solid-propellant ducted rocket

 
  • 固体火箭冲压发动机

solid-propellant ducted rocket的用法和样例:

例句

  1. At first, the thermodynamic calculation of Solid Ducted Rocket is researche.
    在此基础上,首先对固体冲压发动机热力计算展开了研究分析。
  2. The characterization of the combustion properties of the aluminum? magnesium fuel? rich propellant for unchoked ducted rocket was studied.
    系统研究了铝镁贫氧推进剂低压燃烧特性的表征方法。
  3. The effects of TMOs and their mixtures on the burning rate and the pressure exponent of the aluminum magnesium fuel rich propellant for unchoked ducted rocket are investigated.
    研究了过渡金属氧化物(TMO)及其复配物对非壅塞固体火箭冲压发动机铝镁贫氧推进剂燃烧特性的影响。
  4. We shall try by means of a highly simplified development to expose certain advantages and disadvantages of solid propellant rocket systems.
    我们想通过相当简单的推导来试图阐明固体推进剂火箭系统的某些优缺点。
  5. J.J. Choury,carbon/carbon materials for nozzle of solid propellant rocket motors[J].AIAA76-609.
    崔红;李瑞珍;苏君明等.;多元基体抗烧蚀炭/炭复合材料的微观结构分析[J]
  6. In this paper, the theory of minitype Solid Ducted Rocket with shot is researche nd analyzed.
    本文研究和分析了炮射小型固体火箭冲压发动机的工作原理。

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