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MMH/NTO injection and ignition in vacuum downstream from an Aestus engine single injection element

机译：Aestus发动机单喷射元件下游的MMH / NTO喷射和真空点火

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An experimental study of the injection and ignition of MMH and NTO propellants injected under vacuum conditions downstream from an Aestus rocket-engine single element injector was undertaken to investigate the physical phenomena occurring during the first steps of injection and ignition in the actual conditions of the Aestus engine. A laser sheet technique was used to visualize the phenomena in a windowed combustion chamber, connected, through a sonic throat, to a vacuum tank. The injector and the combustion chamber were equipped with large bandwidth temperature and pressure transducers to follow accurately the unsteady phenomena. The paper describes the injection of each propellant injected alone and then their ignition when they are injected together. The low pressure conditions (200 hPa) have no influence on the MMH injection. On the contrary, the NTO spray is strongly modified when injected in vacuum (5 hPa). Ignition is always smooth because of the oxidizer injection lead procedure used and totally ruled by the MMH flow rate. Finally, because of the oxidizer injection lead procedure, frequent pre-ignitions between MMH and NTO vapor are observed in the MMH manifold when this valve is opened. According to the experimental conditions, these pre-ignitions are smooth and limited or steep.
机译：对在Aestus火箭发动机单元素喷油器下游的真空条件下注入的MMH和NTO推进剂的注入和点燃进行了实验研究，以调查在Aestus实际条件下的注入和点燃的第一步过程中发生的物理现象发动机。激光薄片技术用于可视化窗口化燃烧室中的现象，该窗口通过声波喉连接到真空箱。喷油器和燃烧室配有大带宽温度和压力传感器，可以精确地跟踪不稳定现象。本文介绍了每种单独喷射的推进剂的喷射，然后将它们一起喷射时的点火。低压条件（200 hPa）对MMH注入没有影响。相反，在真空（5 hPa）中注入时，NTO喷雾剂会发生强烈变化。由于使用的氧化剂注入铅程序完全由MMH流量控制，因此点火始终很平稳。最后，由于使用了氧化剂注入引导程序，因此在打开此阀时，会在MMH歧管中观察到MMH和NTO蒸气之间频繁的提前点火。根据实验条件，这些提前点火是平滑的，有限的或陡峭的。

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