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Thermal Control of the Cryogenic Upper Stage of ARIANE 5 Midlife Evolution

机译:Ariane 5中生进化的低温上阶段的热控制

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In the frame of the ESA project ARIANE 5 Midlife Evolution a new cryogenic upper stage is currently under development. The new upper stage shall be used together with the existing main stage and boosters, extending the successful family of ARIANE 5 launchers. For the first time in a European launcher, the new cryogenic upper stage is capable of LEO and GTO missions including long ballistic phases and multiple boost phases, featuring a re-ignitable engine. The resulting wide domain of functional temperatures implies the necessity of a well-defined thermal control concept in order to meet the requirements of the individual parts and the performance even for mission durations of several hours. In particular, the long ballistic phases exact the development to new strategies regarding cryogenic propellant management and insulation concepts. Thermal design and ballistic phase strategy definition are challenging aspects regarding the complex thermodynamic processes in the cryogenic tanks, taking into consideration e.g. sub-cooling of liquid oxygen or the heat transfer in micro-gravity environment. The thermal concept is outlined in selected examples. The approach, using dedicated thermal analyses and tests as well as synergies from the existing cryogenic upper stage ESC-A, is described.
机译:在ESA项目的框架中,Ariane 5中午进化目前正在开发新的低温上阶段。新的上阶段应与现有的主要舞台和助推器一起使用,扩大了Ariane 5发射器的成功家庭。在欧洲发射器中首次,新的低温上阶段能够提供Leo和GTO任务,包括长弹性阶段和多个升压阶段,具有可重新点燃的发动机。由此产生的功能温度域意味着必须定义明确定义的热控制概念,以满足各个部件的要求和即使是几个小时的任务持续时间也是如此。特别是,长弹道阶段将开发出了关于低温推进剂管理和绝缘概念的新策略。考虑到例如,热设计和弹道阶段策略定义是关于低温罐中复杂的热力学过程的具有挑战性的方面。液氧或微重力环境中的液体氧气或传热的次冷却。在选定的例子中概述了热概念。描述了使用专用的热分析和测试以及来自现有低温上级ESC-A的协同作用的方法。

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