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Rationale for using inflatable structures for habitable surface elements and associated with them limitations

机译：可居住表面元素使用充气结构的原理及其相关限制

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Selection of planetary habitat design, envelop type and overall dimensions must comply with a range of launch, orbital assembly and transfer, landing and surface mobility/deployment constraints. Key among these are launch vehicle payload envelope volume and mass limitations, availability of interfaces to allow transport and landing vehicles rendezvous, footprint and center-of-gravity placements for stable landing and surface relocations, and EVA access determined by the module interior arrangements and entrance levels. This paper discusses rationale for expandable structures applications in relation to these constraints and specific mission's goals and objectives. It examines some key aspects that form design criteria for selection of external and internal forms of habitable structures. Such design criteria are proposed to compare and evaluate possible alternatives for expandable space structures and architectures studies: orbital platform-Gateway habitats and lunar surface mission planning, first outpost configurations and expansions for permanent settlement establishments. In addition, it provides bases for "consolidated assessments" to test preliminary ideas and assumptions and guide documentation of lessons learned. Examples include previous and current space architecture projects conducted at the UH space architecture center (SICSA).
机译：行星栖息地设计、外壳类型和外形尺寸的选择必须符合一系列发射、轨道组装和转移、着陆和表面机动/部署限制。其中的关键是运载火箭有效载荷包线体积和质量限制、允许运输和着陆车辆会合的接口可用性、稳定着陆和表面重新定位的足迹和重心位置，以及由舱内布置和入口标高确定的EVA通道。本文讨论了可扩展结构应用的基本原理，以及这些约束条件和特定任务的目标。它研究了构成可居住结构外部和内部形式选择的设计标准的一些关键方面。提出此类设计标准是为了比较和评估可扩展空间结构和建筑研究的可能替代方案：轨道平台入口栖息地和月球表面任务规划、第一前哨站配置和永久定居设施扩建。此外，它还为“综合评估”提供了基础，以测试初步想法和假设，并指导经验教训的记录。例子包括在UH太空建筑中心（SICSA）进行的以前和现在的太空建筑项目。

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