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 (+/- 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个新的对接和停泊系统，以支持未来的太空勘探任务到低地轨道，月球和火星。这种称为低冲击对接系统的机制，旨在连接加压空间车辆和结构。 NASA Glenn Research Center在开发新型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。基线系统被设计为具有完全雌雄同体的配合界面，从而当两个系统配合时需要密封密封配置。这些密封件直径约为147厘米（58英寸）。 NASA Glenn设计并制作了一种新的测试夹具，该夹具将用于评估模拟热，真空和接合条件下的候选全尺度密封件的泄漏。这包括在密封密封或密封板配置下进行测试，从-50到50°C（-58至122°F），运行和飞行前的结账压力梯度以及车辆未对准（+/- 0.381厘米（0.150英寸））和拉伸（高达0.10厘米（0.040英寸））条件。本文介绍了用于克服一些设计挑战的测试台和技术的主要设计特征。
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