案,这为今后开展该领域分离发射技术的研究和临近空间气动流场的仿真分析奠定了基础。To obtain the relationship of the speed,altitude,force and pitching angle in abdominal separation mode,the CFD simulation method was used in this article.For the special flight environment and airflow characteristics in near space,the spherically symmetric cluster munition was considered as the specific subject.By studying and analysis of multi-variation between the patterns and trends,the approaching separation scheme was proposed,which can provide an important basis for carrying out approaching launch technology and airflow simulation analysis.

关 键 词：多体分离 临近空间 分离方案 

分 类 号：V411.3[航空宇航科学与技术—航空宇航推进理论与工程]