Abstract The objective of this research is to demonstrate the feasibility of sustained combustion in hybrid rocket motor configuration with oxidizers containing high concentrations of C O 2 , an in situ propellant suitable for Mars applications. Motor tests are performed by using N 2 O / C O 2 mixtures as the oxidizer and paraffin fuel loaded with high concentrations metal powders. Fuel grains with aluminum and magnesium powders have been cast at 40% by mass in the paraffin wax binder. C O 2 is mixed with liquid N 2 O up to 50% in weight percentage as a saturated liquid mixture. Experiments are performed in the blowdown mode using the self-pressurizing capability of the mixed oxidizers. A lab-scale hybrid motor with 70 mm grain length and 31 mm outer grain diameter is used to measure the key performance parameters such as regression rate and combustion efficiency. Successful ignition and sustained/stable combustion with the mixed oxidizer are achieved at C O 2 concentrations up to 43% by mass in the liquid mixture. The primary conclusion from this study is that the operation of hybrid rockets with substantial levels of in situ propellant C O 2 is feasible.

中文翻译：

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带有混合 N2O/CO2 氧化剂的混合火箭，用于火星上升车辆

摘要 本研究的目的是证明在混合火箭发动机配置中使用含有高浓度 CO 2 的氧化剂持续燃烧的可行性，CO 2 是一种适用于火星应用的原位推进剂。通过使用 N 2 O / CO 2 混合物作为氧化剂和负载高浓度金属粉末的石蜡燃料来进行电机测试。含铝和镁粉的燃料颗粒以 40% 的质量被浇铸在石蜡粘合剂中。CO 2 作为饱和液体混合物与液体N 2 O混合至多重量百分比为50%。使用混合氧化剂的自加压能力在排污模式下进行实验。使用具有 70 毫米颗粒长度和 31 毫米外颗粒直径的实验室规模混合电机来测量回归率和燃烧效率等关键性能参数。使用混合氧化剂在液体混合物中的 CO 2 浓度高达 43%（质量）时实现成功点火和持续/稳定燃烧。这项研究的主要结论是，使用大量原位推进剂 CO 2 的混合火箭运行是可行的。