液体火箭燃料贮箱破损的危害：低温液态氢氧混合物爆炸的条件和危险性
Hazards Induced by Breach of Liquid Rocket Fuel Tanks: Conditions and Risks of Cryogenic Liquid Hydrogen-Oxygen Mixture Explosions
摘要：
我们分析的数据有目的的破裂实验与液氧和液氢坦克，氢-氧垂直冲击（HOVI）的测试，进行澄清的点火机制，在不同条件下的低温H2/Ox混合物的爆炸力，并阐明令人费解的来源的初始形成的火焰附近的intertank部分在挑战者号灾难。我们进行了一个基于物理学的分析，一般的低温气态H2/Ox混合物的爆炸场景，并确定其实现条件，使用完善的简化模型从爆震和爆燃理论。我们研究气溶胶H2/Ox混合物燃烧的特点，并显示，特别是气溶胶加强爆燃火焰，并可以诱导爆震的任何点火机制。我们提出了一个空泡诱导机制的低温H2/Ox混合物，可以实现当气态H2和Ox流与液体Ox湍流混合，发生在所有HOVI测试自燃。我们提出了一个概述的HOVI测试作出结论，在可能的液体火箭事件的强烈爆炸的风险，并提供了一个半定量的解释的HOVI数据的基础上气溶胶燃烧。我们揭示了最危险的情况，并讨论了在太空任务中可能出现的可预见的风险，并导致悲惨的结果。我们的分析仅涉及可能因液体推进剂航天器事故而产生的无约束混合物。
英文摘要：
We analyze the data of purposeful rupture experiments with LOx and LH2 tanks, the Hydrogen-Oxygen Vertical Impact (HOVI) tests that were performed to clarify the ignition mechanisms, the explosive power of cryogenic H2/Ox mixtures under different conditions, and to elucidate the puzzling source of the initial formation of flames near the intertank section during the Challenger disaster. We carry out a physics-based analysis of general explosions scenarios for cryogenic gaseous H2/Ox mixtures and determine their realizability conditions, using the well-established simplified models from the detonation and deflagration theory. We study the features of aerosol H2/Ox mixture combustion and show, in particular, that aerosols intensify the deflagration flames and can induce detonation for any ignition mechanism. We propose a cavitation-induced mechanism of self-ignition of cryogenic H2/Ox mixtures that may be realized when gaseous H2 and Ox flows are mixed with a liquid Ox turbulent stream, as occurred in all HOVI tests. We present an overview of the HOVI tests to make conclusion on the risk of strong explosions in possible liquid rocket incidents and provide a semi-quantitative interpretation of the HOVI data based on aerosol combustion. We uncover the most dangerous situations and discuss the foreseeable risks which can arise in space missions and lead to tragic outcomes. Our analysis relates to only unconfined mixtures that are likely to arise as a result of liquid propellant space vehicle incidents.
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