Abstract Multimode space propulsion systems are being proposed that integrate high specific impulse electric propulsion and high thrust chemical propulsion. The most important attribute of this concept is a shared propellant capable of both modes of propulsion, which enables mission flexibility. One promising approach is a catalytic monopropellant thruster paired with an electrospray electric thruster. Previous research has identified a green double-salt ionic liquid consisting of 41% wt. 1-ethyl-3-methylimidazolium ethyl sulfate and 59% wt. hydroxylammonium nitrate as a promising propellant candidate. In this work, the burn rate of this monopropellant is measured through pressure-based and high-speed imaging methods in a fixed-volume chamber pressurized across a pressure range from 0.5 to 10 MPa. Its performance is benchmarked by 80% wt. hydroxylammonium nitrate-water and nitromethane propellants. The burn rate of the multimode monopropellant is found to follow an exponential law given by r b = 5.35 exp 1.11 P between 0.5 and 3 MPa and is approximately constant at 142 ± 29 mm/s between 3 and 10 MPa.

中文翻译：

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绿色离子液体多模单组元推进剂的线性燃烧速率

摘要 将高比冲电力推进和高推力化学推进相结合的多模空间推进系统正在被提出。该概念最重要的属性是能够实现两种推进模式的共享推进剂，从而实现任务灵活性。一种有前景的方法是将催化单组元推进剂与电喷雾电动推进器配对。先前的研究已经确定了一种由 41% wt 组成的绿色双盐离子液体。1-乙基-3-甲基咪唑乙基硫酸盐和59%重量。硝酸羟铵是一种很有前途的推进剂候选者。在这项工作中，这种单组元推进剂的燃烧速率是通过基于压力和高速成像方法在固定体积的腔室中测量的，该腔室的压力范围为 0.5 到 10 MPa。其性能以 80% wt 为基准。硝酸羟铵-水和硝基甲烷推进剂。发现多模单组元推进剂的燃烧速率遵循由 rb = 5.35 exp 1.11 P 在 0.5 到 3 MPa 之间给出的指数规律，并且在 3 到 10 MPa 之间近似恒定在 142 ± 29 mm/s。