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微重力火箭设计中减旋方案等问题 被引量:1

On the Problems of Gyration Reduction etc in Microgravity Rocket Design
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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.
作者 程养民
出处 《固体火箭技术》 EI CAS CSCD 1999年第1期1-5,共5页 Journal of Solid Rocket Technology
关键词 微重力实验 探空火箭 旋转 飞行载荷 减旋方案 microgravity test sounding rocket gyration flight load dynamic heating
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参考文献8

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  • 2钱立志.弹载任务设备抗高过载方法研究[J].兵工学报,2007,28(8):1017-1020. 被引量:27
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