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Bioregenerative life support systems have the potential to reduce the need for resupply from Earth for extraterrestrial habitats. The proposed advanced life support system, developed by an international and interdisciplinary team, is an innovation combination of current and near term research and technologies. The system combines physico-chemical methods with algae, aquaculture and higher plants to purify wastes and provide consumables. A closed loop percentage of 90-95% percent is expected with additional supplies for dietary supplement and maintenance. The information gained from the development of the proposed artificial biosphere can also help to solve sustainability problems currently prevalent on Earth.

Dynamic simulation of the Lunar Outpost habitat life support was undertaken to investigate the impact of Extravehicular Activity (EVA). The preparatory static analysis and some supporting data are reported in another paper. (Jones, 2008-01-2184) Dynamic simulation is useful in understanding systems interactions, buffer needs, control approaches, and responses to failures and changes. A simulation of the Lunar outpost habitat life support was developed in MATLAB/Simulink™. The simulation is modular and reconfigurable, and the components are reusable to model other physicochemical (P/C) based recycling systems. EVA impacts the Lunar Outpost life support system design by requiring a significant increase in the direct supply mass of oxygen and water and by reducing the net mass savings of using dehydrated food. The mass cost of EVA depends on the amount and difficulty of the EVA scheduled.

NASA scientists have previously researched biomass production units for the purpose of bioregenerative life support systems (BLSS). The University of Arizona, Controlled Environment Agriculture Center (UA-CEAC) in cooperation with Sadler Machine Company (SMC) designed, constructed and assisted real-time operations of the South Pole Food Growth Chamber (SPFGC). The SPFGC is a semi-automated, hydroponic, multiple salad crop production chamber located within the U.S. National Science Foundation New Amundsen-Scott South Pole Station. Fresh vegetables are grown for the Station crew during the annual eight-month period of isolation in one of the most extreme and remote environments on Earth. An empirical mathematical model was developed from data monitored onsite and remotely by Internet and telecommunications during the winter of 2006.

The objective of the Food And Revitalization Module (FARM) project was to design a plant growth chamber module to be integrated in a bio-regenerative life support system for a permanent human Moon base. Several trade-offs have been performed in order to evaluate the possible design architectures, cultivation methods, the selection of the crop and the diet composition. Different soil-less culture methods were evaluated and issues related to light intensity, pressure, temperature, CO2 concentration and humidity control were analyzed trading-off between the different needs of the base and of the plants. From these results, different options of diet/crop combinations have been evaluated, starting from a greenhouse able to fulfill almost 100% of all the nutritional needs of the crew, scaling down reaching less than 50% of the needs considering integrations from Earth.

Future human exploration roadmaps involve the development of temporary or permanent outposts on Moon and Mars. The capability of providing astronauts with proper conditions for living and working in extraterrestrial environments is therefore a key issue for the sustainability of those roadmaps, and closed-loop Environment Control and Life Support Systems (ECLSSs) and bio-regenerative plants represent the necessary evolution of current technologies for complying with the challenging requirements imposed. This paper presents the architectural design of a terrestrial plant to be exploited to test and validate air and water management technologies for a biological life support system in a closed environment. The plant includes a crew area and a plant growth area. These two spaces can be considered as either a unique volume or two separated environments with reduced contact, e.g. for plant harvesting or other up-keeping activities.

The Node 2 has been launched by NSTS-120 flight on October 23rd 2007. The Thermal Control has been identified as one of the critical systems for which the off site support (in Torino) has been mandatory required by NASA/ESA to the thermal specialists that directly followed the design and manufacturing of the thermal hardware. A team of specialists has been trained to adequately support the mission from Torino TAS-I plant for both active and passive thermal aspects. The support consisted into troubleshooting of unexpected problems occurred during the mission for which a fast thermal assessment was necessary, provision of thermal predictions to support changes in the activation procedures, processing of telemetry data for mathematical models correlation. This paper describes the thermal issues encountered during the provided mission support and how they have been solved.

The Bioregenerative Life Support program CAB (Controllo Ambientale Biorigenerativo) is a key element of the Italian Space Agency (ASI) Medicine & Biotechnology scientific program, set forth in the ASI Activity Plan 2006-2008 [01], [02], [03]. The CAB program team performed a one-year feasibility study of a controlled biological life support system (BLSS), allowing the regeneration of resources and the production of food for life support in long duration missions, under the prime contractorship of Thales Alenia Space - Italia, defining: State of art in the field Functional and technical requirements for the BLSS Functional architecture and preliminary sizing of a BLSS for planetary surface Development plan with associated scientific activities and technological demonstration.

A unique combination of manikin measurement and mathematical simulation was used to evaluate the thermal performance of two prototype modular boot systems intended to provide protection across a range of environmental conditions. Measured thermal insulations ranged from 0.91 to 1.85 clo (1 clo = 0.155 m2°C/W), and predicted endurance times (e.g. time for the toe temperature to reach 5°C) ranged from 56 to 169 min at -20°C, from 40 to 102 min at -30°C, and from 27 to 62 min at -50°C. Both systems provided appropriate thermal protection in a wide range of environmental conditions. The approach is time-saving and cost-effective, and is useful to understand the physical characteristics and thermal protection afforded by complex modular footwear, and better meet the needs of the customer.

In reaction to the prevalent space design paradigm, we would like to explore a combination of transparent polymer laminate membranes and high tensile strength webbing as the envelope of future transparent space habitats. Further study reveals fascinating possibilities in the use a tensegrity structures as the exo- or endoskeleton for such envelopes. In the following work we look at thin shell transparent structures as possible observation modules in space habitats or as the domed component for a colony on the moon or another planet. For such structures the internal pressure is not only a load but their shaping force as well, i.e. they are de-facto inflatables. We investigate their feasibility based on available technologies, such as lobed balloons. Other sources of technological transfer are ETFE (ethylene-tetrafluoroethylene copolymer) cushions, safety laminate foils, and hi-tech laminate sails design.

NASA's vision for Space Exploration includes a long term human presence on the surface of the moon and missions to Mars. In support of these missions, habitation structures will be developed to support operations in these challenging gravitational environments and maximize safety and comfort to the crew. One class of structures that is under study is expandable structures because of their mass and stowed volume efficiency. These structures follow the natural paradigm of exploration that has been observed for centuries. An expandable technology demonstration unit has been constructed and is being tested in the lunar analog environment of Antarctica, over several years. The habitat has yielded test data regarding transport and deployment, sensor integration, reconfigurability, habitability, performance in harsh environments, radiation shielding and dust mitigation. Data from these tests is being used by NASA to support lunar architecture studies.

Europe has embarked on a new programme of space exploration involving the development of rover, lander and probe missions to visit planets, moons and near Earth objects (NEOs) throughout the Solar System. Rovers and landers will require testing under simulated planetary, and NEO conditions to ensure their ability to land on and traverse the alien surfaces. ESA has begun work on a building project that will provide an enclosed and controlled environment for testing rover and lander functions such as landing, mobility, navigation and soil sampling. The facility will first support the European ExoMars mission due for launch in 2013. This mission will deliver a robotic rover to the Martian surface. This paper, the first of several on the project, gives an overview of its design configuration and construction phasing. Future papers will cover its applications and operations.

This paper presents a case for supporting the architecting of a conceptual system and its associated human activity with an analytical model. The human activity is treated as a peer to the system's operation using Object Process Methodology (OPM) and uses manned Lunar operations as an example. There is a brief discussion of architecture, architecting, and systems architecture, to set the context for the terminology used to present the modeling context. This early stage analytical modeling in a systems conceptual definition provides a comprehensive means for evaluation of the design for functions it is required to support. The models also provide a consistent basis for the more complex models used later in the systems implementation. Systems modeling is an accepted practice for describing the complex interactions in and among systems, however, the modeling of human activity in conjunction with systems is less well developed.

In light of the renewed international interest in lunar exploration, including plans for setting up a permanent human outpost on the Moon, the need for next generation earth-based human space mission simulators has become inevitable and urgent. These simulators have been shown to be of great value for medical, physiological, psychological, biological and exobiological research, and for subsystem test and development, particularly closed-loop life support systems. The paper presents a summary of a survey of past, present and future human space mission simulators. In 2006, the Vienna based company Liquifer Systems Group (LSG) conducted an in-depth survey, for a European Space Agency (ESA) commissioned Phase-A contract involving a Design Study for a Facility for Integrated Planetary Exploration Simulation (FIPES).

Fine water mist has become a commercial technology for fire suppression in multiple applications. With funding from NASA, ADA Technologies, Inc. (ADA) is developing a handheld fine water mist fire extinguisher for use on manned spacecraft and in future planetary habitats. This design employs only water and nitrogen as suppression agents to allow local refill and reuse. The prototype design incorporates features to generate a uniform fine water mist regardless of the direction of the gravitational vector or lack of gravity altogether. The system has been proven to extinguish open fires and hidden fire scenarios in tests conducted at the Colorado School of Mines (CSM). This design can be deployed as a portable extinguisher or as an automated system for local fire protection in instrument racks or storage spaces. Continued development will result in prototype hardware suitable for use on future manned spacecraft.

During Lunar missions, NASA's new Orion Crew Exploration Vehicle (CEV) may benefit from mass savings and increased reliability by the use of a passive, capillary-driven Static Phase Separator (SPS) for urine collection, containment, and disposal in place of a rotary-fan separator and wastewater storage tank. The design of a capillary separator addresses unique challenges for microgravity fluid management for liquids with a wide range of possible contact angles and high air-to-liquid flow ratio. This paper presents the iterative process leading to a successful test in a reduced gravity aircraft of the SPS concept. Using appropriately scaled test conditions, the resulting prototype allows for a range of wetting properties with complete separation of liquid from gas.

The Moon Mineralogy Mapper (M3) instrument is scheduled for launch in 2008 onboard the Indian Chandrayaan-1 spacecraft. The mission is managed by the Indian Space Research Organization (ISRO) in Bangalore, India and is India's first flight to the Moon. M3 is being developed for NASA by the Jet Propulsion Laboratory under the Discovery Program Office managed by Marshall Space Flight Center. M3 is a state-of-the-art instrument designed to fulfill science and exploratory objectives. Its primary science objective is to characterize and map the lunar surface composition to better understand its geologic evolution. M3's primary exploration goal is to assess and map the Moon mineral resources at high spatial resolution to support future targeted missions. M3 is a cryogenic near infrared imaging spectrometer with spectral coverage of 0.4 to 3.0 μm at 10 nm resolution with high signal to noise ratio, spatial and spectral uniformity.

The Orbiting Carbon Observatory (OCO) instrument is scheduled for launch onboard an Orbital Sciences Corporation LEOStar-2 architecture spacecraft in December 2008. The instrument will collect data to identify CO2 sources and sinks and quantify their seasonal variability. OCO observations will permit the collection of spatially resolved, high resolution spectroscopic observations of CO2 and O2 absorption in reflected sunlight over both continents and oceans. OCO has three bore-sighted, high resolution, grating spectrometers which share a common telescope with similar optics and electronics. A 0.765 μm channel will be used for O2 observations, while the weak and strong CO2 bands will be observed with 1.61 μm and 2.06 μm channels, respectively. The OCO spacecraft circular polar orbit will be sun-synchronous with an inclination of 98.2 degrees, mean altitude of 705 km and 98.9 minute orbit period.

The SMOS satellite is a polar-orbit sun-synchronous Earth observation ESA mission, whose science objectives are to: globally monitor surface soil moisture over land surfaces, globally monitor surface salinity over the oceans, characterise ice and snow covered surfaces The SMOS satellite is composed of the Proteus platform and the Payload module/MIRAS instrument. This paper is dedicated to the thermal design and testing of SMOS payload module (PLM). The PLM thermal design is passive, maximizes the use of proven materials and processes and is supported by heaters. The major drivers for the design are the limitation in heater power allocation and the stringent temperature requirements. The verification of the PLM thermal design is based on a Thermal Balance (TB) testing of a Structural Thermal Model (STM), followed by a TB/TV test on the ProtoFlight Model (PFM). A Thermal Vacuum (TV) test has also been performed for the complete spacecraft.

GOCE (the Gravity Field and Steady State Ocean Circulation Explorer) is the first Earth Explorer Core Mission of the Earth Observation Envelope Program of the European Space Agency (ESA). The Satellite is planned to be launched in June 2008 on a Rockot launcher into a near-circular sun-synchronous orbit for Earth's gravity field measurements. The objective of the mission is to produce high-accuracy, high-resolution, global measurements of the Earth's gravity by satellite, leading to improved gravity field and geoid models for use in a wide range of applications (geodesy, solid-Earth physics, oceanography, climate, ice topography). In particular, the goal is to produce a map of the gravity anomaly field with an accuracy better than 1mGal (1 mGal=10-5 m s-2), and of the geoid height with accuracy better than 1 cm, all over the Earth's surface with a resolution at sea level of at least 100 km.

Final preparation and configuration of the Columbus module at the Kennedy Space Center (KSC) required the performance of system level tests with the Active Thermal Control System (ATCS). These tests represented the very last system level activities having been concluded on the Columbus module before handover to NASA for space shuttle integration. Those very last tests, performed with the ATCS comprised the final ATCS Leakage Test, the final calibration and adjustment of the Water Flow Selection Valves (WFSV) and Water On/Off Valves (WOOV) as well as a sophisticated ATCS Residual Air Removal test. The above listed tests have been successfully performed and test data evaluated for verification closeout as well as input delivery for operational Flight Rules and Procedures. Some of the above mentioned tests have been performed the first time hence, a succeeding lessons learned collection followed in order to improve the perspectives of future tests.