Cryogenic Orbital Testbed (CRYOTE) development status

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• 作者：M. Gravlee^a ; ^{mari.gravlee@ulalaunch.com} ; B. Kutter^a ; C. McLean^b ; J. Marquardt^b
• 关键词：Cryogenic fluid management ; CFM ; Flight demonstration ; Multi-layer insulation ; Cryogenic propulsion stage ; Propellant management device ; Liquid acquisition device ; Thermodynamic vent system ; Vapor cooling ; Zero boiloff ; Cryogenic propellant storage and tr
• 刊名：Cryogenics
• 出版年：2012
• 期刊代码：45_00112275
• 类别：et
• 出版时间：April-June, 2012
• 卷：52
• 期：4-6
• 页码：231-235
• 文件大小：911 K

摘要

High-performance space travel is enabled with propellants having a high specific impulse, and the highest specific impulse can be produced with hydrogen. The Cryogenic Orbital Testbed (CRYOTE) provides an in-space environment where the unique properties and fluid flow of hydrogen can be demonstrated in micro- or zero-gravity. With partnerships across industry and NASA, CRYOTE has developed a detailed concept of an in-flight core system (that can accommodate a variety of experiments). Development has included launch vehicle interface development for transfer of residual Liquid Hydrogen (LH2) from the launch vehicle to a development tank and an in-depth thermal analysis considering the orbital thermal environment and heat loads imparted on the thermal system.

This paper will describe the non-proprietary development to date, outline lessons learned in the development, and detail the plan moving forward with the CRYOTE project.