NASA is developing a new docking and berthing system to support future space exploration missions to low-Earth orbit, the Moon, and Mars. This mechanism, called the Low Impact Docking System, is designed to connect pressurized space vehicles and structures. NASA Glenn Research Center is playing a key role in developing advanced technology for the main interface seal for this new docking system. The baseline system is designed to have a fully androgynous mating interface, thereby requiring a seal-on-seal configuration when two systems mate. These seals will be approximately 147 cm (58 in.) in diameter. NASA Glenn has designed and fabricated a new test fixture which will be used to evaluate the leakage of candidate full-scale seals under simulated thermal, vacuum, and engagement conditions. This includes testing under seal-on-seal or seal-on-plate configurations, temperatures from -50 to 50 C (-58 to 122 F), operational and pre-flight checkout pressure gradients, and vehicle misalignment (plus or minus 0.381 cm (0.150 in.)) and gapping (up to 0.10 cm (0.040 in.)) conditions. This paper describes the main design features of the test rig and techniques used to overcome some of the design challenges.
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机译:美国宇航局正在开发一种新的对接和停泊系统,以支持未来对低地球轨道,月球和火星的太空探索任务。这种称为“低冲击对接系统”的机制旨在连接增压航天器和结构。美国宇航局格伦研究中心在开发用于这种新对接系统的主界面密封件的先进技术方面发挥着关键作用。基准系统设计为具有完全雌雄同体的配合界面,因此在两个系统配合时需要密封密封结构。这些密封件的直径约为147厘米(58英寸)。 NASA Glenn设计并制造了一种新的测试夹具,该夹具将用于评估在模拟的热,真空和接合条件下候选全尺寸密封件的泄漏情况。这包括在密封盖密封或板载密封配置,-50至50 C(-58至122 F)的温度,运行和飞行前检查压力梯度以及车辆未对准(正负0.381厘米)下进行的测试。 (0.150英寸))和间隙(最大0.10厘米(0.040英寸))条件。本文介绍了测试装置的主要设计特征以及用于克服某些设计挑战的技术。
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