Demonstration of charge-hold-vent (CHV) and no-vent-fill (NVF) in a simulated propellent storage tank during tank-to-tank cryogen transfer in microgravity.

IF 4.4 1区 物理与天体物理 Q1 MULTIDISCIPLINARY SCIENCES
J N Chung, Jun Dong, Hao Wang, Bo Han Huang, Jason Hartwig
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Abstract

The space exploration from a low earth orbit to a high earth orbit, then to Moon, Mars, and possibly asteroids and moons of other planets is one of the biggest challenges for scientists and engineers for the new millennium. The enabling of in-space cryogenic rocket engines and the Lower-Earth-Orbit (LEO) cryogenic fuel depots for these future manned and robotic space exploration missions begins with the technology development of advanced cryogenic thermal-fluid management systems for the propellant transfer line and storage tank system. One of the key thermal-fluid management operations is the chilldown and filling of the propellant storage tank in space. As a result, highly energy efficient, breakthrough concepts for quenching heat transfer to conserve and minimize the cryogen consumption during chilldown have become the focus of engineering research and development, especially for the deep-space mission to Mars. In this paper, we introduce such thermal transport concepts and demonstrate their feasibilities in space for cryogenic propellant storage tank chilldown and filling in a simulated space microgravity condition on board an aircraft flying a parabolic trajectory. In order to maximize the storage tank chilldown thermal efficiency for the least amount of required cryogen consumption, the breakthrough quenching heat transfer concepts developed include the combination of charge-hold-vent (CHV) and no-vent-hold (NVF). The completed flight experiments successfully demonstrated the feasibility of the concepts and discovered that spray cooling combined with hold and vent is more efficient than the pure spray cooling for storage tank chilldown in microgravity. In microgravity, the data shows that the CHV thermal efficiency can reach 39.5%. The CHV efficiency in microgravity is 6.9% lower than that in terrestrial gravity. We also found that pulsing the spray can increase CHV efficiency by 6.1% in microgravity.

在微重力条件下,模拟推进剂贮箱在贮箱到贮箱的低温传送过程中,演示充注-保持-排气(CHV)和无排气-充注(NVF)。
从低地球轨道到高地球轨道,再到月球、火星,甚至小行星和其他行星的卫星的空间探索,是科学家和工程师在新千年面临的最大挑战之一。要为这些未来的载人和机器人太空探索任务提供空间低温火箭发动机和低地轨道(LEO)低温燃料库,首先要为推进剂传输线和贮箱系统开发先进的低温热流体管理系统。热流体管理的关键操作之一是推进剂贮箱在太空中的冷却和填充。因此,高效节能的突破性淬火传热概念已成为工程研发的重点,尤其是针对火星深空任务。在本文中,我们介绍了这种热传输概念,并演示了在抛物线轨迹飞行器上模拟太空微重力条件下,低温推进剂贮箱冷却和填充在太空中的可行性。为了以最少的所需低温消耗最大限度地提高贮箱冷却热效率,所开发的突破性淬火传热概念包括装料-保持-排气(CHV)和无排气-保持(NVF)的组合。已完成的飞行实验成功证明了这些概念的可行性,并发现在微重力条件下,喷淋冷却与保持和排气相结合比纯喷淋冷却更有效。数据显示,在微重力状态下,CHV 的热效率可达 39.5%。微重力下的 CHV 效率比地面重力下低 6.9%。我们还发现,在微重力条件下,脉冲喷射可使 CHV 效率提高 6.1%。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
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来源期刊
npj Microgravity
npj Microgravity Physics and Astronomy-Physics and Astronomy (miscellaneous)
CiteScore
7.30
自引率
7.80%
发文量
50
审稿时长
9 weeks
期刊介绍: A new open access, online-only, multidisciplinary research journal, npj Microgravity is dedicated to publishing the most important scientific advances in the life sciences, physical sciences, and engineering fields that are facilitated by spaceflight and analogue platforms.
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