In order to reduce the engine size and mass of spacecraft for Mars missions, powdered magnesium (Mg) and carbon dioxide rocket engines should use liquid carbon dioxide (liquid CO₂) as their oxidizer. Experimental studies are carried out on the characteristics of liquid CO₂ feed, powdered Mg feed, engine ignition, combustion, and pressure oscillation. Results show that both the feeding systems of liquid CO₂ and powdered Mg work stably. Although the use of liquid CO₂ makes ignition more difficult, reliable ignition and a stable flame are achieved by means of multi-step ignition. The Damköhler number, L/[v_j × (t_i + t_b)], incorporates the parameters of pre-combustion chamber length, powder-injection velocity, particle ignition delay, and burning time. Successful ignition is indicated by Damköhler number>1. Fluctuations in the powdered Mg feeding flowrate will cause serious combustion chamber pressure oscillation, whose maximum relative amplitude can be suppressed from 5.3% to 1.8% by choosing a suitable fluidization gas. Serious depositions are generated in the pre-chamber, which influence the propellant injection process and stable combustion process. The maximum relative amplitude of combustion pressure oscillation caused by this problem can grow up to 6%. The combustion efficiency of the engine reaches 83%, validating the feasibility of the powdered Mg and liquid CO₂ rocket engine.

为了减小用于火星飞行的航天器的发动机尺寸和质量，镁粉和二氧化碳火箭发动机应使用液态二氧化碳（液态CO ₂）作为氧化剂。对液态CO ₂进料，粉状Mg进料，发动机点火，燃烧和压力波动的特性进行了实验研究。结果表明，液态CO ₂和粉状Mg的进料系统均稳定运行。尽管使用液态CO ₂使点火更加困难，但是通过多步点火可以实现可靠的点火和稳定的火焰。达姆勒数L / [ v _j  ×（t _i  +  t_b）]，包括预燃烧室长度，喷粉速度，颗粒着火延迟和燃烧时间等参数。点火成功由Damköhler编号> 1表示。镁粉进料流量的波动会引起严重的燃烧室压力波动，通过选择合适的流化气体，其最大相对振幅可以从5.3％抑制到1.8％。预燃室中会产生严重的沉积物，这会影响推进剂的喷射过程和稳定的燃烧过程。由该问题引起的燃烧压力振荡的最大相对幅度可以增长到6％。发动机的燃烧效率达到83％，这证明了粉状Mg和液态CO ₂火箭发动机的可行性。