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FADS在尖楔前体高超声速飞行器外形中的应用 被引量:1

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摘要 对于具有尖楔前体的高超声速飞行器外形,特别是某些验证超燃发动机项目的飞行器外形,仅仅依靠惯性导航系统得到的攻角不能满足其精度要求。嵌入式大气数据传感系统作为一种先进的大气数据传感系统,可以准确地测量攻角,为此可以将INS与FADS结合运用到尖楔前体的高超声速飞行器外形中。就FADS系统在具有尖楔前体高超声速飞行器外形中的工作原理及校准方法进行了探讨。
出处 《飞航导弹》 北大核心 2012年第5期16-20,73,共6页 AERODYNAMIC MISSILE JOURNAL
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同被引文献7

  • 1郑守铎,陆宇平,叶玮.FADS系统迭代算法的收敛性分析[J].航空计算技术,2007,37(1):15-18. 被引量:2
  • 2科林·西格尔.超燃冲压发动机:过程和特性[M].北京:航空工业出版社.2012.
  • 3Whitmore, S. A., Cobleigh, B. R., Haering, E. A., Jr. Design mid calibration of the X-33 Flush Airdata Sensing (FADS) system[ C]. AIAA, Aerospace Sciences Meeting & Exhibit, 36th, Reno, NV; UNITED STATES, 1998.
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  • 6叶玮,郑守铎,温瑞珩.FADS/INS组合法迎角、侧滑角测量方法研究[J].飞机设计,2007,27(6):14-18. 被引量:12
  • 7王鹏,金鑫,张卫民.FADS/INS组合系统融合方法[J].战术导弹技术,2012(6):70-73. 被引量:2

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