微重力火箭设计中减旋方案等问题  

On the Problems of Gyration Reduction etc in Microgravity Rocket Design

作　　者：程养民[1] 

机构地区：[1]中国航天工业总公司四院四十一所

出　　处：《固体火箭技术》1999年第1期1-5,共5页Journal of Solid Rocket Technology

摘　　要：讨论了一种微重力火箭总体设计中减旋方案、飞行载荷、气动加热与壁温计算等几个关键问题。结合该火箭的具体特点，提出了一种简单实用的被动式减旋措施，即，安装反旋尾翼及辅助减旋机构，并分析了减旋与动稳定性的关系。对超高音速火箭的飞行载荷和气动热进行了分析计算。The gyration reduction proposals, calculations of the flight loads, airdynamic heating and rocket wall temperature in microgravity rocket system design are discussed. Proceeding from the actual situation of the rocket, a practical measure for passive gyration reduction installing a contrarotating tail fins and auxiliary gyration reduction device is put forward. And the relation between the gyration reduction and dynamic stability is analyzed. The flight loads and dynamic heating of the rocket during flight in a high supersonic velocity are also analyzed and calculated.

关 键 词：微重力实验 探空火箭 旋转 飞行载荷 减旋方案 

分 类 号：V421.1[航空宇航科学与技术—飞行器设计]