Electric solid propellants are advanced solid chemical rocket propellants controlled by electric current. Electric solid propellants may also be used in an electric propulsion system, specifically, an ablative pulsed plasma thruster. Previous experiments with the electric solid propellant HIPEP suggest its ablation processes are similar to traditional propellant polytetrafluoroethylene (C_2F_4). Better understanding of the ablation and resulting propulsion performance of HIPEP requires a model of its vapor composition and transport properties. This paper reports on the development of such a model. The model was validated by comparing results for C_2F_4 with literature, which showed agreement with multiple models described. Transport property results matched within an order of magnitude for temperatures less than 15,000 K and equilibrium composition densities matched to within an order of magnitude. The electric solid propellant vapor composition was predicted in the temperature range of 500-40,000 Kelvin at 1 bar pressure. Low temperatures (<2,000 K) are dominated by H_2O, CO_2 and N_2, and results at 700 K match within 10% of previous combustion model predictions. At high temperatures (>25,000 K) the vapor is strongly ionized and dominated by C~(2+), O~(2+), N~(2+), and H~+ ions. The viscosity of the electric solid propellant vapor is on the order of 10~(-4) kg/m/s and thermal conductivity is on the order of 10 W/m/K.
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机译：电动固体推进剂是通过电流控制的先进固体化学火箭推进剂。电动固体推进剂也可以用于电推进系统，具体地，一种烧蚀脉冲血浆推进器。先前的电动式推进剂Hipep的实验表明其消融方法类似于传统推进剂聚四氟乙烯（C_2F_4）。更好地理解嗜睡和产生的髋都推进性能需要其蒸气组成和运输性能的模型。本文报告了这种模型的发展。通过将C_2F_4与文献的结果进行比较，该模型验证，这与描述的多种模型进行了一致。运输物业符合级别的符合条件，温度低于15,000 k，平衡组成密度与幅度均匀匹配。在1巴压力下，预测电动固体推进剂蒸气组合物在500-40,000个开尔文的温度范围内。低温（<2,000 k）由H_2O，CO_2和N_2支配，结果在先前的燃烧模型预测的10％以内的700k匹配。在高温下（> 25,000k），蒸汽被强烈电离并由C〜（2+），O〜（2+），N〜（2+）和H〜+离子主导。电固体推进剂蒸气的粘度约为10〜（-4）kg / m / s，导热率约为10w / m / k。
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