propellant burning rate

Applying burning-rate catalysts is one of optimal approaches to regulate burning rate of HTPB propellant.

使用燃速催化剂是调节丁羟推进剂燃速的最佳途径之一.

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Effect of Nitramine on Energy and Burning Rate of Low Burning Rate HTPB Propellant

硝胺对低燃速丁羟推进剂能量与燃速的影响

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The decrease of the burning rate and flame temperature by adding energetic additive PQ is due to the reduction of energy level of the propellant and the decrease of the chemical reaction rate by the endothermic melting of PQ.

含能添加剂PQ降低燃速、燃温的原因是加入PQ后，推进剂的能量水平下降以及PQ在分解时的熔化吸热降低了化学反应速率。

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Experimental Research on Increasing the Burning Rate of Screw Extrusion Modified Nitramine Double Base Propellant

提高螺压硝胺改性双基推进剂燃速的试验研究

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It is considered that the combustion surface and the heat feedback of the propellant are increased by addition of ACP, leading that the increasing of burning rate of the propellant.

分析了ACP提高无烟改性双基推进剂燃速的作用机理，认为ACP可增加燃烧表面积和热量向燃烧表面积的反馈，使推进剂的燃速大增。

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Study on Software of Solid Propellant Burning Rate Prediction Based on one-dimensional Steady-state Reaction Gas Flow

基于一维气相稳态反应流的燃速预估软件研究

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The homogeneity reference material is studied by acoustic emission method for composite solid propellant burning rate.

采用声发射燃速测试方法研究了复合固体推进剂方坯燃速的均匀性.

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Based on the solid propellant burning rate formula, a new method for the combustion time determination during the data treatment in solid rocket motor firing test was studied with a method of numerical integration and interpolation.

以固体推进剂燃速公式为基础，采用计算力学中的数值积分及插值法，并利用计算机技术，研究了用燃烧室药柱的实际肉厚，确定固体火箭发动机试验曲线中燃烧时间的新方法。

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The NHC is an efficient modifier to make HTPB propellant obtain a high burning-rate of 80~ 100? mm/ s ( 9.8? MPa).

NHC是使丁羟推进剂获得80～100mm/s（9.8MPa）高燃速的有效调节剂。

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For the propellant mechanism of increasing burning rate is discussed.

分析了这种推进剂能提高燃速的机理.

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Increasing added quantity of ethyne carbon in the propellants can enhance the burning rate and lower the pressure exponent of the propellant in the pressure range of 3~ 20MPa.

增加乙炔碳黑含量可使推进剂在3~20MPa压力范围内的燃速提高，压力指数降低。

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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

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