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Research on high pressure cryogenic combustion

机译：高压低温燃烧研究

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Due to their high specific impulse, Oxygen/Hydrogen systems are often used to increase launcher performance and will probably continue to be the preferred option for the next decades. In order to get insight into complex processes involved in the combustion of such propellants, research efforts have been conducted in both France and Germany including theoretical and experimental activities. This article deals with recent progress achieved by research teams from both countries in high pressure Oxygen/Hydrogen (O_2/H_2) combustion systems. In France, the research program was conducted in the framework of the GDR group including Snecma Moteurs-Rocket Engine Division, Centre National d'Etudes Spatiales (CNES), Centre National de la Recherche Scientifique (CNRS) and ONERA. In Germany, research was conducted in the framework of the national technology program "TEKAN" involving universities, DLR and Astrium. A close cooperation between teams was made possible through a Memorandum of Understanding (MoU) on research on high pressure cryogenic combustion. First, general design issues of liquid propellant engines are addressed, demonstrating a clear need for a new approach in engine development taking into account the complex chemical and physical processes in rocket engines. A brief description about the organization of the research programs is followed by a short presentation of the test facilities and the experimental setup's in use. Examples of experimental as well as numerical achievements applying sophisticated optical diagnostic tools are discussed and finally, the paper summarises the results achieved so far and addresses the questions still open.
机译：由于其高的比冲，氧气/氢气系统通常用于提高发射器的性能，并且在未来几十年中可能会继续成为首选。为了深入了解此类推进剂燃烧所涉及的复杂过程，法国和德国都进行了包括理论和实验活动在内的研究工作。本文讨论了两国研究小组在高压氧气/氢气（O_2 / H_2）燃烧系统中取得的最新进展。在法国，该研究计划是在GDR小组的框架内进行的，该小组包括Snecma Moteurs-火箭发动机分部，国家航天技术中心（CNES），国家科研中心（CNRS）和ONERA。在德国，研究是在国家技术计划“ TEKAN”的框架内进行的，涉及大学，DLR和Astrium。通过关于高压低温燃烧研究的谅解备忘录（MoU），团队之间的紧密合作成为可能。首先，解决了液体推进剂发动机的一般设计问题，明确表明了在发动机开发中需要一种新方法的考虑，其中要考虑到火箭发动机中复杂的化学和物理过程。在对研究程序的组织进行简要说明之后，简要介绍测试设备和使用中的实验装置。讨论了使用先进的光学诊断工具获得的实验和数值成果的示例，最后，本文总结了迄今为止取得的成果并解决了仍然存在的问题。

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