固体发动机装药CAD  

Computer Aided Design of Propellant Grains for Solid Rocket Motors

作　　者：鲍福廷[1] 李逢春[1] 徐东来[1] 

机构地区：[1]西北工业大学,西安710072

出　　处：《固体火箭技术》1994年第3期1-7,共7页Journal of Solid Rocket Technology

摘　　要：基于计算机图形处理直接获得燃面几何数据,发展了一种装药设计新方法,可以进行装药燃面、质量及惯性随肉厚变化的计算,为一维内弹道计算及流场计算提供更为详尽的数据,还能进行动态燃面推移,使设计者直观地判断其设计的合理性。A new Propellant grain design method which is based on computer graphic Processing techniques by geting burning suface data directly is developed .On this basis, other data such as burning area, mass properties and inertia properties versus web can be caculated respectively. Moreover,more detailed data for one dimensional internal ballistic and internal flow field caculations are presented. A propellant grain design computer code was developed. A dynamic burning surface recession allows the user to judge if his design is reasonable.

关 键 词：固体推进剂 火箭发动机 装药结构 药柱 CAD 

分 类 号：V435.21[航空宇航科学与技术—航空宇航推进理论与工程]