微重力火箭气动加热计算  

Aerodynamic heating calculation of micro-gravity rocket

作　　者：乐发仁[1] 杨军[1] 姜贵庆[2] 卢睿[1] 

机构地区：[1]中国航天科技集团公司四院四十一所,西安710025 [2]中国航天科技集团公司七一所,北京100074

出　　处：《固体火箭技术》2003年第1期1-3,9,共4页Journal of Solid Rocket Technology

摘　　要：针对气动外形为曲线、锥(柱)旋转组合体的微重力火箭,采用半球 柱(锥)和后掠翼的气矾加热计算方法及公式,分析计算了超高音速飞行状态下微重力火箭各特征表面上的热流及温度,并用一元平板传热模型和差分方法计算了箭体结构内部的温度分布,为箭体结构及热防护提供了有效的设计方法和可靠依据。The heat flux density and temperature on each character surface of microgravity rocket under the ultrasonic state, whose aerodynamic configuration is the combination rotating body of curve , are calculated and analyzed by the aerodynamic heating calculation method and equation of hemispherecolumn(cone) and sweepback wing.The temperature distribution within the structure of rocket is calculated by using the heat transfer model of onedimension plate and differential method.The effective design methods and credible basis for the structure and heat shield of rocket are provided.

关 键 词：微重力火箭 超音速 气动加热 热流密度 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]