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低燃速推进剂
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  “低燃速推进剂”译为未确定词的双语例句
     AN INVESTIGATION ON THE BURNING RATE PERFORMANCE OF LOW BURNING RATE SOLID PROPELLANT APPLIED TO SPIN ROCKET MOTOR
     高速旋转固体发动机低燃速推进剂燃速性能的研究
短句来源
     o improve specific impulse of nozzleless rocket motors, this paper has investigated the anti-erosion performance of low burning rate solid propellant mixed with short fibre, shaping technology of reversed cone nozzle in the contraction section of propellant "nozzle" and concentric charging method of two solid propellants with various burning rates. The specific impulse of nozzleless rocket motorsis stabilized between 1882. 0~1989. 0 N· s/kg, which satisfies our requirement.
     为提高无喷管发动机的比冲,从装药角度研究了在低燃速推进剂配方中加入短纤维以提高推进剂的抗冲刷性能,采用装药"喷管"收敛段的倒锥形造型技术及两种不同燃速推进剂的同心层装药,使无喷管发动机的比冲稳定在1882.0~1989.0N·s/kg,满足了预定要求。
短句来源
  相似匹配句对
     ESTIMATE OF BURNING RATE OF PROPELLANT
     推进剂预估
短句来源
     Study on Low Burning Rate NEPE Propellant
     高能NEPE推进剂的研究
短句来源
     STUDY ON BURNING RATE CONTROL OF LOW BURNING RATE HTPB PROPELLANT
     HTPB推进剂控制研究
短句来源
     The Catalytic Combustion of DB Propellant with Low Burning Rate and Low Flame Temperature
     温双基推进剂的催化
短句来源
     A Study on Ultra High Burning Rate Propellants with Low Pressure Indices
     超高推进剂的压力敏感性
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o improve specific impulse of nozzleless rocket motors, this paper has investigated the anti-erosion performance of low burning rate solid propellant mixed with short fibre, shaping technology of reversed cone nozzle in the contraction section of propellant "nozzle" and concentric charging method of two solid propellants with various burning rates. The specific impulse of nozzleless rocket motorsis stabilized between 1882. 0~1989. 0 N· s/kg, which satisfies our requirement.The specific impulse of nozzleless...

o improve specific impulse of nozzleless rocket motors, this paper has investigated the anti-erosion performance of low burning rate solid propellant mixed with short fibre, shaping technology of reversed cone nozzle in the contraction section of propellant "nozzle" and concentric charging method of two solid propellants with various burning rates. The specific impulse of nozzleless rocket motorsis stabilized between 1882. 0~1989. 0 N· s/kg, which satisfies our requirement.The specific impulse of nozzleless rocket motors is extremely greater than that ofthe same rocket with nozzle.

为提高无喷管发动机的比冲,从装药角度研究了在低燃速推进剂配方中加入短纤维以提高推进剂的抗冲刷性能,采用装药"喷管"收敛段的倒锥形造型技术及两种不同燃速推进剂的同心层装药,使无喷管发动机的比冲稳定在1882.0~1989.0N·s/kg,满足了预定要求。与有喷管同类型发动机的内弹道性能比较,无喷管发动机的总冲量达到相当高的水平。

The effects of aluminum particle size on agglomeration situation orburning rate of aluminum powder were investigated.The experimental results and theoritical analysis indicate that the increase of aluminum particle size obviously decreases its agglomeration, but fine-grained aluminum improves its ignition and combustion characteristics.Due to the influence of aluminum particle size on thermal effect of the propellant burning surface, the burning rate decreases with the increase of aluminum particle size in...

The effects of aluminum particle size on agglomeration situation orburning rate of aluminum powder were investigated.The experimental results and theoritical analysis indicate that the increase of aluminum particle size obviously decreases its agglomeration, but fine-grained aluminum improves its ignition and combustion characteristics.Due to the influence of aluminum particle size on thermal effect of the propellant burning surface, the burning rate decreases with the increase of aluminum particle size in low burning rate propellant,but the situation is opposite to that in high burning rate propellant. Therefore, reasonable use of aluminum particle size is very important to formulation design of solid propellants.

研究了铝粉粒度对含铝推进剂铝粉凝聚行为和燃烧速度的影响。实验和理论分析表明,增大铝粉粒度有利于减小铝粉凝聚程度,而小粒度的铝粉可以改善其点火与燃烧特性。另外,由于铝粉粒度对推进剂燃面的热效应影响,因此,在低燃速推进剂中随铝粉粒度增大燃速降低;在高燃速推进剂中随铝粉粒度增大燃速升高;所以,合理使用铝粉粒度对研制固体推进剂配方是至关重要的。

 
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