带非正锥头助推级火箭的地面风载荷风洞试验模型设计  

Wind Tunnel Test Model Design of Launch Vehicle with Non-right Circular Type Fairing Booster

作　　者：马斌捷[1] 吴艳红[1] 张冬梅[1] 刘祯[1] 侯传涛[1] 

机构地区：[1]北京强度环境研究所,北京100076

出　　处：《导弹与航天运载技术》2014年第3期60-67,共8页Missiles and Space Vehicles

摘　　要：介绍火箭地面风载荷试验的性质,讨论目前风洞地面风试验对侧平锥头助推级火箭模型设计的处理方法和合理性。根据圆锥曲线特性和侧平锥头的特点,利用抛物线方程和柱段直径,首次推导了侧平锥头对接面角度的表达式;为适应可能出现的斜锥头助推级,利用圆锥斜截面的理论结果推导斜锥头对接面角度的表达式,并给出形式简单的高精度近似公式,对斜锥柱反向对接的近似正锥性质进行分析,为火箭与模型的设计和加工提供了有效的工具。Ground wind loads test of launch vehicles was introduced in this paper. And design of scale model with non-right circular cone fairing was discussed. Using parabolic equations and column diameter, the angle expression of joint face between side-flat cone section and column section was deduced. Based on the results of cone oblique section theory, the angle expression of joint face between oblique cone and column section was deduced, for the launch vehicle with oblique cone type booster which may be used in future. The results can be used to design and process the launch vehicle and its scale model, and the high precision approximate formula is simplified.

关 键 词：侧平锥 斜锥 锥柱对接角度 风洞试验 靶场试验 

分 类 号：V416[航空宇航科学与技术—航空宇航推进理论与工程]