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首页> 外文期刊>Journal of Energetic Materials >Silicone bridged iron metallocene butadiene composite solid propellant binder: aspects of thermal decomposition kinetics, pyrolysis and propellant burning rate
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Silicone bridged iron metallocene butadiene composite solid propellant binder: aspects of thermal decomposition kinetics, pyrolysis and propellant burning rate

机译：硅胶桥铁茂金属丁二烯复合材料固体推进剂粘合剂：热分解动力学，热解和推进剂燃烧率的方面

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Propellant binders are essential components of composite solid propellants (CSP's) used in launch vehicles and missiles. Binders act as a fuel and contribute directly to the combustion in conjunction with oxidizer particles and metallic fuel apart from imparting structural integrity to the solid propellant grain .The performance of CSP's are directly related to the burn rate of the propellant. The burn rates of the ammonium perchlorate (AP) propellants are generally moderated using various types of transition metal oxide (TMO) catalysts. However, TMO's are associated with inherently large dispersions in propellant burn rates and compromise on energetics. One of the most suitable methods for achieving lower dispersion in burn rate is using binders wherein a burn rate catalyst is grafted to the polymer matrix. In the present paper, the thermal decomposition of ferrocene bound hydroxyl terminated polybutadiene (FC-Si-HTPB) grafted to butadiene backbone via hydrosilylation was investigated The thermal degradation mechanism, stability and its effectiveness as burn rate catalyst are the most important aspects for use in CSP's. The mechanism of decomposition of the neat resin and in combination with AP has been elucidated using pyrolysis gas chromatography-mass spectrometric technique (GC-MS). FC-Si-HTPB exhibits single stage decomposition in the temperature range of 263-491 degrees C. The decomposition of FC-Si-HTPB with AP oxidizer follows a two stage mechanism in the 195-490 degrees C.The char residue was characterized using FTIR, Raman spectroscopy and FE-SEM analysis, which enables to vindicate the mechanism of reaction. The activation energy for the decomposition of HTPB is 283.6 kJ/mol, FC-Si-HTPB is 251.5 kJ/mol and for Fc-Si-HTPB-AP system is 67.1 kJ/mol. The major pyrolysis products of neat FC-Si-HTPB are ferrocenyl derivatives, silylated ferrocenyl derivatives and precursors emanating from polybutadiene backbone. The propellants based on the new binder exhibited an increase in burn rate with iron content and higher fine content. A comparison of propellant burn rate with conventional micron sized ferric oxide exhibited an improvement of 34%.Based on the thermal analysis studies, the thermal endurance of the system was computed to be FC-HTPB HTPB FC-HTPB-AP.
机译：推进剂粘合剂是发射车辆和导弹中使用的复合固体推进剂（CSP）的基本组分。粘合剂用作燃料并与氧化剂颗粒和金属燃料一起直接促进燃烧，除了赋予固体推进剂颗粒的结构完整性。CSP的性能与推进剂的烧伤率直接相关。使用各种过渡金属氧化物（TMO）催化剂，通常调节高氯酸铵（AP）推进剂的燃烧速率。然而，TMO与推进剂燃烧率的固有大型分散率有关，并在能量上妥协。用于在燃烧速率下实现较低分散的最合适的方法之一是使用粘合剂催化剂接枝到聚合物基质中的粘合剂。在本文中，研究了通过氢化硅烷化接枝到丁二烯主链的二茂铁结合的羟基封端的聚丁二烯（Fc-Si-HTPB）的热分解，作为燃烧速率催化剂是使用的最重要方面的热降解机理，稳定性及其有效性CSP的。使用热解气相色谱 - 质谱技术（GC-MS）阐明了整颗树脂和AP结合的分解机理。 FC-SI-HTPB在263-491℃的温度范围内表现出单级分解。与AP氧化剂的FC-SI-HTPB的分解在195-490℃下遵循两级机制。使用炭残余物FTIR，拉曼光谱和Fe-SEM分析，使能致力于反应的机制。 HTPB分解的活化能是283.6 kJ / mol，Fc-Si-HTPB为251.5 kJ / mol，对于Fc-Si-HTPB-AP系统为67.1kJ / mol。整齐的Fc-Si-HTPB的主要热解产物是二茂铁衍生物，甲硅烷基的二茂烷基衍生物和来自聚丁二烯骨架的前体。基于新粘合剂的推进剂表现出燃烧率的增加，铁含量和更高的细含量。具有传统微米尺寸的铁氧化物的推进剂燃烧速率的比较表现出34％的改善。基于热分析研究，该系统的热耐久性被计算为FC-HTPB＆GT; htpb＆ FC-HTPB-AP。

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