International Conference on Environmental Systems

Permanent URI for this collectionhttps://hdl.handle.net/2346/58495

The International Conference on Environmental Systems, or ICES (known prior to 1990 as the Intersociety Conference on Environmental Systems), is an annual technical conference focusing on human spaceflight technology and space human factors. Session topics include: Environmental Control and Life Support Systems (ECLSS), thermal control, life sciences, extra-vehicular activity (EVA) systems (including space suit design and human-robot interaction), space architecture, and mission planning for exploration. The conference has taken place annually since 1971.

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Poly-Culture Food Production and Air Revitalization Mass and Energy Balances Measured in a Semi-Closed Lunar Greenhouse Prototype (LGH)
(44th International Conference on Environmental Systems, 2014-07-13) Patterson, R. Lane; Giacomelli, Gene A.; Hernandez, Erica; Yanes, Marianna; Jensen, Tyler
Bioregenerative life-support (BLSS) studies were completed at the University of Arizona Controlled Environment Agriculture Center (UA-CEAC) with support by the Arizona NASA Ralph Steckler Phase II Space Grant. In cooperation with Sadler Machine Co. (USA) and international Italian collaborators, Thales Alenia Space Italia (TAS-I) and Aero-Sekur, SpA, and AGC Green-Tech Co. (Japan), a lightweight flexible cable culture hydroponic plant production system incorporated with an automated 23 m3, sealed, collapsible plant growth chamber was used to demonstrate polyculture production of food crops and air revitalization in a semi-closed Lunar Greenhouse Prototype (LGH). Mass and energy balances were measured and the flows of input resources (i.e. water, carbon dioxide, dry fertilizer salts, labor, electricity and heat) and output production (i.e. food, water condensate, oxygen and heat) were quantified for the purpose of demonstrating life support capability utilizing biological processes under controlled environments for human space applications.
Thermal Design of the Solar Orbiter SPICE instrument
(44th International Conference on Environmental Systems, 2014-07-13) Shaughnessy, Bryan M.; Cornaby, James
The European Space Agency Solar Orbiter spacecraft is planned for launch in July 2017. It is targeted for an elliptical orbit about the Sun, with a minimum perihelion of 0.284 Astronomical Units (AU). The thermal challenge is therefore management of the extreme (~17 kW/m2) solar heat input at perihelion. Solar Orbiter is designed to identify the origins and causes of the solar wind, the heliospheric magnetic field, solar energetic particles, the transient interplanetary disturbances, and the Sun's magnetic field itself. The Spectral Imaging of the Coronal Environment (SPICE) instrument is one of six remote sensing instruments on the spacecraft. It is a high resolution imaging spectrometer operating at ultraviolet wavelengths. The driving requirement for the SPICE thermal design is to manage the solar load incident through the aperture in the spacecraft heat-shield. At a perihelion this solar load is 44 W. However, the thermal control system must also be compliant during periods with little or no solar loading and with the conditions during the Earth and Venus gravity assist maneuvers required for orbit adjustment. A key feature of the thermal design is a selectively transparent primary mirror that reflects the science beam but allows much of the solar energy to be transmitted and then reflected to space. Currently we are in the detailed definition phase (C) of the project. This paper describes the design and analysis that has been undertaken to define the thermal control system.
3D Modeling of Human Thermal Interaction in Complex Environments using the Wissler Human Thermal Model
(44th International Conference on Environmental Systems, 2014-07-13) Cognata, Thomas; Durrant, Tom
Models for human thermal evaluation in extreme environments have played a key role in life support, suit, and crewed vehicle development at NASA for many decades. These models, which include the 41-Node Metabolic Man and Wissler models, among others, have proved excellent tools in predicting survivability without performing costly testing in extreme environments. These models have been limited, however, to predictions in simple 1-D environments rather than the highly directional heat load environments experienced in space exploration. A three dimensional geometric interface to the NASA version of the Wissler human thermal model has been developed in Thermal Desktop to better support exploration suit design. This tool is employed in complex radiation environments to improve prediction of survivability in real environments. This paper describes the composition of this new tool and presents results of its predictions in a representative exploration environment.
IXV Venting System Design and Testing
(44th International Conference on Environmental Systems, 2014-07-13) Loddoni, Giovanni; Bertone, Massimo; Andrioli, Lorenzo; Tavera, Salvatore; Sinesi, Cosimo
The Intermediate eXperimental Vehicle (IXV) is a non-pressurized lifting-body shaped re-entry vehicle committed by ESA to TAS-I as prime contractor (on June 2009) in a synergic approach with industrial partnerships. The flight element is currently under integration at TAS-I premises (in Turin, Italy) and planned to be shipped for testing to ESA/ESTEAC by Mid-2014 and subsequently to Launch Facility. IXV mission target (whose flight is scheduled by End 2014, launch site Kourou) is basically addressed to the demonstration of advanced technologies capable of sustaining an atmospheric re-entry after a 1-hr orbital arch ranging from 120 km to 400 km of altitude. In this perspective, innovative design solutions suitable to the IXV mission have been designed and manufactured for the flight element after the completion of focused development tests and qualification campaign. Testing allowed to increase the design maturity at component, sub-systems and system Element level (technology readiness level, TRL) up to a robust design compliant with mission success criteria and ESA ECSS directed prototype demonstration requirements. To provide adequate depressurization and repressurization levels during ascent and re-entry, a dedicated venting system was accurately designed against mission-dependent environments and requirements dictated by structural and avionics constraints to preclude catastrophic effects or equipment malfunctions / damages. The scope of this paper is to present the IXV de-press/re-press venting system design, its major constituents, the analysis / test-based end-to-end development and qualification approach. The latter was adopted to achieve an adequate TRL at element / system level, reduced risks and sufficient margins for mission success. The IXV venting system, which is under responsibility of the IXV Thermal Control System (TCS), basically consists of venting ports which allow quick de-pressurization under the fairing during ascent and preclude re-entry overheating. The latter I due to the fluxes entering the internal volumes when IXV is passing across the plasma layers down to 27 km altitude. The overheating of the IXV external structures due to the high temperature of the low gas concentration mesosphere layer combined to the molecular plasma have been attentively evaluated for the venting ports design and performance optimization. The venting system architecture is discussed with reference to the driving requirements, the thermal- hydraulic behavior at element level, the performed development and qualification tests (at element and system level), the tools used to perform test predictions / post-test correlations, and finally, the test-based analysis outcomes to give evidence of functional verification. In addition, this paper intends also to present an overview of the qualified hardware manufactured and integrated in IXV for flight.
Icy Target Thermal Test Apparatus and Calibration of a Planetary Spectrometer
(44th International Conference on Environmental Systems, 2014-07-13) Vaidyanathan, Preethi; Wallach, Alex; Berisford, Daniel F.; Carlson, Robert; Hand, Kevin; Keymeulen, Didier
The Compositional Infrared Imaging Spectrometer (CIRIS) is currently under development at JPL for outer planetary missions, and is undergoing thermal-vacuum environmental testing as part of the TRL progression effort. This involves analyzing icy targets under cryogenic vacuum conditions with the spectrometer and the use of an optical calibration device designed for integration with the test setup. CIRIS was designed for use on a future Europa orbiter, with applications for missions to other worlds including Mars. It has a compact and rugged design due to its spinning refractor, which replaces the moving mirror setup of a traditional Michelson interferometer. We have designed and fabricated a test apparatus to calibrate CIRIS using a black body source and to measure reflectance of ice specimens. The apparatus presented here is validating the performance of CIRIS under Europa-like conditions, including temperature of the spectrometer, temperature of the target, and illumination of the target. A dewar assembly resides inside the vacuum chamber and is filled with liquid nitrogen using a fluid feedthrough. A cold plate mounted directly to the dewar will freeze/ contain the ice or rock targets. An external blackbody light source will illuminate the targets via a mirror/ window assembly, and a second mirror will direct the reflected light into the spectrometer. The mirror configuration can be moved in six degrees of freedom for optical alignment. The calibration source is designed to emit blackbody radiation at known and controllable temperatures between 150 and 350K via interchangeable apertures. To maintain an emissivity as close as possible to that of an ideal blackbody, the calibration source is a conical cavity coated with highly emissive paint within a solid cylinder. The cavity is made of aluminum and contains multiple heaters to ensure isothermal conditions, with ceramic standoffs to create a long thermal path which allows the cavity to be at a high temperature while the spectrometer and other nearby hardware remain cryogenic.
Suitport and Tether Operational Simulations for the 2013 Haughton Mars Project
(44th International Conference on Environmental Systems, 2014-07-13) Fort, James; Greene, Marc; Quinn, Gregory; Lee, Pascal
UTC Aerospace Systems participated in the 2013 Haughton Mars Project field studies on Devon Island, Canada by testing a new version of their suitport concept and a novel suit tether system. The suitport concept integrated lessons learned from prior studies and upgraded the user interface to use pneumatic actuation. Pneumatic actuation of the suitport and other minor upgrades were successful in improving the donning and doffing process for most users. The tether system used an external waist bearing hooked to four retractable cables that were anchored in a square pattern to form a work area. These features allowed the test subject to conduct geological work without frequent re-clipping, nor unintended entanglement in the tethers.
The Use of Porifera Membranes for Urea Rejection in Forward Osmosis Systems
(44th International Conference on Environmental Systems, 2014-07-13) Contés-de-Jesús, Enid J.; Cha, Xer; Flynn, Michael
Forward Osmosis (FO) systems are used to produce clean water from wastewater due to an osmotic pressure difference across a semipermeable membrane. While it is important to have membranes that can produce high water flux and low salt back flux, it is also necessary for them to highly reject organic and inorganic contaminants present in wastewater. It is of our interest to evaluate membranes that can highly reject urea, the main component in urine, without fouling. Currently, there are no commercially available FO membranes that can reject urea. Porifera, Inc. manufactures high performance FO membranes with open-pore hydrophilic configuration with an excellent rejection layer. Porifera FO membranes have three times higher flux and more than three times lower salt passage than conventional cellulose acetate FO membranes. In this work, deionized (DI) water with urea at ppm level was used as feed, while calcium nitrate (Ca(NO3)2) at a concentration range of 5% to 15% w/w was used as draw solution. The performance of Porifera FO membranes was evaluated terms of water flux rates, salt back flux and urea rejection. Results confirm that Porifera FO membranes have high urea rejection and very low salt back flux.
Novel CO2 Selective Membranes for CO2 Control in Space Station and Space Suit
(44th International Conference on Environmental Systems, 2014-07-13) Okada, Osamu; Teramoto, Masaaki; Nonouchi, Tamotsu; Hanai, Nobuaki; Miyata, Junya; Kiyohara, Yasato; Sakurai, Masato
For the CO2 control in the space station, attention has been mainly paid to the adsorption method. One of the alternatives to this method is the separation using membranes, which is a simple continuous system with low energy consumption and no capacity limit since CO2 absorption at the feed side of the membrane and desorption at the permeate side occur simultaneously. In order to apply membranes for the CO2 removal in space stations and also in space suits, development of membranes with extremely high CO2 selectivity over O2 and N2 is required for minimizing the O2 and N2 losses. In the present work, we developed several types of CO2 selective facilitated transport membranes. These are gel-type membranes supported on microporous membranes. The gel layer contains a CO2 carrier, which enhances CO2 permeability, and also an additive, which improves the permeation characteristics. Typical membrane performances observed at low CO2 partial pressures (0.7kPa) and room temperature are as follows. CO2 permeance: 1.23104  1.71104 Ncm3 cm-2 s-1 cmHg-1 (4.1105  5.7105 mol m-2 s-1 kPa-1), CO2/N2 selectivity: 570013700, which is much larger than those reported so far. CO2/O2 selectivity was about half the CO2/N2 selectivity. The performance of membrane module, in which the developed membranes are supposed to be used, was estimated when the module is applied to space stations and space suits. It was found that the mol fraction of CO2 recovered from the permeate side of the membrane is higher than 0.96 (dry basis), which suggests very small O2 and N2 losses. When this membrane is applied to a space suit, the membrane area and volume of the membrane module required for removing CO2 at the rate 2.23 kg/day were approximately estimated as 31.6 m2 and 16 L, respectively. The membrane module works also for removing water vapor from space suits.
Torrefaction Processing of Spacecraft Solid Wastes
(44th International Conference on Environmental Systems, 2014-07-13) Serio, Michael A.; Cosgrove, Joseph E.; Wójtowicz, Marek A.; Lee, Jeffrey; Wignarajah, Kanapathipillai; Fisher, John
New technology is needed to collect, stabilize, recover useful materials, and store human fecal waste and other spacecraft solid wastes for long duration space missions. The system should also require minimal crew interactions, low energy demands, and tolerate mixed or contaminated waste streams. The current study addressed the technical feasibility of a torrefaction (mild pyrolysis) processing system that could be used to sterilize feces and related cellulosic biomass wastes (food, paper, wipes, and clothing), while simultaneously recovering moisture and producing small amounts of other useful products (e.g., CO2, CO, and CH4). This work was done using bench scale torrefaction processing units and examined different modes of heating (conventional and microwave) in laboratory studies. A fecal simulant was tested over a range of process conditions (temperature, holding time and atmosphere), along with selected runs with a sludge derivative (Milorganite), cotton fabric, and wipes. The results demonstrated that microwave heating allowed for careful control of torrefaction conditions for the fecal simulant. The net result was complete recovery of moisture, some additional water production, a modest reduction of the dry solid mass, and small amounts of gas (CO2, CO, and CH4) and hydrocarbon liquid production. The amounts of solid vs. gas plus liquid products can be controlled by adjusting the torrefaction conditions, especially the final temperature and holding time. The solid char product from the fecal simulant was a dry, free flowing powder that did not support bacterial growth and was hydrophobic relative to the starting material. The proposed torrefaction approach has potential benefits to NASA in allowing for solid waste sterilization and stabilization, planetary protection, in-situ resource utilization (ISRU) and/or production of chemical feedstocks and carbon materials. In particular, the torrefaction char residue has several potential applications in space. These include production of activated carbon, a nutrient-rich substrate for plant growth, construction material, radiation shielding, storage of elemental carbon, hydrogen, or oxygen, and fuel gas (CH4, CO, and H2) production.
Fluid selection for space thermal control systems
(44th International Conference on Environmental Systems, 2014-07-13) van Gerner, Henk Jan; Benthem, R. C. van; Es, J. van; Schwaller, D.; Lapensée, S.
The selection of a suitable fluid is one of the first and most important steps for the design of a thermal control system. For example, for a heat pipe it is important to use a fluid with a high surface tension and heat of evaporation, and a low viscosity. These characteristics can be combined in a ‘figure of Merit’. This figure of Merit is used to pre-select a number of fluids, after which these fluids are further investigated for material compatibility, safety, radiation hardness etc. This systematic approach results in the selection of the most favourable fluid for each application. In this paper, the fluid selections for heat pumps and pumped loops (both single- and two-phase) are discussed. It is explained for instance why CO2 is used in the thermal control system of AMS02 (which was launched with the space shuttle in May 2011 and subsequently mounted on the International Space Station). Also discussed is the selection of Galden HT80 for ESA’s single-phase Mechanically Pumped Fluid Loop (MPFL) and the selection of isopentane for an ESA Heat Pump application.
Carbon Dioxide Washout Testing Using Various Inlet Vent Configurations in the Mark-III Space Suit
(44th International Conference on Environmental Systems, 2014-07-13) Korona, F. Adam; Norcross, Jason; Conger, Bruce; Navarro, Moses
Requirements for using a space suit during ground testing include providing adequate carbon dioxide (CO2) washout for the suited subject. Acute CO2 exposure can lead to symptoms including headache, dyspnea, lethargy, and eventually unconsciousness or even death. Symptoms depend on several factors including inspired partial pressure of CO2 (ppCO2), duration of exposure, metabolic rate of the subject, and physiological differences between subjects. Computational Fluid Dynamics (CFD) analysis has predicted that the configuration of the suit inlet vent has a significant effect on oronasal CO2 concentrations. The main objective of this test was to characterize inspired oronasal ppCO2 for a variety of inlet vent configurations in the Mark-III suit across a range of workload and flow rates. Data and trends observed during testing along with refined CFD models will be used to help design an inlet vent configuration for the Z-2 space suit. The testing methodology used in this test builds upon past CO2 washout testing performed on the Z-1 suit, Rear Entry I-Suit, and the Enhanced Mobility Advanced Crew Escape Suit. Three subjects performed two test sessions each in the Mark-III suit to allow for comparison between tests. Six different helmet inlet vent configurations were evaluated during each test session. Suit pressure was maintained at 4.3 psid. Suited test subjects walked on a treadmill to generate metabolic workloads of approximately 2000 and 3000 BTU/hr. Supply airflow rates of 6 and 4 actual cubic feet per minute were tested at each workload. Subjects wore an oronasal mask with an open port in front of the mouth and were allowed to breathe freely. Oronasal ppCO2 was monitored real-time via gas analyzers with sampling tubes connected to the oronasal mask. Metabolic rate was calculated from the CO2 production measured by an additional gas analyzer at the air outlet from the suit. Real-time metabolic rate measurements were used to adjust the treadmill workload to meet target metabolic rates. This paper provides detailed descriptions of the test hardware, methodology and results, as well as implications for future inlet vent designs and ground testing.
Z-2 Prototype Space Suit Development
(44th International Conference on Environmental Systems, 2014-07-13) Ross, Amy; Rhodes, Richard; Graziosi, David; Jones, Bobby; Lee, Ryan; Haque, Bazle Z. (Gama); Gillespie, John W.
NASA’s Z-2 prototype space suit is the highest fidelity pressure garment from both hardware and systems design perspectives since the Space Shuttle Extravehicular Mobility Unit (EMU) was developed in the late 1970’s. Upon completion the Z-2 will be tested in the 11 foot human-rated vacuum chamber and the Neutral Buoyancy Laboratory (NBL) at the NASA Johnson Space Center to assess the design and to determine applicability of the configuration to micro-, low- (asteroid), and planetary- (surface) gravity missions. This paper discusses the ‘firsts’ that the Z-2 represents. For example, the Z-2 sizes to the smallest suit scye bearing plane distance for at least the last 25 years and is being designed with the most intensive use of human models with the suit model.
Spacecraft Fire Experiment (Saffire) Development Status
(44th International Conference on Environmental Systems, 2014-07-13) Ruff, Gary A.; Urban, David L.; Fernandez-Pello, A. Carlos; T'ien, James S.; Torero, Jose L.; Legros, Guillaume; Eigenbrod, Christian; Smirnov, Nickolay; Fujita, Osamu; Cowlard, Adam J.; Rouvreau, Sebastien; Minster, Olivier; Toth, Balazs; Jomaas, Grunde
The status is presented of a spacecraft fire safety research project that is under development to reduce the uncertainty and risk in the design of spacecraft fire safety systems for exploration missions. The Spacecraft Fire Safety Demonstration Project is developing three Spacecraft Fire Experiments (Saffire-I, -II, and -III) to conduct a series of material flammability tests at a length scale that is realistic for a serious spacecraft fire in low-gravity. The objectives of these experiments are to (1) determine how rapidly a large scale fire grows in low-gravity and (2) investigate the low-g flammability limits compared to those obtained in NASA’s normal gravity material flammability screening test. The experiments will be conducted in Orbital Science Corporation’s Cygnus vehicle after it has deberthed from the International Space Station. Although the experiment will need to meet rigorous safety requirements to ensure the carrier vehicle does not sustain damage, the absence of a crew removes the need for strict containment of combustion products. The tests will be fully automated with the data downlinked at the conclusion of the test before the Cygnus vehicle reenters the atmosphere. A computer modeling effort will complement the experimental effort. An international topical team is collaborating with the NASA team in the definition of experiment requirements and performing supporting analysis, experimentation and technology development. The status of the overall experiment are summarized in this paper along with a brief look at future experiments that could further enhance NASA’s approach to spacecraft fire safety.
Orion Multi-Purpose Crew Vehicle Active Thermal Control and Environmental Control and Life Support Development Status
(44th International Conference on Environmental Systems, 2014-07-13) Lewis, John F.; Barido, Richard A.; Boehm, Paul; Cross, Cynthia D.; Rains, George Edward
The Orion Multi Purpose Crew Vehicle (MPCV) is the first crew transport vehicle to be developed by the National Aeronautics and Space Administration (NASA) in the last thirty years. Orion is currently being developed to transport the crew safely beyond Earth orbit. This year, the team focused on building the Exploration Flight Test 1 (EFT1) vehicle to be launched in September of 2014. The development of the Orion Active Thermal Control (ATCS) and Environmental Control and Life Support (ECLS) System, focused on the integrating the components into the EFT1 vehicle and preparing them for launch. Work also has started on preliminary design reviews for the manned vehicle. Additional development work is underway to keep the remaining component progressing towards implementation on the flight tests of EM1 in 2017 and of EM2 in 2020. This paper covers the Orion ECLS development from April 2013 to April 2014.
Fresnel-based Solar Concentration Power System for Mars and Lunar Outposts
(44th International Conference on Environmental Systems, 2014-07-13) Furfaro, Roberto; Gellenbeck, Sean; Sadler, Phil
Future human exploration of the solar system will require architecting and deploying missions that last for years. Oxygen generation and atmosphere revitalization represent a critical component for sustainable long-term space missions. Bioregenerative Life Support Systems (BLSS) can recycle oxygen, water and produce food. However, power is generally a limiting factor for effective implementation of such systems. Nevertheless, solar concentrating technology can be integrated with BLSS to improve performance and reduce the Equivalent System Mass (ESM). In this paper we present and discuss the development of a Fresnel-based Solar Concentration Power System (SCPS) for future Mars and lunar outposts. SCPS is primarily conceived to operate as energy support system for outposts that comprise a greenhouse-based BLSS as source for oxygen, water and food. The system employed a closed-loop sun-tracking system coupled with a Fresnel-based collector capable of separating the solar irradiation as function of wavelength along the system’s longitudinal axis. A set of fiber optics was employed to distribute the Photosynthetic Active Radiation (PAR) portion of the spectrum to the greenhouse components. In addition, the system was designed to collect infra-red portion of the spectrum and convert it to electricity using a set of PV cells. An initial Fresnel-based SCPS prototype was tested and evaluated at the University of Arizona Controlled Environment Agriculture Center. An analysis was conducted to understand the impact of the system performance on the energy balance of future Mars and lunar outposts.
Environmental Control and Life Support System Reliability for Long-Duration Missions Beyond Lower Earth Orbit
(44th International Conference on Environmental Systems, 2014-07-13) Sargusingh, Miriam J.; Nelson, Jason R.
NASA has highlighted reliability as critical to future human space exploration, particularly in the area of environmental controls and life support systems. The Advanced Exploration Systems (AES) projects have been encouraged to pursue higher reliability components and systems as part of technology development plans. However, no consensus has been reached on what is meant by improving on reliability, or on how to assess reliability within the AES projects. This became apparent when trying to assess reliability as one of several figures of merit for a regenerable water architecture trade study. In the spring of 2013, the AES Water Recovery Project hosted a series of events at Johnson Space Center with the intended goal of establishing a common language and understanding of NASA’s reliability goals, and equipping the projects with acceptable means of assessing the respective systems. This campaign included an educational series in which experts from across the agency and academia provided information on terminology, tools, and techniques associated with evaluating and designing for system reliability. The campaign culminated in a workshop that included members of the Environmental Control and Life Support System and AES communities. The goal of this workshop was to develop a consensus on what reliability means to AES and identify methods for assessing low- to mid-technology readiness level technologies for reliability. This paper details the results of that workshop.
Development of an Outreach and Teaching Module (LGH- OTM) Based On Prototype Lunar Greenhouse Program
(44th International Conference on Environmental Systems, 2014-07-13) Munday, Michael F.; Giacomelli, Gene; Yanes, Marianna; Patterson, R. Lane
The Lunar Greenhouse Outreach & Teaching Module (LGH-OTM) was developed by the Controlled Environment Agriculture Center of the University of Arizona (UA-CEAC), with its associates Hungry Planets Systems and Services (HPSS), Sadler Machine Company (SMC) and several site-specific organizations. A public education platform, the LGH-OTM served to advance the activities of the Arizona-NASA Ralph Steckler Space Colonization grant program, focused on outreach goals to present science, technology, education, food security and production, with educational exhibits and demonstrations. In display at high efficacy public education venues to achieve education outreach, media placement, and controlled environment agriculture training opportunities, the LGH-OTM was a more portable and tangible version of the prototype Lunar Greenhouse (LGH) installation at UA-CEAC. With written and video materials marshalled by HPSS and developed by CEAC staff, HPSS and site-specific professionals, the LGH-OTM was displayed at three sites in the USA, gaining a verified total audience of more than 2.5 million. The LGH program was based on more than a decade of installed research at and from the UA-CEAC, Systems and Industrial Engineering (UA-SIE) and Aerospace and Mechanical Engineering (UA-AME) in collaboration with SMC and many other partners, beginning with the South Pole Food Growth Chamber through Raytheon Polar Services Company and the National Science Foundation (NSF), and with continued sponsorship by NASA, NSF and various aerospace companies including Aero- Sekur SpA (Italy), Franco-Italian Thales Alenia Space, and AGC Green-Tech Co. (Japan). The LGH program, funded by NASA Steckler Phase 1 and 2 Space Grant, supported collaboration from a multidisciplinary and multinational team of experts to study and evaluate the scientific and technical merit and feasibility of the LGH as a Bioregenerative Life Support System. The LGH-OTM was constructed to demonstrate crop production within a BLSS-type physical environment with a hydroponic multi-cropping system that could produce crops (lettuce, strawberry, sweet potato, and tomato). It was a semi-autonomous food production device capable of automated climate control (air temperature, light, and hydroponic nutrient solution), and using labor for transplant and harvest it successfully demonstrated controlled environment and hydroponic crop production within a semi- portable educational setting. The system also included sensor and reports systems allowing for remote data collection. The presentation will focus on technical and communication accomplishments in design; materials of construction and display; operation; and educational programs of UA-CEAC and its partners about the LGH-OTM.
Full System Modeling and Validation of the Carbon Dioxide Removal Assembly
(44th International Conference on Environmental Systems, 2014-07-13) Coker, Robert; Knox, James; Gauto, Hernando; Gomez, Carlos
The Atmosphere Revitalization Recovery and Environmental Monitoring (ARREM) project was initiated in September of 2011 as part of the Advanced Exploration Systems (AES) program. Under the ARREM project, testing of sub-scale and full-scale systems has been combined with multiphysics computer simulations for evaluation and optimization of subsystem approaches. In particular, this paper describes the testing and modeling of various subsystems of the carbon dioxide removal assembly (CDRA). The goal is a full system predictive model of CDRA to guide system optimization and development. The development of the CO2 removal and associated air-drying subsystem hardware under the ARREM project is discussed in a companion paper.
Material Circulation Control with Modules Addition in Advanced Life Support System using Hierarchical Autonomous Control Method
(44th International Conference on Environmental Systems, 2014-07-13) Nakane, Masakatsu; Ishikawa, Yoshio
An advanced life support system (ALS) recycles and circulates materials within a system, and will eventually make possible sustained life in outer space. This study addresses a subsystem that recycles the elements of carbon, hydrogen and oxygen, with planned functions that include waste recycling and food production. We have previously proposed a procedure for such a system that combines automatic generation of scheduling and multi- agent reinforcement learning (MARL), based on a hierarchical control method. This procedure is again used in this paper to simulate material circulation during modifications to the ALS. Specifically, one module was added to both the existing human habitation module and the plantation module while the scheduling calculations were in progress. The results indicated that both the upper and the lower control layers successfully adapted to the new environment and performed control. Also, it was demonstrated to be possible to guarantee effective overall control of the ALS, with a flexible response to system modifications, which had been difficult under a decentralized autonomous control scheme alone.
Thermal Control System of X-ray Astronomy Satellite ASTRO-H: Current Development Status and Prospects
(44th International Conference on Environmental Systems, 2014-07-13) Iwata, Naoko; Usui, Takashi; Miki, Akihiko; Ikeda, Mizuho; Yumoto, Takahiro; Ono, Yukari; Abe, Kazuhiro; Ogawa, Hiroyuki; Takahashi, Tadayuki
The current development status and prospects of the thermal control system of JAXA’s next major X-ray astronomy mission, ASTRO-H, are presented. ASTRO-H finished thermal balance tests (TBTs) with its thermal test model (TTM) in 2012 and is currently undergoing mechanical and electrical integration tests. ASTRO-H will be launched in 2015 after about one year of proto-flight model (PFM) system integration tests. The thermal mathematical models (TMMs) were correlated with the TTM TBT results, and the orbital thermal analyses were performed for 48 cases including not only the nominal cases but also the launch and contingency cases. According to the analysis results, some thermal designs such as the heater size and radiator area were changed. Also, some of the PFT hardware will be changed because of discrepancies found during and after the TTM TBTs. All of the design changes will be reflected to the PFM before system integration tests. The thermal design and the TMM will be finally verified by the TBTs in the PFM system integration tests campaign.

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