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Challenging Pneumatic requirements for acoustic testing of the second stage for the new delta III rocket

机译：新三角洲III火箭第二阶段声学测试的气动要求极具挑战性

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The paper describes the unique pneumatic test requirements for the acoustic and shock separation testing of the Second Stage for the new Delta III Rocket at the Goddard Space Flight Center in Greenbelt, Maryland. The testing was conducted in the 45,000 ft3 (25-feet wide by 30-feet deep by 50-foot high) Acoustic Facility. The acoustic testing required that the liquid oxygen (LOX) and liquid hydrogen (LH sub 2) tanks be filled with enough liquid nitrogen (LN sub 2) to simulate launch fuel masses during testing. The challenge for this test dealt with designing, procuring, and fabricating the pneumatic supply systems for quick assembly while maintaining the purity requirements and minmizing costs. The pneumatic systems were designed to fill and drain the both LOX and LH sub 2 tanks as well as to operate the fill/drain and vent valves for each of the tanks. The test criteria for the pneumatic sub-systems consisted of function, cleanliness, availability, and cost. The first criteria, function, required the tanks to be filled and drained in an efficient manner while preventing them from seeing pressures greater than 9 psig which would add a pressure cycle to the tank. An LN sub 2 tanker, borrowed from another NASA facility, served as the pre-cool and drain tanker. Pre-cooling the tanks allowed for more efficient and cost effective transfer from the LN sub 2 delivery tankers. Helium gas, supplied from a high purity tube trailer, was used to pressurize the vapor space above the LN sub 2 pushing it into the drain tanker. The tube trailer also supplied high pressure helium to the vehicle for valve control and component purges. Cleanliness was maintained by proper component selection, end-use particle filtration, and any on-site cleaning determined necessary by testing. In order to meet the availability/cost juggling act, products designed for LOX delivery systems were procured to ensure system compatibility while off the shelf valves and tubing designed for the semiconductor industry were procured for the gas systems.
机译：本文介绍了在马里兰州格林贝尔特的戈达德太空飞行中心对新型Delta III火箭第二阶段进行声学和冲击分离测试的独特气动测试要求。该测试是在45,000平方英尺（25英尺宽，30英尺深，50英尺高的声学设备）上进行的。声学测试需要在液氧（LOX）和液氢（LH sub 2）储罐中填充足够的液氮（LN sub 2），以模拟测试期间的发射燃料质量。该测试面临的挑战是如何设计，采购和制造用于快速组装的气动供应系统，同时又要保持纯度要求并最小化成本。气动系统设计用于填充和排放LOX和LH sub 2油箱，以及操作每个油箱的填充/排放和排气阀。气动子系统的测试标准包括功能，清洁度，可用性和成本。第一个标准是功能，要求以有效的方式填充和排放储罐，同时防止储罐承受大于9 psig的压力，这会增加储罐的压力循环。从美国国家航空航天局（NASA）的另一处设施借来的LN Sub 2油轮用作预冷却和排水油轮。对储罐进行预冷可以从LN sub 2输送油罐进行更高效，更具成本效益的转移。由高纯度管式拖车提供的氦气用于加压LN sub 2上方的蒸汽空间，将其推入排水槽。管式拖车还向车辆提供了高压氦气，用于阀门控制和零件清洗。通过适当的组件选择，最终用途的颗粒过滤以及测试确定的必要的现场清洁，可以保持清洁度。为了满足可用性/成本方面的要求，采购了为LOX输送系统设计的产品，以确保系统的兼容性，同时为气体系统采购了为半导体行业设计的现成的阀门和管材。

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