TY-4火箭发射装置导流器热结构计算分析  

Analysis on thermal structure of guider for TY-4 rocket launcher

作　　者：赵宪斌[1] 乐发仁[1] 杨军[1] 王永平[1] 高昱[1] 

机构地区：[1]中国航天科技集团公司四院设计部,西安710025

出　　处：《固体火箭技术》2005年第2期87-90,共4页Journal of Solid Rocket Technology

摘　　要：根据TY4火箭离轨段燃气流瞬态特性,对双面楔形导流器面板强度、温度参数和离轨扰动等具体技术问题进行了计算分析。结果表明,采用熔点和导热系数高的导流材料,使热量沿厚度方向传递,可以容纳燃气传热,降低表面温度,减少烧蚀;导流型面和冲击角的设计,对于减小冲击,抑制火箭起始扰动有重要作用。Based on transient characteristics of hot gas flow during the rocket off-orbit period, some key technologies were calculated and analyzed, such as panel strength of double-edged wedge guider, temperature parameters and off-orbit disturbance. The results show the that by using guider material with high melting point and high heat conductivity coefficient, the heat in hot gas flow can be transferred across the thickness direction, and surface temperature and erosion can be reduced. The reasonable design of guider contour and impact angle can play an important role in controlling impact and initial disturbance of rockets.

关 键 词：导流器 燃气流 火箭发射装置 热结构 

分 类 号：V553.1[航空宇航科学与技术—人机与环境工程]