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A high altitude space simulation facility to study exhaust plume interactions and contamination

机译：一种高空空间模拟设施，用于研究排气羽流相互作用和污染

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Interest in realistic simulation of the space environment as applied to the study of spacecraft contamination and thruster plumes has led to the development of the CHAFF-4 facility. CHAFF-4 uses a multi-fin cryogenically cooled array (-20K) that completely envelops the interior of the chamber providing an available condensing surface area of 590 m sup 2. The geometry of the array capitalizes on the face that both neutral and ion species from spacercraft propulsion systems predominantly undergo diffuse reflections when impacting at angles normal to the surfaces they encounter. Preliminary figures of merit for the equivalent altitude possible for various propulsion systems vary between 150-350 km (depending on thruster type). The effective pumping speed is predicted to be between 3x10 sup 7 and 1x10 sup 8 liters/sec. The facility is expected to accommodate thruster power levels up to 3500W wighout the use o supplementary liquid helium, although infrastructure permitting its use is available. Ddvelopmental considerations and design issues are discussed in view of basic principles of plume testing and contamination, in order to ensure the integrity of phenomena that are observed in the facility. Provisions for the simulation of high-speed LEO flow environments have been incorporated in the design, and the corresponding pumping requirements are well within the capabilities of CHAFF-4.
机译：用于研究航天器污染和推进器羽流的对空间环境进行逼真的模拟的兴趣促使CHAFF-4设施的发展。 CHAFF-4使用多翅片低温冷却阵列（-20K），该阵列完全包围腔室内部，提供590 m sup 2的可用冷凝表面积。阵列的几何形状充分利用了中性和离子形式的表面当以垂直于它们所遇到的表面的角度撞击时，来自间隔飞行器推进系统的辐射主要发生漫反射。各种推进系统可能的等效高度的初步品质因数在150-350 km之间变化（取决于推进器类型）。预计有效抽速在3x10 sup 7和1x10 sup 8升/秒之间。尽管可以使用基础设施，但在不使用补充液氦的情况下，该设施预计可容纳高达3500W的推进器功率。为了确保在工厂中观察到的现象的完整性，讨论了开发方面的考虑因素和设计问题，并考虑了羽流测试和污染的基本原理。设计中纳入了模拟高速LEO流动环境的规定，并且相应的泵送要求完全在CHAFF-4的能力范围内。

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