Theory and Application of the Equivalent System Mass Metric

A review towards the design of extraterrestrial structures: From regolith to human outposts

The currently known resources on Mars are massive, including extensive quantities of water and carbon dioxide and therefore carbon, hydrogen and oxygen for life support, fuels and plastics and much else. The regolith is replete with all manner of minerals. In Situ Resource Utilization (ISRU) applicable frontier technologies include robotics, machine intelligence, nanotechnology, synthetic biology, 3-D printing/additive manufacturing and autonomy. These technologies combined with the vast natural resources should enable serious, pre- and post-human arrival ISRU to greatly increase reliability and safety and reduce cost for human colonization of Mars. Various system-level transportation concepts employing Mars produced fuel would enable Mars resources to evolve into a primary center of trade for the inner solar system for eventually nearly everything required for space faring and colonization. Mars resources and their exploitation via extensive ISRU are the key to a viable, safe and affordable, human presence beyond Earth. The purpose of this paper is four-fold: 1) to highlight the latest discoveries of water, minerals, and other materials on Mars that reshape our thinking about the value and capabilities of Mars ISRU; 2) to summarize the previous literature on Mars ISRU processes, equipment, and approaches; 3) to point to frontier ISRU technologies and approaches that can lead to safe and affordable human missions to Mars; and 4) to suggest an implementation strategy whereby the ISRU elements are phased into the mission campaign over time to enable a sustainable and increasing human presence on Mars.

/pdf/frontier-in-situ-resource-utilization-for-enabling-sustained-2q0lq0oyio.pdf

Frontier In-Situ Resource Utilization for Enabling Sustained Human Presence on Mars

The International Space Station (ISS) United States Operational Segment (USOS) currently provides a Temporary Sleep Station (TeSS) as crew quarters for one crewmember in the Laboratory Module. The Russian Segment provides permanent crew quarters (Kayutas) for two crewmembers in the Service Module. The TeSS provides limited electrical, communication, and ventilation functionality. A new permanent rack sized USOS ISS Crew Quarters (CQ) is being developed. Up to four CQs can be installed into the Node 2 element to increase the ISS crewmember size to six. The new CQs will provide private crewmember space with enhanced acoustic noise mitigation, integrated radiation reduction material, controllable airflow, communication equipment, redundant electrical systems, and redundant caution and warning systems. The rack sized CQ is a system with multiple crewmember restraints, adjustable lighting, controllable ventilation, and interfaces that allow each crewmember to personalize their CQ workspace. Providing an acoustically quiet and visually isolated environment, while ensuring crewmember safety, is critical for obtaining crewmember rest and comfort to enable long term crewmember performance. The numerous human factor, engineering, and program considerations during the concept, design, and prototyping are outlined in the paper.

/pdf/international-space-station-usos-crew-quarters-development-4rdhgk4wgi.pdf

International Space Station USOS Crew Quarters Development

In space habitat construction, the application of kit-of-parts concepts and construction robotics is of particular interest, due to flexibility, compactness of transport, and the ability to erect structures in harsh, unsafe environments autonomously. In this paper, Kit-of-parts Theory and automated construction principles are discussed in depth, and some attributes and specifications of a conceptual integrated spacebased construction system are delineated. Special attention will be given to the discussion of the optimum scale of components, joint design, parametric pressure vessels, parametric kinematic mechanisms, and in-situ assembly / disassembly. The paper will conclude with some thoughts on the development of sustainable, closed construction systems that rely on in-situ materials and manufacturing.

The ultimate construction toy: applying kit-of-parts theory to habitat and vehicle design

The Advanced Inflatable Airlock (AIA) System is currently being developed for the Space Launch Initiative (SLI). The objective of the AIA System is to greatly reduce the cost associated with performing extravehicular activity (EVA) from manned launch vehicles by reducing launch weight and volume from previous hard airlock systems such as the Space Shuttle and Space Station airlocks. The AIA System builds upon previous technology from the TransHab inflatable structures project, from Space Shuttle and Space Station Airlock systems, and from terrestrial flexible structures projects. The AIA system design is required to be versatile and capable of modification to fit any platform or vehicle needing EVA capability. During the basic phase of the program the AIA conceptual design and key features were developed to help meet the SLI program goals of reduced cost and program risk. Option 1 focused on development of key design features and testing of breadboard units to demonstrate effectiveness of the design solutions. This paper discusses the progress made during option 1 of the AIA program. BACKGROUND

/pdf/breadboard-development-of-the-advanced-inflatable-airlock-41fyaaafe0.pdf

Breadboard Development of the Advanced Inflatable Airlock System for EVA

This paper will summarize the study that was conducted under the auspices of the National Aeronautics and Space Administration (NASA), lead by Johnson Space Center s Engineering Directorate in support of the Lunar Lander Preparatory Study (LLPS) as sponsored by the Constellation Program Office (CxPO), Advanced Projects Office (APO). The lunar lander conceptual design and analysis is intended to provide an understanding of requirements for human space exploration of the Moon using the Advanced Projects Office Pre-Lander Project Office selected "HabiTank" Lander concept. In addition, these analyses help identify system "drivers," or significant sources of cost, performance, risk, and schedule variation along with areas needing technology development. Recommendations, results, and conclusions in this paper do not reflect NASA policy or programmatic decisions. This paper is an executive summary of this study.

The Lunar Lander ‘HabiTank’ Concept

ISS TransHab: Architecture Description

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Breadboard Development of the Advanced Inflatable Airlock System for EVA

The Lunar Lander ‘HabiTank’ Concept

ISS TransHab: Architecture Description