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首页> 外文期刊>International journal of design engineering >Illustrative NASA Low Earth Orbit spacecraft subsystems design-for-demise trade-offs, analyses and limitations
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Illustrative NASA Low Earth Orbit spacecraft subsystems design-for-demise trade-offs, analyses and limitations

机译：说明性的NASA低地球轨道航天器子系统为消亡设计的权衡，分析和限制

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An uncontrolled re-entry mission that completely ablates would comply with stipulated NASA Earth atmosphere re-entry requirements without requiring an integrated provision for controlled re-entry. Consequently, such a mission design implies a relatively simpler and cheaper option. Moreover, mission unavailability risk due to a controlled re-entry subsystem failure is essentially eliminated, which would improve mission on-orbit reliability and robustness. We propose a generic critical parts identification plan that is followed by methods of designing spacecraft parts for demise. To demonstrate the exhaustive analyses and design of spacecraft parts for demise, we consider representative parts from the propulsion and power subsystems - propellant tank and batteries respectively. On-orbit performance and practical design threshold considered provide intuition into the design-for-demise limitations of investigated parts. Further, the tank proposed here is not only demisable, but is also seen to exhibit superior on-orbit performance compared to a similar monolithic titanium tank.
机译：完全消融的不受控制的重返飞行任务将符合NASA规定的地球大气再入要求，而无需为受控的重返飞行提供统一的规定。因此，这种任务设计意味着相对简单和便宜的选择。此外，由于受控的重入子系统故障而导致的任务不可用性风险已基本消除，这将提高任务在轨可靠性和鲁棒性。我们提出了一个通用的关键零件识别计划，然后是设计用于消亡的航天器零件的方法。为了展示详尽的分析和航天器零件消亡设计，我们考虑了推进和动力子系统中的代表性零件-分别是推进剂箱和电池。所考虑的在轨性能和实际设计阈值提供了直觉了解被调查零件的消亡设计限制。此外，与类似的整体式钛制储罐相比，这里提出的储罐不仅是可丢弃的，而且还具有更好的在轨性能。

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