Development of Nano‐Al Based Highly Metalized Fuel‐Rich Propellant for Water Ramjet Propulsion Applications,Propellants, Explosives, Pyrotechnics

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Development of Nano‐Al Based Highly Metalized Fuel‐Rich Propellant for Water Ramjet Propulsion Applications
Propellants, Explosives, Pyrotechnics ( IF 1.7 ) Pub Date : 2020-03-13 , DOI: 10.1002/prep.201900384
Murugesan Ramakrishnan ₁ , Satyanarayanan R. Chakravarthy ₁ , Jayaraman Kandasamy ₁ , Ramanujam Sarathi ₂

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Aluminium‐water reaction‐based ramjet propulsion system shows the higher theoretical performance when compared to the conventional solid propellant based propulsion system for high‐speed underwater applications. In the present study, investigations have been carried out on water ramjet propulsive performance using theoretical approach and also the primary combustion characteristics of the fuel‐rich propellant compositions studied experimentally. The aluminized fuel‐rich propellant compositions contain 40–50 % of aluminium with the average particle sizes of 18 μm, 250 nm, and 100 nm, and also comprise 34.5‐46 % of Ammonium Perchlorate (AP) in a total of 15 formulations, are tested over a pressure range of 0.2–3.1 MPa in CO₂ atmosphere. Paraffin wax and Hydroxyl‐terminated Polybutadiene (HTPB) based binders are used for the preparation of the nano and micro aluminized propellants respectively. Primary combustion features are estimated using thermochemical calculation for the fuel‐rich propellants. The calculations show that the increase of metal fraction from 40–60 % in the composition leads to a marginal decrement in the combustion temperature whereas it favors the formation of a large fraction of condensed phase products and the presence of unreacted metals also increases considerably. Theoretical propulsive performance calculations show that higher I_sp is ascertained with the higher metal content in the fuel‐rich propellants. By comparing with Magnesium (Mg) and Aluminium (Al) based propellants, a water ramjet‐powered using Boron (B)‐based propellant shows higher theoretical specific impulse for a ratio of water to fuel greater than 1. The primary combustion of propellants comprises 50 % aluminium by mass and causes more than 20 % of mass to leave as residue, which mainly contains unreacted aluminium, besides other condensed phase combustion products. Nano aluminized propellant compositions show a 2–5 times higher burning rate than the micro aluminized counterparts. These propellants exhibit a wide range of pressure indices (n) from 0.23 to 0.56. Morphology and elemental composition of condensed phase combustion products from primary combustion are also examined.

中文翻译：

用于水冲压发动机应用的纳米铝基高金属化富油推进剂的开发

与传统的基于固体推进剂的高速水下推进系统相比，基于铝-水反应的冲压喷气推进系统具有更高的理论性能。在本研究中，已经使用理论方法对水冲压冲压发动机的推进性能进行了研究，并通过实验研究了富燃料推进剂组合物的主要燃烧特性。含铝燃料丰富的推进剂组合物包含40％至50％的铝，平均粒径为18μm，250 nm和100 nm，在总共15种配方中还包含34.5％至46％的高氯酸铵（AP），在CO _2中在0.2–3.1 MPa的压力范围内进行了测试大气层。石蜡和羟基封端的聚丁二烯（HTPB）基的粘合剂分别用于制备纳米和微铝化推进剂。使用热化学计算估算富含燃料的推进剂的主要燃烧特性。计算表明，组成中金属分数从40-60％的增加导致燃烧温度略有下降，而这有利于形成大部分冷凝相产物，未反应金属的存在也大大增加。理论推进性能计算表明，较高的I _sp可以确定富含燃料的推进剂中的金属含量较高。通过与基于镁（Mg）和铝（Al）的推进剂进行比较，使用基于硼（B）的推进剂的水冲压发动机显示出更高的理论比冲，适用于水/燃料比大于1的情况。铝的质量百分比为50％，并导致超过20％的质量作为残留物残留，除其他冷凝相燃烧产物外，其主要包含未反应的铝。纳米铝化推进剂组合物的燃烧速率是微铝化推进剂的2-5倍。这些推进剂的压力指数（n）范围从0.23到0.56。还检查了一次燃烧产生的冷凝相燃烧产物的形态和元素组成。

更新日期：2020-03-13

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