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In long-duration, closed human habitats in space that include crop growth, one challenge that is faced while designing a candidate waste processor is the composition of solid-waste loads, which include human waste, packaging and food-processing materials, crop spoilage, and plant residues. In this work, a new modeling tool is developed to characterize crop residues and food wastes based on diet in order to support the design of solid-waste technologies for closed systems. The model predicts amounts of crop residues and food wastes due to food processing, crop harvests, and edible spoilage. To support the design of solid-waste technologies, the generation of crop residues and food wastes was characterized for a 600-day mission to Mars using integrated menu, crop, and waste models. The three sources of plant residues and food waste are identified to be food processors, crop harvests, and edible spoilage.

The on-demand production of Medical Grade Water (MGW) is a critical biomedical requirement for future long-duration exploration missions. Potentially, large volumes of MGW may be needed to treat burn victims, with lesser amounts required to reconstitute pharmacological agents for medical preparations and biological experiments, and to formulate parenteral fluids during medical treatment. Storage of MGW is an untenable means to meet this requirement, as are nominal MGW production methods, which use a complex set of processes to remove chemical contaminants, inactivate all microorganisms, and eliminate endotoxins, a toxin originating from gram-negative bacteria cell walls. An innovative microgravity compatible alternative, using a microwave-based MGW generator, is described in this paper. The MGW generator efficiently couples microwaves to a single-phase flowing stream, resulting in super-autoclave temperatures.

Several small life sciences research modules were designed to accommodate both scientific research and K-12 educational objectives on the same spaceflight mission. The K-12 educational objectives are accomplished by participating students around the globe and complimented by ground experiments conducted in their own classrooms. The spaceflight research is analyzed by students through image analysis of downlinked video and still images. The science objectives of the mission often require sample return for more detailed sample analysis on ground. Integration of new modules as part of a CGBA Science Insert (CSI) into the CGBA incubator is facilitated through standardized interfaces. Engineering challenges, trades and system architecture designs are presented for the CGBA Incubator and the CSI life sciences habitats currently on board of ISS.

Water recovery from wastewater is essential for the success of long-term missions to the Moon and Mars and human crew operations during explorations of these planets. Honeywell International and the team consisting of Thermodistillation Co. ( Kyiv, Ukraine) and NASA JSC Crew and Thermal Systems Division are developing an efficient wastewater processing subsystem that is based on centrifugal vacuum distillation. This subsystem will be tested at the NASA JSC Advanced Water Recovery Systems Development Facility. The Wastewater Processing Cascade Distillation Subsystem (CDS) utilizes an innovative and proven multi-stage thermodynamic process to produce purified water efficiently, and its rotary centrifugal design provides gas/liquid phase separation and liquid transport (pumping) under microgravity conditions.

A modular and scalable Dense Medium Plasma Water Purification Reactor was developed, which uses atmospheric-pressure electrical discharges under water to generate highly reactive species to break down organic contaminants and microorganisms. Key benefits of this novel technology include: (i) extremely high efficiency in both decontamination and disinfection; (ii) operating continuously at ambient temperature and pressure; (iii) reducing demands on the containment vessel; and (iv) requiring no consumables. This plasma based technology was developed to replace the catalytic reactor being used in the planned International Space Station Water Processor Assembly.

The paper summarizes the six years' experience gained with the ISS water management system during the missions ISS-1 through ISS-14 (since November 2, 2000 through October 31, 2006). The water supply sources, consumption structure and supply balance and balance specifics at various phases of space station operation are reviewed. The performance data of the system for water recovery from humidity condensate SRV-K and urine feed and pretreatment system SPK-U in the Russian orbital segment are presented. The key role of water recovery during space missions and the prospects of regenerative water supply of an interplanetary space station are discussed. The aim of this paper is to summarize the water supply experience and to provide recommendations for a perspective water supply integrated system based on water recovery.

Trace contaminants are produced on-orbit by human metabolic processes and equipment off-gassing. These potentially hazardous contaminants are removed by the Trace Contaminant Control Subassembly (TCCS) in the US segment of the International Space Station (ISS). The TCCS has been operating since February 2001. Analysis of on-orbit telemetry data indicated a slow increase in the TCCS system flow resistance over the five years of operation. Two of the packed beds within the TCCS were replaced to return the TCCS to its nominal operation conditions: the high temperature catalytic oxidizer and the post-sorbent bed. Results from the examination of the returned beds are presented along with a discussion about changes to bed service life.

The Carbon Dioxide Removal Assembly (CDRA) is a part of the International Space Station (ISS) Environmental Control and Life Support (ECLS) system. The CDRA provides carbon dioxide (CO2) removal from the ISS on-orbit modules. Currently, the CDRA is the secondary removal system on the ISS, with the primary system being the Russian Vozdukh. Within the CDRA are two Desiccant/Adsorbent Beds (DAB), which perform the carbon dioxide removal function. The DAB adsorbent containment approach required improvements with respect to adsorbent containment. These improvements were implemented through a redesign program and have been implemented on units on the ground and returning from orbit. This paper presents a DAB design modification implementation description, a hardware performance comparison between the unmodified and modified DAB configurations, and a description of the modified DAB hardware implementation into the on-orbit CDRA.

The use of porous media has enormous potential for thermal management and phase separation in terrestrial, micro, Lunar and Marian gravity environments. Recently, a porous media based gravity insensitive condensing heat exchanger for humidity control has been proposed and successfully demonstrated by the authors. A strongly hydrophilic porous substrate is essential for condensing and trapping water vapor from the airstreams. However, most porous media which have good thermal characteristics are poorly wetting to water. This poses a significant obstacle in the development of the porous media based condensing heat exchanger. In response to this problem, a clay based process was developed for improving the wettability of non-wetting and partially wetting porous media. It was demonstrated that poorly wetting porous graphite as well as porous stainless steel could be converted to a completely wetting porous substrate by kaolinite treatment.

The Shuttle retirement in 2010 will force the ISS program to reconsider how to supply the Station with nitrogen and oxygen for six to ten more years beyond 2010. The major options for post-Shuttle retirement resupply are resupply via transfer vehicle, the use of small Intervehicular Activity (IVA) high pressure tanks, “stockpile” enough gas to support International Space Station (ISS) through end of life, or generate the necessary gases onboard the Station. The method chosen to sustain the ISS will serve as a building block for producing new minimally dependent environmental control and life support systems for future manned missions to the Moon, Mars and beyond.

Based on a study of a Mobile Pressurized Laboratory (MPL) concept made during the European Mars Mission Architecture Study conducted for ESA, further design development of the laboratory and interior functional layout of the rover has been performed. This includes volume optimization, wheel system and geometry, interior layout and functional zoning, airlock placement and ergonomics, radiation protection, ergonomic detailing of habitation functions like sleep, kitchen, hygiene, ergonomics of work environment for driver, glove box, laboratory and storage systems and spatial flexibility and adaptability. The large wheel concept proposed in the ESA study to maximize habitable volume is further investigated. Additionally, omni-directional wheels have been introduced to the design to improve the vehicle's manoeuvrability. The inclusion of new design features led to a decision to rename the concept, MarsCruiserOne (MCO). The paper describes the design of the MCO.

In many cases science projects in extreme and remote locations require only semi-permanent installations or seasonal use. The mini module concept draws upon our experience designing the British Antarctic Survey's new station, Halley VI, to provide a simple, robust, self-supporting and lightweight facility, which can be used to provide high quality living and working accommodation in the remotest cold regions of our planet.

This paper discusses how the ideas embodied by a class of of polyhedra called floral polyhedra can be used as inspirational analogies for systematically developing new types of inflatable envelope shapes based on simple polyhedra. These envelopes have the potential to be used for a variety of Moon or Mars habitats, and extend the catalog of envelope shapes available for design work beyond the sphere, torus and cylinder. Some basic geometric properties of floral polyhedra, and how these relate to inflatable envelopes, are discussed. The paper also discusses how variations on such envelopes allow for the installation of integral flat floors made from square honeycomb panels in a manner that may reduce or eliminate the necessity for extensive external staying, or significant excavation when used as a classic surface habitat.

NASA's Digital Learning Network (DLN) reaches out to thousands of students each year through video conferencing and webcasting. As part of NASA's Strategic Plan to reach the next generation of space explorers, the DLN develops and delivers educational programs that reinforce principles in the areas of science, technology, engineering and mathematics. The DLN has created a series of live education videoconferences connecting the Desert Research and Technology Studies (RATS) field test to students across the United States. The programs are also extended to students around the world via live webcasting. The primary focus of the events is the Vision for Space Exploration. During the programs, Desert RATS engineers and scientists inform and inspire students about the importance of exploration and share the importance of the field test as it correlates with plans to return to the Moon and explore Mars. This paper describes the events that took place in September 2006.

This research analyzes potential methods to construct concrete radiation shielding for primary lunar habitats by In-Situ Resource Utilization (ISRU) before crew arrival on the Moon, considering the following key factors: Small and light-weight production plant Ability of automatic material processing and construction Large span coverage availability The concrete shielding production process and necessary facilities are shown in this paper. Moreover, mass and power budgets are estimated based on assumptions from today's research status.

In a context of global warming and our needs to reduce CO2 emissions, building envelopes will play an important role. A new imperative has been put forth to architects and engineers to develop innovative materials, components and systems, in order to make building envelopes adaptive and responsive to variable and extreme climate conditions. Envelopes serve multiple functions, from shielding the interior environment to collecting, storing and generating energy. Perhaps a more recent concern of terrestrial habitats is permeability and leakages within the building envelope. Such air tight and concealed envelopes with zero particle exchange are a necessity and already exist in regard to space capsules and habitats. This paper attempts to acknowledge existing and visionary envelope concepts and their functioning in conjunction with maintaining a favourable interior environment. It introduces several criteria and requirements of advanced façades along with interior pressurization control.

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.

AFR, Inc. is developing a multifunctional Carbon material that, in addition to excellent radiation shielding characteristics, is appropriate for certain energy storage applications. As an excellent Hydrogen gas sorbent, it increases the usable storage capacity of a gas cylinder by ∼25% at 3500 PSI and by ∼150% at 500 PSI. Our ongoing NASA Langley funded study shows that when a sorbent-filled tank is charged with hydrogen, it provides shielding superior to polyethylene against most types of ionizing particles. Even as hydrogen is consumed, the carbon and tank ensure that significant radiation shielding capability is maintained. In addition to storing hydrogen, the carbon material also displays considerable strength. In this paper, we explore some of its mechanical properties that show this material is very versatile and highly multifunctional.

An analytical prediction capability for space radiation in Low Earth Orbit (LEO), correlated with the Space Transportation System (STS) Shuttle Tissue Equivalent Proportional Counter (TEPC) measurements is presented. The model takes into consideration the energy loss straggling and chord length distribution of the detector, and is capable of predicting energy deposition fluctuations in a micro-volume by incoming ions through direct events. The charged particle transport calculations correlated with STS 56, 51, 110 and 114 flights are accomplished by using the most recent version (2005) of the Langley Research Center (LaRC) deterministic ionized particle transport code High charge (Z) and Energy TRaNsport (HZETRN) which has been extensively verified with laboratory beam measurements and available space flight data.

In this paper we investigate three numerical techniques for solving the one-dimensional straight-ahead Boltzmann equation for calculating the flux of low energy neutrons produced within a shielding material. The one-dimensional Boltzmann equation is split into a forward and backward coupled system of equations representing the production of ions of various types within a shielding material. The three numerical methods are then compared with neutron data from the Mir and ISS space station as well as Monte Carlo simulations for the production of low energy neutrons.