Feasibility Study of a Hybrid Thruster using Wire-Shaped Magnesium and Water for Application to Small Spacecraft
Feasibility Study of a Hybrid Thruster using Wire-Shaped Magnesium and Water for Application to Small Spacecraft
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DOI：
10.2322/tjsass.64.223
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发表时间：
2021
影响因子：
1.1
通讯作者：
Mariko Akiyama;K. Nishii;Yoshihito Mannami;Masaya Murohara;H. Koizumi;K. Komurasaki
中科院分区：
文献类型：
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作者：
Mariko Akiyama;K. Nishii;Yoshihito Mannami;Masaya Murohara;H. Koizumi;K. Komurasaki
为了扩大小型航天器的使用，迫切需要可用于小型航天器的大推力推进系统。这项研究提出了一种用于小型航天器的混合推进器，使用线状镁作为燃料，水作为氧化剂。“混合推进器”指的是空间推进系统利用固体燃料和蒸汽氧化剂之间的化学反应产生推力，例如用于混合火箭的推进器。镁和水都是非常安全的，高度可用的，并且非常容易储存。为了评估混合推进器的可行性，我们利用镁丝在低于大气压力的水蒸气中进行了燃烧实验，并估计了点火输入功率、可燃性和平均镁质量消耗率。然后，利用实验结果对推进性能进行了计算，结果表明，对于较细的镁丝，输入功率为2~3W时，具有较高的可点火性和较低的平均质量消耗率。计算得到的比冲在323时达到最大值，S的质量混合比为1.25.在该质量混合比下，直径为0.5 mm和0.8 mm的镁丝推力分别为49.8mN和68.5mN。此外，通过考虑现有深空导弹的案例研究，说明了混合推进器的适用性。
High thrust propulsion systems that can be used in small spacecraft are urgently needed to expand the use of small spacecraft. This study proposes a hybrid thruster for small spacecraft using wire-shaped magnesium as a fuel and water as an oxidizer. “Hybrid thruster” means that the in-space propulsion system generates thrust using a chemical reaction between a solid fuel and a vapor oxidizer, such as those utilized for hybrid rockets. Both magnesium and water are very safe, highly available, and very storable. To assess the feasibility of a hybrid thruster, we carried out experiments utilizing magnesium-wire combustion in water vapor at a pressure lower than the atmosphere, and estimated the input power for ignition, ignitability, and the average magnesium mass consumption rate. Then, propulsion performances were calculated using the experimental results, which show there is an input power of 2–3W, with higher ignitability and a lower average mass consumption rate for thinner magnesium wires. The calculated specific impulse achieved its maximum at 323 s, with a mass mixture ratio of 1.25. At that mass mixture ratio, the calculated thrust using magnesium wires having diameters of 0.5mm and 0.8mm was 49.8mN and 68.5mN, respectively. Additionally, the applicability of the hybrid thruster was shown through a case study considering an existing deep-space misson.