National Aeronautics and Space Administration

DRAFT Human Health, Life Support and Habitation Systems Technology Area 06

Kathryn Hurlbert, Chair Bob Bagdigian Carol Carroll Antony Jeevarajan Mark Kliss Bhim Singh

November • 2010 DRAFT This page is intentionally left blank

DRAFT Table of Contents Foreword Executive Summary TA06-1 1. General Overview TA06-2 1.1. Technical Approach TA06-2 1.2. Benefits TA06-2 1.3. Applicability/Traceability to NASA Strategic Goals, AMPM, DRMs, DRAs TA06-2 1.4. Top Technical Challenges TA06-5 2. Detailed Portfolio Discussion TA06-6 2.1. Environmental Control and Life Support Systems (ECLSS) and Habitation Systems TA06-7 2.1.1. Approach and Major Challenges TA06-7 2.2. Extra-Vehicular Activity (EVA) Systems TA06-10 2.2.1. Approach and Major Challenges TA06-11 2.3. Human Health and Performance (HHP) TA06-12 2.3.1. Approach and Major Challenges TA06-14 2.4. Environmental Monitoring, Safety, and Emergency Response (EMSER) TA06-16 2.4.1. Approach and Major Challenges TA06-17 2.5. Radiation TA06-17 2.5.1. Major Approach and Challenges TA06-19 3. Interdependency with Other Technology Areas TA06-21 4. Possible Benefits to Other National Needs TA06-21 Acronyms TA06-24 Acknowledgements TA06-24

DRAFT Foreword NASA’s integrated technology roadmap, including both technology pull and technology push strategies, considers a wide range of pathways to advance the nation’s current capabilities. The present state of this effort is documented in NASA’s DRAFT Space Technology Roadmap, an integrated set of fourteen technology area roadmaps, recommending the overall technology investment strategy and prioritization of NASA’s space technology activities. This document presents the DRAFT Technology Area 06 input: Human Health, Life Support and Habitation Systems. NASA developed this DRAFT Space Technology Roadmap for use by the National Research Council (NRC) as an initial point of departure. Through an open process of community engagement, the NRC will gather input, integrate it within the Space Technology Roadmap and provide NASA with recommendations on potential future technology investments. Because it is difficult to predict the wide range of future advances possible in these areas, NASA plans updates to its integrated technology roadmap on a regular basis.

DRAFT Executive Summary lieve that each activity or milestone represented in This roadmap provides a summary of key capa- the TASR does indeed have a technology solution bilities in the domain of TA06, Human Health, to pursue at the present time, or will have within Life Support and Habitation Systems (HLHS), the timeframe shown. Each sub-TA portion of the necessary to achieve national and agency goals in roadmap is detailed in Section 2, providing fur- human space exploration over the next few de- ther explanation of the sub-TA as well as a sum- cades. As an example, crewed missions venturing mary table of the priority technologies and/or sys- beyond Low-Earth Orbit (LEO) will require tech- tem functional areas of interest, the current SOA, nologies with improved reliability, reduced mass, the major challenges for advancement, and the self-sufficiency, and minimal logistical needs as an recommended milestones/activities to advance to emergency or quick-return option will not be fea- a TRL-6 or beyond (i.e., demonstration in a rele- sible. The sub-technology areas (sub-TAs) includ- vant mission environment or simulation thereof), ed in the roadmap are Environmental Control which correlates with the TASR content. Section and Life Support Systems (ECLSS) and Habita- 2 also provides some example technological solu- tion Systems; Extra-Vehicular Activity (EVA) Sys- tions, but these should not be considered all-in- tems; Human Health and Performance (HHP); clusive or decisive without rigorous survey of SOA Environmental Monitoring, Safety, and Emergen- and proposed technologies and further review/ cy Response (EMSER); and Radiation. study. Some major technical challenges identified Shown on the next page is an overview road- for each sub-TA are presented in Section 1.4, for map (called the Technology Area Strategic Road- periods spanning the next two decades. map (TASR)), which includes planned, predict- As can be seen in the TASR, milestones are ed, and new proposed missions and milestones aligned to minimize the number of necessary at the top. Examples of the planned and predict- flights to progress the technologies and maximize ed missions are human missions to LEO (e.g., In- the use of integrated ground tests/demonstrations ternational Space Station (ISS)) and Near-Earth of new technologies for reduced risk. The ‘flight Objects (NEOs). More detail on these “pull” mis- campaigns’ serve as validation beacons to project sions and milestones is given in Section 1.3. In managers of future missions. It is recognized that addition, new “push” missions and milestones are validation to TRL-6 should occur by the Prelim- proposed, and represent key events that would ad- inary Design Reviews (PDRs) of these missions; vance or validate technologies to a point where PDR is targeted for no later than three years be- they would be available to implement into future fore launch readiness, and more often desired five missions at low risk. An example “push” mission is to six years before human missions. the extension of ISS operations beyond 2020, to The primary benefit of investment in technolo- allow for continued and sustained testing and ad- gy development for the HLHS domain is the abil- vancements related to space-environment effects ity to successfully achieve human space missions on humans. to LEO and well beyond, as described in Section The lower portion of the TASR is populated 1.2. At the same time, significant potential exists with technology milestones and activities for each for improvements in the quality of life here on of the sub-TAs, as recommended to allow signif- Earth and for benefits of national and global inter- icant advancements to support the missions and est. Section 4 provides an extensive description of milestones identified. The icons are designated how investment in HLHS can provide technolo- in the legend at the bottom, and distinguish be- gies for climate change mitigation, emergency re- tween “pull” that directly tie to a mission, activity sponse, defense operations, human health, biolog- or milestone, versus “push” where there is no di- ical breakthroughs, and more. rect link but a recommendation/path to support The OCT Roadmapping activity is intended to future needs. Also, distinction is made for ground identify overlaps across TAs, and for the topical versus flight activities, and cross-cutting technol- areas of TA06, HLHS, many such overlaps exist. ogies are identified. Notably, some technologies Notably, the greatest overlap occurs with TA07, in the roadmap are currently at a low Technology Human Exploration and Development of Space Readiness Level (TRL), but could provide signifi- (HEDS). Delineation exists in that the focus of cant advancement in the current State-of-the-Art HLHS is specific to the human element, includ- (SOA) and/or drive new approaches or techniques ing technologies that directly affect crew needs for in accomplishing mission implementation. The survival, human consumption, crew health and subject matter experts authoring this roadmap be- well-being, and the environment and/or interfaces DRAFT TA06-1 to which the crew is exposed. Alternately, HEDS proposed technologies as well as associated mile- focuses on the global architecture and overall in- stones and missions correlating to the TASR. frastructure capabilities to enable a sustained hu- Also, the TASR milestones are aligned to mini- man presence for exploration destinations. More mize the number of necessary flights to progress detail on HLHS relationships to the other TAs is the technologies and maximize the use of integrat- included in Sections 2.0 and 3.0. ed ground tests/demonstrations for reduced risk. The ‘flight campaigns’ serve as validation beacons 1. General Overview to project managers of future missions. It is rec- ognized that validation to TRL-6 should occur by 1.1. Technical Approach the Preliminary Design Reviews of these missions; This roadmap provides a summary of key ca- PDR is targeted for no later than three years be- pabilities, including game-changing or break- fore launch readiness, and more often desired five through items, within the domain of TA06, to six years before human missions. HLHS, necessary to achieve predicted national and agency goals in space over the next few de- 1.2. Benefits cades. As an example, crewed missions venturing The primary benefit of significant technology beyond LEO will require technologies for high re- development for the HLHS domain is the abili- liability, reduced mass, self-sufficiency, and min- ty to successfully achieve affordable human space imal logistical needs, as an emergency or quick- missions to LEO and well beyond. Continued ISS return option will not be feasible. Human space operation and missions will directly contribute to missions include other critical elements such as the knowledge base and advancements in HLHS 1) EVA systems to provide crew members protec- in the coming decade, as a unique human-tended tion from exposure to the space environment dur- test platform within the space environment. Ei- ing planned and contingency/emergency opera- ther extension of ISS operations, or using an al- tions; 2) crew health care to address physiological, ternative permanent or semi-permanent in-space psychological, performance and other needs in-si- facility would facilitate sustained research/testing tu; 3) monitoring, safety, and emergency response and associated advancements into the following systems such as fire protection and recovery, envi- decade as well, in preparation for missions beyond ronmental monitoring sensors, and environmen- LEO. In-space test beds will be crucial to the de- tal remediation technologies; and 4) systems to velopment and validation of technologies needed address radiation health and performance risks, for those bold space missions, such as a NEO, cur- and shielding and other mitigations. rently under consideration. The TASR provides a top-level overview of the The proposed roadmap includes many suggest- roadmap content herein. The missions shown in- ed in-flight and ground test activities for pre-flight clude those to LEO (e.g., ISS) and other poten- evaluation and augmented research/testing of rec- tial destinations beyond (e.g., NEO). In addition, ommended technologies, which will regularly and “push” missions and milestones are recommended efficiently provide advancements during the de- for consideration, which represent key events for velopment phases. More details on the benefits advancement or validation of technologies and/ for each entry are defined in subsequent sub-TA or a point where the technologies could be avail- sections. Additionally, Section 4 provides an ex- able to implement for future missions. An exam- tensive description of how investment in HLHS ple “push” mission is the extension of ISS oper- technologies can lead to improvements in the ations beyond 2020 to allow for continued and quality of life here on Earth and create benefits sustained testing and advancements related to of national and global interest. Examples include, space-environment effects on humans. Notably, but are not limited to, technologies related to cli- some technologies in the roadmap are currently at mate change mitigation, emergency response, mil- a low TRL, but could provide significant advance- itary operations, human health, and biological sci- ment in the SOA and/or drive new approaches or ence breakthroughs. techniques in accomplishing mission implemen- 1.3. Applicability/Traceability to NASA tation. Strategic Goals, AMPM, DRMs, DRAs The HLHS sub-TAs detailed in the roadmap The process to develop the TASR included 1) content herein are ECLSS and Habitation Sys- initial consideration of the overall agency goals, tems; EVA Systems; HHP; EMSER; and Radi- outcomes, and objectives as “pull” missions for the ation. Section 2 details each sub-TA, including technology content and milestones; and 2) incor-

TA06-2 DRAFT Figure 1: Human Health, Life Support and Habitation Systems Roadmap

DRAFT TA06–3/4 This page is intentionally left blank poration of the NASA Mission Directorate and this technology area (TA) exists; however, the dis- NASA Centers needs and focus within the sub- tinction is that TA06, HLHS, is specific to the TAs. While the strategic plan for the agency, and human element, including technologies that di- therefore its strategic goals, specific missions, etc., rectly affect crew needs for survival, human con- is currently being finalized, the top portion of the sumption, crew health and well-being, and the en- roadmap does include the proposed agency-level vironment and/or interfaces to which the crew is major missions and milestones derived from the exposed. For the TA06, HLHS, drafted roadmap drafted FY11 Agency Mission Planning Manifest herein, some “push” missions and milestones are (AMPM)1 ; an example is the planned ISS opera- also recommended for consideration, like extend- tions through 2020. In addition, some content re- ed operation of the ISS. It should be noted that lated to Design Reference Missions (DRMs) were alternative platforms might serve this purpose as based on Design Reference Architectures (DRAs) well, such as commercial or joint space stations/ evaluated as a part of the Human Exploration vehicles, if available and appropriate for the pro- Framework Team (HEFT) activity2 ; an exam- posed technologies. ple is the assumed human missions beyond LEO, The proposed roadmap provides time phasing such as the mission to a NEO/Near-Earth Aster- that would allow infusion of technologies or ca- oid (NEA), within the 2025 timeframe. An at- pabilities to support planned, predicted, and new tempt was also made to consider the relevant mis- proposed agency missions and/or milestones. sions and milestones included on TA07, Human Once the agency direction and authorization for Exploration and Development of Space (HEDS), FY11 and beyond is finalized, the roadmap should Roadmap, as considerable potential overlap with be re-evaluated. 1 Agency Mission Planning Manifest. Draft internal NASA 1.4. Top Technical Challenges document. 2011. The table below summarizes some major techni- 2 Human Exploration Framework Team (HEFT) DRM Re- view - Phase 1 Closeout, September 2, 2010. cal challenges that will be faced in the continua- Table 1. Major Technical Challenges Present – 2016 Integrate fundamental research results on radiation environment biological effects, and including other effects from space exposure, into damage/risk model(s) and consolidate and interpret databases of major signaling pathways causative of cancer from space exposure and other damage Stabilize liquid and solid wastes to recover water and to control pathogens, biological growth and gas/odor production

Achieve high reliability and reduce dependence on expendables over existing SOA systems that recover O2 from CO2 and H2O from humidity condensate and urine Develop advanced screening technologies, to detect and/or predict subclinical malignancies, subclinical cataracts, individual susceptibility levels to space exposure (e.g., radiation) and carbon dioxide exposures, osteoporosis, oxidative stress, renal stone formation, anxiety, and depression Demonstrate EVA technologies that could be used to extend EVA capability on ISS beyond 2020. These technologies include advances for on-back regener-

able CO2 and humidity control, advanced suit materials, and more capable avionics Demonstrate real time airborne particle monitoring on the ISS 2017 – 2022 Develop radiation risk model(s) as a predictive systems biology model approach for space radiation, including development of experimental methods/ techniques and models to verify integrated risk and understand synergistic effects of other spaceflight stressors (microgravity, reduced immune system response, etc.) combined with radiation Validate physiological and psychological countermeasures for long-duration missions, which can include any combination of exercise, non-exercise (e.g., pharmacological) and/or advanced techniques (e.g., Virtual Reality technologies such as a “Holodeck”, artificial gravity)

Close high-reliability ECLSS more fully, with >95% O2 and H2O recovery from an integrated mission perspective Implement bulk food processing in-flight and augmentation of food supply with plants Advanced EVA technologies to enable missions to NEOs, which includes suits that incorporate advanced materials and component demonstrations of life support technologies that reduce consumables Complete development of a distributed hybrid fire-detection system for space missions 2023 – 2028

Demonstrate hybrid physical/chemical and biological ECLSS with >95% recovery of O2 and H2O with bulk food production Develop and validate a non-ionizing, full body, dynamic, 3-D imaging with in-situ diagnosis and treatment capabilities (e.g., renal stone ablation) Validate real-time monitoring and forecasting space weather model(s), to include prediction of onset and evolution of Solar Particle Events (SPEs) as well as all clear periods Flight demonstration of an advanced EVA system, including suits that utilize multifunctional materials, a portable life-support system (PLSS) with no con- sumables, on-suit power generation, and avionics that enable the crew to operate autonomously Complete integrated system testing of portable, non-solvent-based microbial remediation on ISS

DRAFT TA06-5 tion and progression of human spaceflight, espe- 2. Detailed Portfolio cially for crewed missions beyond LEO. The listing Discussion was determined by reviewing the recommended This document provides a summary of key ca- content for each sub-TA for the time period spec- pabilities in the TA06, HLHS, domain, recom- ified, and selecting one or two technologies and/ mended to achieve predicted national and agen- or priority system functions within that domain cy goals in space over the next few decades. The for a balanced representation of HLHS. The table sub-TAs, illustrated in Figure 2, are described in specifies technologies that are a low TRL and re- more detail in subsequent sections. Notably, for quire extended development time to be ready for TA06, HLHS, the greatest TA interdependen- future missions, those that may significantly im- cy is with TA07, HEDS. Substantial delineation pact mission implementation (e.g., high reliabil- between the two TA scopes does exist. HLHS ity, reduced logistics, decreased mass, high effi- concentrates specifically on the human element, ciency power systems, etc.), and/or those that are whereas HEDS focuses on the global architecture critical to human safety and well-being. An exam- and overall infrastructure capabilities to enable a ple is that top priorities for ECLSS include matur- sustained human presence for exploration desti- ing technologies for high reliability and reduced nations. The HLHS domain includes technol- logistics, as supported by the recent HEFT activ- ogies that directly affect crew needs for survival, ity3 . The recommended activities and milestones human consumption, crew health and well-being, related to the challenges listed below, and those in and the environment and/or interfaces to which the Section 2 tables for each sub-TA, are direct- the crew is exposed. An example is water technol- ly correlated to the TASR content. The TASR also ogies, which are needed for direct human water shows when the milestones and activities related intake, but also for hygiene and humidity control. to the challenges are intended to be met. This is distinguished from HEDS, for which the water focus is on extraction from in-situ materials 3 Ibid. for use in vehicle systems, or optimal placement of storage tanks to maximize radiation shielding

Figure 2. Technology Area Breakdown Structure (TABS) TA06-6 DRAFT without affecting the functional architecture. An- venting or de-orbiting in spent resupply vehicles. other example is that for HLHS, the EVA systems Longer-duration missions demand that reusable are those that directly interface to the human and water be recovered from wastewater in order to provide the life support, such as the suit itself and reduce or eliminate the need for Earth-based re- the support systems. Conversely, in HEDS, for supply. Short- and long-duration missions typical- the EVA systems include the mobility technolo- ly also require some degree of wastewater stabili- gies needed to interface to the vehicles/systems at zation to protect equipment and facilitate potable the exploration site(s) and to the components, in water disinfection for storage. order to conduct human mission operations; ex- Waste Management – The objective of this el- amples include a suitport and/or suitlocks, rovers, ement is to safeguard crew health, increase safety tools and translation aids. Another area of poten- and performance, recover resources, and protect tial overlap for both TAs is food preparation and planetary surfaces, all while decreasing mission production, but this too has been resolved: for costs. Key technology gaps to be addressed for HLHS, food is a critical consumable for humans future missions include waste/trash volume re- and provides a future interface to the life support duction and stabilization, water recovery from system for carbon dioxide scrubbing. For HEDS, wastes, and ultimately a high-percentage recovery the primary concentration is on production and of H2O, O2, N2, CO2, and minerals. Additional preservation of food for in-transit space and desti- technology gaps include waste collection, disposal nations, to minimize human-specific logistics and, and containment technologies, and source odor/ therefore, support self-sufficiency for remote mis- contaminant control. sions beyond LEO. Overlaps with other TAs are Habitation – This area focuses on habitation described briefly in Section 3. functions that closely interface with life support 2.1. Environmental Control and Life systems, including food preparation and produc- Support Systems (ECLSS) and tion, hygiene, metabolic waste collection, cloth- Habitation Systems ing/laundry, and the conversion of logistics trash The main objective of spacecraft life support and to resources. Other habitation functions such as habitation systems is to maintain an environment deployable crew volumes, habitation analogs, suitable for sustaining human life throughout the lighting, housekeeping tools, and noise mitigation duration of a mission. The ECLSS and Habitation are addressed in TA07, HEDS. System includes four functions, each of which is 2.1.1. Approach and Major Challenges described below. The basic human metabolic spacecraft require- Air Revitalization – The overarching function ments of oxygen, water, and food have been well of this element is to maintain a safe and habitable characterized, and these requirements have largely atmosphere within a spacecraft, surface vehicle, been met for short-duration missions (from Proj- or habitat. This is achieved through the remov- ect Mercury to the Space Shuttle) with open-loop al of carbon dioxide, trace volatile organic com- life support systems using expendables. pounds, and particulates that are released into the For the ISS, continual operational costs of a atmosphere from crew member and vehicle sourc- conventional open-loop system are prohibitive. es. Oxygen and nitrogen are added to the atmo- Accordingly, the ISS life support systems process sphere in controlled manners to maintain cabin condensate and urine into potable water. An up- pressures and composition, and to make-up for coming technology demonstration will also enable metabolic consumption and loss. Ventilation mix- recovery of half of the oxygen available in carbon es atmospheric constituents and transports sensi- dioxide. This approach is a significant advance ble and latent heat loads to rejection devices. In over previous systems, but many of the technical long-duration missions, oxygen and carbon can be solutions to human life support for the ISS de- recovered from carbon dioxide and recycled to re- pend upon reliable system operation and timely duce mission life-cycle costs and upmass. logistical support from Earth. Water Recovery and Management – This ele- As NASA looks toward human missions be- ment provides a safe and reliable supply of pota- yond LEO, two key distinctions exist from all ble water to meet crew consumption and opera- crewed space missions to date: 1) human beings tional needs. Short-duration missions often can be will spend significantly longer periods of time far- executed by using launched water supplies com- ther from reliable logistics depots, and 2) an emer- bined with disposing wastewater via overboard gency quick-return option will not be feasible.

DRAFT TA06-7 Accordingly, to sustain life on long-duration mis- pabilities with the optimal combination of mass, sions beyond LEO, high reliability will become an size, reliability, logistics, and loop closure charac- increasingly dominant design driver. Therefore, teristics that will best support the given mission the ECLSS and Habitation Systems technical area scenario. must develop and mature technologies that em- In maturing these technologies, life support and phasize 1) high-reliability processes and integrated habitation systems for missions beyond LEO will systems that employ autonomous monitoring and need to address both the technological shortcom- control systems and that are easily maintained by ings and the functional integration inefficiencies the crew; 2) increased self-sufficiency, enabled by of existing systems. Further reduction of life-cy- highly reliable means of recovering life-supporting cle costs and closure of life support systems is par- commodities such as oxygen, water, and food; and amount, including focus on the key challenges 3) minimized logistics supply to diminish overall summarized in Table 2. mass of spares, maintenance equipment, clothing, Air revitalization is typically achieved by the food containers, and other items requiring stow- combined operation of many individual equip- age mass and volume. ment items, each optimized to perform one or two Reliability, logistics, and loop closure all con- functions4 . Utilization of multifunctional materi- tribute to overall mission life-cycle costs. As ca- als and processes can reduce system size and oper- pabilities to recover and produce life support con- ational complexity, regardless of mission duration. sumables (O2, H2O, food) are added to a launch Such multifunctional systems must be developed vehicle, initial mass may be increased for addition- to avoid burdensome maintenance or repair. Al- al system hardware, spare parts, and expendable though air revitalization life-cycle costs for long- supplies. Depending on the mission duration and duration missions are dominated by the degree operations concept, these initial penalties need to of oxygen recovery, system reliability and utiliza- be justified by the resultant long-term consum- tion of expendables also contribute substantially ables savings. Architectural trades uncover which to mission economics and probability of success. combinations of capabilities yield the lowest life- Reliability drivers include dynamic electrome- cycle cost for a given mission duration and con- chanical devices (valves and valve position indi- cept. A representative break-even comparison of cators, compressors, etc.) as well as components this type is shown in Figure 3. The goal of life sup- often considered “static” due to material attrition port and habitation architecture is to select the ca- and loss of critical properties over time (sorbents, heat exchanger coatings, membranes, etc.). Oper- ating equipment and airflows produce substantial acoustic emissions that dominate the cabin envi- ronment and require system size increases to ac- commodate marginally-effective acoustic treat- ments. Overboard venting of process gases as well as residual atmosphere constituents during airlock operations may require substantially greater con- trols on planetary surfaces than has been histori- cally required in LEO in order to meet planetary protection requirements. Mission concepts that require the recharge of oxygen accumulators drive the need to reliably generate or compress gaseous oxygen to high pressures or liquefy it to achieve high storage densities. Similar to air revitalization, life-cycle costs for water recovery and management are dominated by the degree of water recovery, system reliabili- ty, and utilization of expendables. As in air revi- talization, reliability drivers include both dynamic

Figure 3. Representative Comparison of Life-Cycle 4 Perry, J., Bagdigian, R., and Carrasquillo, R., 2010, “Trade Spaces in Crewed Spacecraft Atmosphere Revitalization System Devel- Mass Predictions, Candidate ECLSS Architec- th tural Approaches opment.” Paper presented at 40 International Conference on Environ- mental Systems, Barcelona, Spain, July 11-15. TA06-8 DRAFT Table 2. ECLS and Habitation Technical Area Details Function Current SOA/Practice Major Challenge(s) Milestones/Activities to Ad- vance to TRL-6 or beyond

Air Revitalization CO2 removal via expendable lithium hydroxide Attain high reliability 2011-14: 75% O2 recovery and regenerable molecular sieves [TRL-9] and amines [TRL-6] Reduce utilization of expendables 2011-14: Variable cabin pressure control

O2 supply via compressed gas delivery, scav- Reduce power and equipment mass and enging of cryogenic fuel cell reactant boil-off, volume 2015-19: 100% O2 recovery consumption of expendable perchlorate

candles, and water electrolysis Increase recovery of O2 from CO2 2020-24: O2 recovery augmented by crop systems and life-support-

50% O2 recovery from CO2 [Sabatier TRL-7] Reduce acoustic emissions ing materials

Trace contaminant removal via catalytic oxida- Control environmental mass exchanges to 2025-29: O2 recovery principally tion and expendable sorbents ensure planetary protection provided by crop systems and life supporting materials Particulate filtration System impacts of cabin atmospheres with reduced total pressures and elevated oxygen Ducted fans concentrations Air/liquid heat exchangers (condensing, non- Develop and validate complex models and condensing) simulations (e.g., Computational Fluid Dynam- ics (CFD), human metabolic models, chemical and microbial processes)

Water Recovery H2O recovery from humidity condensate and Attain high reliability 2011-14: 40-55% H2O recovery and Manage- urine only (representing only 15-20% of the (condensate, urine, hygiene) ment anticipated wastewater load for exploration Reduce utilization of expendables

missions) 2015-19: 98% H2O recovery (con- Reduce power and equipment mass and densate, urine, hygiene, laundry, volume waste)

Reduce acoustic emissions 2020-24: 98% H2O recovery augmented by biological systems Recover water from additional sources, includ- (condensate, urine, hygiene, ing hygiene and laundry laundry, waste, In-Situ Resource Utilization (ISRU)-derived) Increase overall water recovery percentage

2025-29: 98% H2O recovery Stabilize wastewater from multiple sources in principally provided by biological manners that are compatible with processing systems systems Disinfect and maintain microbial control of po- table water by means that protect crew health and provide reliable monitoring Waste Manage- Single-use supplies and return of all wastes to Attain high reliability 2011-14: Waste stabilization and ment Earth for disposal volume reduction Reduce utilization of expendables

2015-19: H2O recovery from Reduce power and equipment mass and wastes volume 2020-24: Waste mineralization Stabilize wastes to control pathogens, biologi- cal growth, and gas/odor production 2025-29: >95% waste resource recovery

Resource Recovery – recover H2O and other re- sources (O2, CO2, N2, minerals, clothing radiation shielding, and fuel) Planetary Protection compatibility Habitation Limited clothing reuse prior to disposal (0.38 Odor/microbial control for multiple uses – limit- 2011-14: Long-wear clothing; 50% kg/crew-day) – no in-flight laundry capability ing impact on wastewater processor less food packaging All ISS food requires ground resupply – zero-g plant growth demonstrated Simplified bulk food preparation and continu- 2015-19: Reusable clothing; fresh ous low-energy and low-volume food produc- food augmentation tion 2020-24: Bulk food processing Laundry systems 2025-29: Bulk food production systems 2025-29: Biological engineering for food production electromechanical devices (valves, pumps, centrif- gaseous contaminant release (e.g., ammonia). Re- ugal gas/liquid separators, etc.) and “static” ma- covered potable water must be disinfected to en- terials (sorbents, catalysts, membranes, etc). The sure safe storage with biocides that don’t pose physical, chemical, and microbiological complex- long-term crew member health risks. The capa- ity and variability of wastewaters necessitate that bility to recover water from a wider range of po- they be stabilized to protect equipment from bi- tential wastewater sources can contribute to low- ological and chemical fouling-induced failure and er life-cycle costs, particularly by enabling clothes DRAFT TA06-9 laundering and reducing dependence on expend- food packaging via new materials, bulk food prep- able wipes for crew hygiene. aration, and on-orbit food production capabilities Solid waste management systems for missions to is also required for future missions. Advances in date have been limited to a “cradle-to-grave” ap- biology have the potential to revolutionize food proach, consisting of a one-time use of supplies production in space through genetic engineering followed by storage and return to Earth. Beyond of plants to increase harvest index, protein and vi- hand compression of trash prior to containment, tamin content, and growth rate, and create short- no processing is conducted. Biological growth and er, more volume-efficient crops. A key challenge concomitant odor production continue during for food production will be developing energy-ef- storage, and are managed using closed or vented ficient lighting technologies, including electrical- storage containment. While this strategy has suf- ly driven devices such as Light-Emitting Diodes ficed for past missions, including frequent down- (LEDs) or the use of captured solar light. mass return to Earth, it will not satisfy the require- Hygiene systems include partial-body cleaning ments of future long-duration missions. (hand washing, wipes), full-body cleansing (show- Enabling long-duration missions will require es- ers), and metabolic waste collection interfaces (fe- tablishing an integrated “cradle-to-cradle” strat- cal, urine, menstrual, emesis). Urine pretreatment egy that employs resource retrieval and reuse via and hygiene cleansers/chemicals must be com- water recovery, air revitalization, and other sub- patible with water recovery technologies, and the systems. Further gains can be realized by deliber- human waste collection interface must facilitate ate selection of mission consumables, packaging processing and stabilization of feces. Necessary plastics, and spacecraft materials that facilitate di- housekeeping improvements include trash/de- rect reuse or serve as feedstock for in-situ man- bris collection, surface cleaning systems, advanced ufacturing of valuable products such as radiation consumables stowage (packaging material devel- protection, spares and fuel. Such processing will, opment), antimicrobial/antiseptic recovery con- by default, 1) provide mass and volume savings; trol, and post-fire cleanup. 2) enhance mission sustainability; and 3) reduce Deep-space missions will require the ability to the amount of waste that requires safe handling, launder clothing in space. Both body hygiene and storage and disposal. Extensive waste reuse also laundry typically utilize water and a cleaning sur- decreases the amount of waste that requires pro- factant to remove salts, body oils, and dander. Re- cessing to satisfy potentially restrictive planetary covery of this high Total Organic Carbon (TOC) protection requirements. Widespread use of spe- wastewater is important to closing the water bal- cifically-designed biodegradable materials, includ- ance. A laundry system that requires minimal sur- ing bioplastics, can dramatically increase resource factants to clean clothing is desirable. Addition- recovery and reduce residue proportions. al key challenges include developing light-weight, Habitation engineering is a distinct TA directly quick-dry fabrics for crew clothing and repeated- applicable to vehicle success, but an area that his- use antimicrobial wipes that require only negligi- torically has been inadequately addressed in initial ble cleaning. vehicle system design. Current habitation capabil- Re-purposing of stowage containers has been ities were designed for LEO missions and are not proposed to minimize mass and allow reuse via optimized for resupply, reliability, mass, volume, conversion into crew items and acoustic/radiation and autonomy requirements which will be design blankets. Alternate approaches include reduction drivers for deep-space missions. in volume for disposal, or conversion to solid plas- Habitation cleaning, clothing, and consumables tic bricks by heat melt compaction for use as radi- are currently all open-loop systems, and portions ation shielding. of the loops must be closed for long-duration mis- The major challenges of each sub-element, as sions beyond LEO. Several habitation systems well as efforts required to overcome the challeng- have considerable interface with Air Revitaliza- es to develop and demonstrate the technology to tion, Waste Management, and Water Recovery TRL-6, are listed in Table 2. systems, and require improved capabilities as stat- 2.2. Extra-Vehicular Activity (EVA) ed in the paragraphs below. Other habitation sys- Systems tems are detailed in TA07, HEDS. Improved means of food preparation, rehydra- EVA systems are critical to every foreseeable hu- tion, water dispensing, and galley architecture man exploration mission for in-space microgravity concepts are needed. A significant reduction of EVA and for planetary surface exploration. In ad-

TA06-10 DRAFT dition, a Launch, Entry and Abort (LEA) suit sys- tems to supply data to enable crew members to tem is needed to protect the crew during launch, perform their tasks with more autonomy and ef- landing and cabin contamination/depressuriza- ficiency. tion events. An EVA system includes software and 2.2.1. Approach and Major Challenges hardware that spans multiple assets in a given mis- The current suit development process is ham- sion architecture and interfaces with many vehicle pered by a lack of analytical modeling to predict systems, such as life support, power, communica- combined body-suit dynamics, effects of body pa- tions, avionics, robotics, materials, pressure sys- rameters, and suit size. A high-fidelity integrat- tems, and thermal systems. AIAA publications5,6,7, provide further details of the current SOA of the ed model will allow computer simulations lead- EVA technology and challenges necessary to ad- ing to decreased development time and cost while vance this TA to conduct NASA’s planned mis- providing better-performing suits. This capability sions safely, affordably, and sustainably. The com- could also potentially lead to preventing crew in- plete EVA system includes three functions, each of jury during mission phases that require suited op- which is described below. erations. Pressure Garment – The suit, or pressure gar- Extending these capabilities to include the abili- ment, is the set of components a crew member ty to model the LEA suit-seat interface and predict wears and uses. It includes the torso, arms, legs, crew injuries during vehicle landing will enhance gloves, joint bearings, helmet, and boots. The suit crew safety and survivability. New suit materi- employs a complex system of soft-goods mobility als could potentially perform multiple functions elements in the shoulders, arms, hips, legs, torso, that may include power generation, heat rejec- boots, and gloves to optimize performance while tion, communication, dust protection, injury pro- pressurized without inhibiting unpressurized op- tection, reduced risk of electrical shock hazards erations. The LEA suit also contains provisions to (e.g., due to plasma charging), radiation protec- protect the crew member from both the nominal tion, and enhanced crew survivability. New mate- and off-nominal environments (e.g., gravitational, rials should continually be identified, evaluated in sound, chemical) encountered during launch, en- coupon-level testing, and then integrated into suit try and landing. components. Once they have been proven as a via- Portable Life Support System (PLSS) ble, effective suit component via a pressurized suit – The test in a relevant environment, they will be con- PLSS performs functions required to keep a crew sidered TRL-6. Advanced suit tests in the Neu- member alive during an EVA. These functions in- tral Buoyancy Laboratory (NBL) at JSC are an ap- clude maintaining thermal control of the astro- propriate environment for microgravity mobility naut, providing a pressurized oxygen environ- evaluations. Other reduced-gravity testing simula- ment, and removing products of metabolic output tors exist and can be used when appropriate. Vac- such as CO2 and H2O. Power, Avionics, and Software (PAS) – The uum chamber tests may also be relevant environ- PAS system is responsible for power supply and ments for suit demonstrations of concepts that use distribution for the EVA system, collecting and advanced materials. These innovations should lead transferring several types of data to and from oth- to game-changing suit configurations and archi- er mission assets, providing avionics hardware to tectures with decreased mass, improved mobility, perform numerous data display and in-suit pro- self-sizing capabilities, and/or increased life. Im- cessing functions, and furnishing information sys- proved materials may also lead to advances in mo- bility elements such as gloves, shoulders, bearings, 5 Chullen, C., and Westheimer, David T., 2010, “Extravehic- and other joints. ular Activity Technology Needs.” Paper presented at AIAA Space 2010 LEA suits could benefit from many of these Conference, Anaheim, California, August 30-September 2. types of advances in suit materials. They could 6 Conger, B., Chullen, C., Barnes, B., Leavitt, G., 2010, be donned extremely quickly in the event of an “Proposed Schematic for an Advanced Development Lunar Portable emergency, which could provide crew protection Life Support System (AIAA-2010-6038).” Paper presented at 40th In- for more vehicle failure scenarios. Integrated crew- ternational Conference on Environmental Systems, Barcelona, Spain, escape or crew-survival hardware would be benefi- July 11-15. 7 Malarik, D., Carek, D., Manzo, M., Camperchioli, W., cial as well. New designs that better integrate the Hunter, G., Lichter, M. and Downey, A., 2006, “Concepts for Ad- suit, restraints, supports, and the vehicle seat could vanced Extravehicular Activity Systems to Support NASA's Vision for greatly increase the safety of crew members. Tech- Space Exploration (AIAA-2006-348).” Paper presented at 44th AIAA nology solutions to enable long-duration suited Aerospace Sciences Meeting and Exhibit, Reno, Nevada, January 9-12. DRAFT TA06-11 operations, as in the case of a cabin depressuriza- of an integrated PLSS on ISS provides the ulti- tion event, could resolve technical challenges as- mate validation of a microgravity suit. sociated with long-duration waste management, PAS has significant opportunities to realize dra- provision of food and water, and administering matic increases in capabilities over the current medication. Emergency breathing systems incor- SOA. Key hardware constraints include mass, porating oxygen generation, rebreathers, or filtra- power, volume, and performance of existing ra- tion systems would be beneficial for emergency diation-hardened electronics. As such, there are scenarios with smoke or the release of toxic chem- many dependencies on other TASRs. For example, icals. significantly increased bandwidth and processing The PLSS is a prime candidate for infusion of requirements will exist for communications sys- new technologies to significantly reduce consum- tems. These will include a radio with networking ables, improve reliability, and increase crew per- capabilities and data rates that support the trans- formance. Regenerable technologies for removing mission of high-definition (HD) video. Integrat- moisture and CO2 from the suit lead to reduced ing speakers and microphones into the suit will consumables and mass requirements. Amine swing improve crew comfort and the reliability of the bed technology, currently being developed, can be communications system. Information systems and proven via a test on ISS in the 2016 timeframe. displays have tremendous possibilities for greatly Additional advances could include the ability to improving crew autonomy and efficiency, and ad- capture CO2 and moisture from the suit, and de- vancing the SOA. The future caution and warning liver them back to the vehicle without incurring system will have to obtain, process, and visually significant mass, volume, or power penalties. This display the affected crew member’s individual cau- would help close the loop for water and oxygen tion and warning telemetry, and that of other crew on a mission level. These advances could be made members. An integrated sensor suite including with technologies such as zeolites, nano-porous crew health diagnostics, coupled with advanced beds, or wash-coated foams. The crew member informatics, speech recognition, voice command- is cooled using a water loop that passes through ing, computing and display systems, can offer a a liquid cooling garment and also an evaporative wealth of information on crew state, external en- cooling device that vents to a space vacuum. Inno- vironment, mission tasks, and other mission-crit- vations to make this water loop robust to chem- ical information to maximize crew performance ical, particulate, or microbial contamination are and safety. Also, dramatic increases in the specif- critical to providing reliable, long-lasting systems. ic energy of future power systems are needed. PAS In addition, non-venting heat rejection technol- system demonstrations should be performed to ogies would lead to significant reduction in mis- mature selected technologies. An initial demon- sion consumables. Compact, low-mass, reliable, stration needs to be performed around 2016 to and efficient technologies need to be developed support EVA flight demonstrations and validate that can reject heat to the spectrum of thermal the maturity of technologies that could be used environments of expected exploration missions. A to support future ISS EVA activities. Additional variable set-point oxygen pressure regulator would demonstrations on ISS in the 2020-25 timeframe provide new capabilities to decrease pre-breathe need to be performed to show that technologies time, treat in-suit decompression sickness, and in- can provide the crew with the autonomy needed terface with a wide number of vehicles that may to perform missions farther and farther away from operate at different atmospheric pressures. Opti- Earth. mization of inhalation/exhalation/ventilation ar- The major technical challenges for each sub-el- chitecture could provide potential benefits for ement, as well as efforts required to overcome the umbilical-based EVA scenarios. Because the PLSS challenges to develop and demonstrate the tech- is such a highly integrated system, it is necessary nology to TRL-6, are listed in the following text to perform system demonstrations to evaluate the and summarized in Table 3. combined performance of advanced technolo- 2.3. Human Health and Performance gies. A PLSS human vacuum chamber test will be (HHP) needed to bring technologies to a maturity level that allows for a flight demonstration in the 2016 The main objective of the HHP technologies is time frame. Another PLSS vacuum chamber test to maintain the health of the crew and support should be performed to evaluate the technologies optimal and sustained performance throughout developed to reduce PLSS consumables. Testing the duration of a mission. The HHP domain in-

TA06-12 DRAFT Table 3. EVA Systems Technical Area Details Technology Current SOA/Practice Major Challenge(s) Recommended Milestones/ Activities to Advance to TRL-6 or beyond lement Sub- E

Multifunctional suit Suits comprised of multiple layers of Materials that can serve multiple functions 2013: coupon-level demo materials development materials that independently provide including eliminating suit-induced injury, functions such as structural support, protecting from electric shock, saving mass, 2020: suit-level capability thermal insulation, or atmosphere and improving suit mobility containment 2025: multifunctional materi- als with increased capabilities Suit modeling tool No integrated modeling capability Optimize suit design using combined body 2013: initial capability development exists to evaluate suit sizing, mobility, and suit modeling to predict dynamic inter- or human-suit kinetics actions between the limbs and the suit 2018: validated model Tests with human subjects and their Provide capability to evaluate multiple suit qualitative assessment is used architectures prior to finalizing design and fabrication Improved suit-seat Crew members are restrained in their Develop options for restraining and protect- 2015: Integrated suit-seat interface design seats with a harness that is applied ing crew members during violently dynamic demo over the suit mission events Personal aviation and auto racing industry advances have not yet been

Pressure Garment incorporated into space applications On-back regener- Suits use Lithium Hydroxide (LiOH), In–situ regenerable technologies that will 2014: TRL-6 component

able CO2 and humidity which is not regenerable, or Metal allow on-back regeneration and enable demo control sustained EVA

Oxides, which are heavy and require a 2020: CO2/H2O capture for power intensive bake-out in-vehicle recovery Closed-loop heat rejec- Water evaporation is vented to space Heat rejection systems with no consumables 2020: component ground tion system with zero – for missions with many EVAs this is to eliminate water loss for cooling and demo consumables a significant impact to the vehicle life decrease total mission mass support system 2025: PLSS demo Variable Set-point Oxy- Suit pressure regulators have two Capability to treat decompression sickness 2015: component ground gen Pressure Regulator mechanically-controlled set points in the suit, allow for rapid vehicle egress, demo and provide flexibility for interfacing the suit with multiple vehicles that may operate at

PLSS different pressures Miniaturized Electronic Suits use limited electronics New techniques to miniaturize electronics 2015: subsystem capability Components Demon- that enable decreased on-back mass while strated increasing the performance of suit avionics 2020: system capability demo Components need to be radiation-hardened or radiation-tolerant and cost-effective to produce Advanced Displays and Laminated data sheets and voice com- Enhanced on-suit displays, tactile data entry, 2020: helmet display Enhanced Information munications from the ground or IVA voice commanding, integrated sensors suite, Systems crew members and on-suit systems to optimize crew perfor- 2025: information system mance, mission planning, and system control based on telemetry On-suit Power Systems The silver-zinc battery provides ap- Low-mass, high-capacity energy storage to 2016: battery demo proximately 70 Wh/kg meet EVA power and mass budgets (1,100 Wh with less than 5 kg of mass ( > 220 Wh/ 2025: advanced power

PAS kg)) system cludes four functional focus areas as shown below. Behavioral Health and Performance – The ob- Medical Diagnosis/Prognosis – The objective jective in this topical area is to provide technol- of this functional area is to provide advanced med- ogies to reduce the risk associated with extend- ical screening technologies for individuals select- ed space travel and return to Earth. Technology ed to the astronaut corps and prior to crew selec- advancements are needed for assessment, over- tions for specific missions; this is a primary and all prevention, and treatment to preclude and/or resource-effective means to ensure crew health. manage deleterious outcomes as mission duration Long-Duration Health – The focus here is pro- extends beyond six months. viding validated technologies for medical practice Human Factors and Performance – This el- to address the effects of the space environment on ement focuses on technologies to support the human systems. Critical elements include research crew’s ability to effectively, reliably and safely in- and testing, including innovative use of test plat- teract within the mission environments. Elements forms such as Biosentinels and micro and nano here include user interfaces, physical and cogni- satellites, and the development of countermea- tive augmentation, training, and Human-Systems sures for many body systems. Integration (HSI) tools, metrics, methods and standards. DRAFT TA06-13 2.3.1. Approach and Major Challenges and nano satellites (Edison) and Commercial or Future human spaceflight exploration objectives International collaborative missions such as Bions. will present significant new challenges to crew Missions beyond LEO will pose significant chal- health, including hazards created by traversing the lenges to astronauts’ psychological health, includ- terrain of planetary surfaces during exploration ing confined living quarters with a small crew, and the physiological effects of variable gravity delayed communications, no view of Earth, and environments. The limited communications with separation from loved ones. Potential deleteri- ground-based personnel for diagnosis and con- ous outcomes associated with these risk factors sultation of medical events will create addition- increase as mission duration extends beyond six al challenges. Providing healthcare capabilities for months; nonetheless, some missions may last up exploration missions will require definition of new to three years. Additional technologies are need- medical requirements and development of tech- ed to identify, characterize, and prevent or reduce nologies; these capabilities will help to ensure Ex- BHP risks associated with space travel, explora- ploration mission safety and success before, dur- tion, and return to terrestrial life. These technol- ing, and after flight. ogies include 1) prevention technologies like reli- Medical systems for Exploration missions will able, unobtrusive tools that detect biomarkers of be pursued based on spaceflight medical evidence vulnerabilities and/or resiliencies to help inform generated to date, as well as research and analog selection recommendations; 2) assessment tech- populations. For each Exploration DRM, a list of nologies for in-flight conditions such as high CO2 medical conditions that have high likelihood and/ levels, high air pressure, noise, microgravity, and or high crew health consequences to mission suc- radiation that may exacerbate risk; and 3) counter- cess will be generated. Astronauts currently un- measures aimed to prevent behavioral health dec- dergo medical screening before they are selected rements, psychosocial maladaptation, and sleep to the astronaut corps and before they are chosen and performance decrements; also, countermea- for specific missions. This is currently the prima- sures aimed to treat if decrements are manifested. ry, and most resource-effective, means to ensure A successful human spaceflight program heavily crew health. depends on the crew’s ability to effectively, reliably The on-going progress made in the field of ge- and safely interact with their environments. HFP nomics, proteomics (protein), metabolomics (me- represents a commitment to effective, efficient, us- tabolites), imaging, advanced computing and in- able, adaptable, and evolvable systems to achieve terfaces, microfluidics, intracellular Nanobots for mission success, based on fundamental advances diagnosis and treatment, materials, and other rel- in understanding human performance (percep- evant technologies will significantly enhance ad- tion, cognition, action) and human capabilities dressing the medical needs of the human system. and constraints in context. The most critical el- Maintenance of HHP will require research be- ements of the HFP roadmap are 1) user interfac- fore and during flight. A number of proposed es such as multimodal interfaces and advanced vi- technologies align with today’s Medical Progno- sualization technologies; 2) physical and cognitive sis Team items and can be transitioned to medi- augmentation such as adaptive automation based cal practice once they have been fully validated. on in-situ monitoring of work activity; 3) training Other cross-cutting technologies provide signifi- methods/interfaces; and 4) Human-Systems Inte- cant value to other discipline teams – one exam- gration (HSI) tools, metrics, methods and stan- ple is artificial gravity, which is seen as a poten- dards, such as those being developed by other gov- tial game-changing technology. Aside from being ernment agencies, NASA HSI assessment tools, a promising countermeasure for many body sys- and human performance tools such as the devel- tems, development would require a new approach opment of human readiness level and related con- to vehicle design and potentially revolutionize the cepts for fitness-for-duty. way we explore space. The effect of microgravi- Table 4 identifies the essential function/technol- ty and radiation on human systems will be ascer- ogy relevant to the four sub-elements identified, tained using model systems (Biosentinels) such as current SOA/practice for the near-term planned cells, 3D-tissue, micro-organisms and small ani- missions, major challenges to mature the technol- mals and these model systems will be evaluated ogy and the potential development activity need- using robotic precursor missions with platforms ed for future missions and the time-line to elevate (including altered-gravity capabilities) planned at the potential technology, as envisioned today, to ISS, free-flyer-hosted payloads including micro TRL-6. TA06-14 DRAFT Table 4. Human Health and Performance Technical Area Details

Technology Current SOA/Practice Major Challenge(s) Recommended Milestones/Activities to Advance to TRL-6 or beyond Condition Specific Astronauts are screened Conditions exist that current medical 2012-20: Early screening technologies for dental Screening Technology for physical and psycho- technology cannot detect far enough in emergencies, subclinical medical conditions includ- logical conditions advance ing malignancies, cataracts, individual susceptibility levels to radiation and carbon dioxide exposures, osteoporosis, oxidative stress and renal stone for- mation, sleep disorder, anxiety and depression. In a phased-fashion, the development in the identified areas will be implemented Genetic/Phenotypic Not in practice for selec- Ethically acceptable screening technolo- 2015-25: Screening technologies to personalize Screening tions gies in-flight medical planning and care Autonomous Medical Screen-shots of paper Lack of standards in data output from vari- 2012-20: Handheld, smart device that integrates Decision procedures ous medical instrumentation with vehicle, hardware, patient, care giver and Mis- sion Control Integrated Biomedical Separate systems that do Integrated standards 2012-20: Integrated electronic medical records, Informatics not seamlessly interface medical devices, inventory management system, procedures and utilizes a medical hardware com- munication standard Virtual Reality Patient Does not exist for space- Modular embedding of the technology 2015-25: Capability for crew members to practice Simulator and Trainer flight just-in-time medical training on a system that accu- rately represents a patient’s body in microgravity Medical Assist Robotics Does not exist for space- Automated laproscopic surgery; advise 2015-25: Capability to develop Medical Assist flight physician of treatment options Robotics Biomedical Sensors Wet-electrodes; multiple Interference from multiple systems; Signal 2012-20: Minimally-invasive diagnostic sensor suite systems for EVA, exercise sensitivity that is easily donned/doffed (e.g. shirt). Systems to and medical assess the physiology of the eye, skin, and brain non-invasively Advanced Scanner Ultrasound with guidance Size, sensitivity and comprehensive nature 2015-25: Non-ionizing, full body, dynamic, three- from the ground dimensional (3-D) imaging with in-situ diagnosis and treatment capabilities (e.g., renal stone abla- tion) Surgical Suite Does not exist for space- Logistics 2015-25: Sterile, closed-loop fluid and ventilation flight systems for trauma and other surgeries Artificial Gravity Does not exist for space- Establishing ground analog study; Cost 2015-20: Prescribed exposure to artificial gravity flight impact to develop space-flight systems that may reduce or eliminate the chronic effects of microgravity 2020: Ground Demo Novel Drug Delivery Pills, injections, ointments In-situ synthetic biology capability for less 2015-20: Drug and Biomaterials manufacturing Mode invasive and more efficient drug delivery using synthetic biology Portable In-flight Bio- Dry chemical strips, Biological sample collection; research- 2012-16: Miniaturized Analyzer sample Analysis portable clinical blood grade water; sample and reagent storage; 2014: Research Grade Water analyzer integrated, portable, hand-held, in-flight 2016: Miniaturized Microscopy Unit bio-sample analysis (micro-fluidic flow 2018: Sample Processing and Storage Samples returned to cytometry; gene expression and proteomic 2014-19: In-flight proteomic analysis ground for analysis in labs analysis; microscopy; spectrophotometry/ 2016-21: Mass spectrometry fluorometry, mass spectrometry); real-time feedback on crew health status Cell/tissue Culture, Limited, primarily Experi- Small, autonomous, pioneering explora- 2013/2016: Bion M2/M3; 2012-2021 (ISS Annual): animal Models ment-Unique Equipment tion satellites using cells or small animal 2018 Biosentinels Flight Demo (EUE) models to assess impacts of long duration 2012-2018: Biosentinels – small, autonomous, exposure of microgravity and radiation to pioneering exploration satellites using cells or small living organisms animal models to assess impacts of long duration exposure of microgravity and radiation to living organisms prior to or in conjunction with human DRMs Induced Pluripotent Stem Does not exist for space- Individualized IPS based Stem cell replace- 2012-16: Individualized stem cell replacement tool Cells (IPS) flight ment to enable longer mission duration kit for specific DRMs 2016-21: IPS for anti-radiation therapies Cost effective breakthroughs in anti- radiation therapies Exercise Equipment and Uses large vehicle Small, robust equipment. High efficacy 2012-2019: Development of concepts and proto- Methods resources with high return for long duration missions types for integrated exercise-based countermea- High crew time sure systems Non-exercise counter- Limited countermeasures Robust, efficient and validated nutritional, 2012-19: Pharmaceutical countermeasures measures radio-protective, and pharmacological 2012-15: Nutritional countermeasures countermeasures 2015-23: Radio-protective countermeasures Separation and isolation Crew members call home, Individual variation in response 2023: Virtual Reality technologies (i.e., “Holodeck”) from home photograph Earth from to provide “back-home” connection; Earth-like ISS scenery

DRAFT TA06-15 Technology Current SOA/Practice Major Challenge(s) Recommended Milestones/Activities to Advance to TRL-6 or beyond Lack of environmental No continuous monitor- Passive monitoring of crew health and per- 2015: Sleep Monitoring detection system control; stress/sleep loss ing formance (e.g., vital signs, exercise, waste 2015-2019: Interfaces with other measures to per- products, sleep, exercise work-load) sonalize aspects of habitat/vehicle such as lighting, noise, temperature Depression, conflict, Sleep medications, con- Identification of early symptoms 2015-19: Next-generation “Virtual Therapist” for insomnia ference with Flight Sur- autonomous missions to treat behavioral health, geon and/or Psychiatrist team cohesion, and sleep decrements and provide crew with surgeon’s care Advanced User Interface Interactive visualization, Selection/ development of interfaces 2011-14: Seamless human system interaction for (UI) Concepts multimodal technologies for unique spacecraft environment (e.g., NEO missions; Smart habitat interface concepts; (haptic, auditory, visual), high-g, low-g, zero-g, high vibration, pres- Adaptive Habitat Design Tool for Human-in-the- Displays and Controls intuitive wireless controls, surized and unpressurized suited) Loop (HITL) evaluation; Proof-of-concept (PoC) for (D&C) Smart Habitats HRI, smart habitats advanced HRI (robotic arm, rover) Human-Robotic Interac- Effective, low cost/mass/volume/power 2015-18: Advanced UI for planetary; PoC for tion (HRI) integrated systems for human spaceflight advanced HRI for aerial; Population analysis /Biome- chanical countermeasures Scalability to real-time scientific and 2020-29: Advanced HRI in-flight demo; Implemen- engineering data tation (spin-offs) and augmentation as necessary augmented by crop systems Physical, Cognitive and Radio Frequency Iden- Effective, low cost/mass/volume/power 2011-15: Wearable computing in-flight demo; Cog- Behavior Augmentation tification (RFID), motion integrated systems for human spaceflight nitive aids/adaptive automation in-flight demo; PoC (including Training and tracking, wireless com- tools for remote collaboration; just-in-time training Maintainability) munication 2012-16: (NEO) / 2017-19 (planetary): Physical augmentation/ countermeasure technologies; Tele-operations, remote Wearable computing, Technology for sensorimotor augmentation, Habit- operations adaptive training and ability Rating Tool decision support systems, 2020-29: Implementation (spin-offs) and augmen- tele-operations tation as needed Human System Integra- Other Governmental Effective transfer/ evolution of other 2011-12: HSI Scorecard Prototype for HSI cost & tion (HSI) Tools, Methods, Agencies’ activities governmental agencies’ approaches to a benefit assessment Standards model effective to NASA environment and 2015: HSI implementation and augmentation as NASA HSI Score Card; HSI culture. needed within human spaceflight technology Standards development programs/projects Direct application of commercial tools and methods in space environment. 2.4. Environmental Monitoring, Safety, biological environments of the crew living areas and Emergency Response (EMSER) and their environmental control systems. Exist- The goals of the EMSER effort are to develop ing technologies will not meet the needs of future technologies to ensure crew health and safety by exploration for LEO and beyond, for which lo- protecting against spacecraft hazards, and for ef- gistical resupply will be impractical and mission fective response should an accident occur. This lengths will be far greater, necessitating greater in- area includes four functions, which are further di- dependence from Earth. Crew time spent moni- vided into sub-elements, as described below. toring and controlling the spacecraft environment Fire Prevention, Detection, and Suppression must be reduced. Related technologies in physi- – The goal of spacecraft fire safety is to develop cal, chemical, and biological monitoring and ad- technologies to ensure crew health and safety by vanced control must be assembled and must be reducing the likelihood of a fire, or, if one does oc- tied synergistically to provide necessary technol- cur, minimizing the risk to the crew, mission, and/ ogies for future human space exploration. NASA or system. This is accomplished by addressing the and NRC documentation8,9,10, , provide more de- areas of materials flammability in low- and partial- gravity, fire detection, fire suppression, and post- 8 Committee for the Decadal Survey on Biological and fire cleanup. These topics will be even more criti- Physical Sciences in Space, Aeronautics and Space Engineering Board cal for long-duration exploration missions as rapid (ASEB), Division on Engineering and Physical Sciences (DEPS), return to Earth is not an option and the ability National Research Council of the National Academies (NRC), 2010, to safely continue the mission will substantially “Life and Physical Sciences Research for a New Era of Space Explora- tion, An Interim Report,” Washington, D.C.: The National Academies increase the probability of mission success. This Press. must be accomplished without adding complexity 9 Committee to Review NASA’s Exploration Technol- to the fire response process or increasing required ogy Development Program, Aeronautics and Space Engineering Board consumables. (ASEB), Division on Engineering and Physical Sciences (DEPS), Sensors – The focus of the sensors task is to National Research Council of the National Academies (NRC), 2008, provide future spacecraft with advanced, micro- “A Constrained Space Exploration Technology Program: A Review of miniaturized networks of integrated sensors to NASA's Exploration Technology Development Program,” Washington, monitor environmental health and accurately de- D.C.: The National Academies Press. termine and control the physical, chemical, and 10 “Life Support and Habitations Systems (LSHS) Project Plan,” Draft 2010. TA06-16 DRAFT tails of sensor technology and challenges necessary exist with the space science instrument commu- to advance this technology area. nity. Challenges in the sensor area may be met by Protective Clothing / Breathing – The focus a combination of technologies. Differential Mo- here is to provide crew sufficient capability to ad- bility Spectrometry (DMS) and miniaturized ion- dress off-nominal situations within the habitable trap mass spectrometry can potentially serve as the compartments of spacecraft. Off-nominal events basis for environmental monitoring instrumenta- include fire, chemical release, microbial contam- tion. Because of their small size, low power require- ination, and unexpected depressurization. Exist- ments, and broad applicability, so-called “hyphen- ing technologies will not meet the needs of future ated analytical techniques”, such as DMS-MS, exploration, which requires greater independence electro-spray ionization (ESI)-MS, and even ESI- from Earth, in which logistical resupply is not DMS-MS, can be realized for space applications. practical. Advancements are needed to reduce With a properly designed sample preparation/in- weight and cost, yet still provide effective protec- let system coupled to any one of these “hyphen- tive clothing and breathing capabilities that may ated analytical techniques”, it is highly possible to be deployed when needed. create a single “suite” of sensors applicable to at- Remediation – The focus of remediation is mospheric, water, and microbial monitoring. In to provide crew the ability to clean the habit- all cases, space needs are more constraining than able environment of the spacecraft in the event terrestrial needs in terms of mass/volume and long of an off-nominal situation. Off-nominal events term reliability, including the need to stay in cal- would include fire, an inadvertent chemical re- ibration. lease, or microbial contamination. Advancements The SOA in protective clothing/breathing and are needed to reduce weight and cost over current remediation technologies for in-flight off-nomi- methods, yet still provide effective remediation ca- nal events relies heavily on the ability to resup- pabilities that may be deployed when needed. ply. Since resupply is highly unlikely, protective 2.4.1. Approach and Major Challenges clothing/breathing and remediation technologies The major challenge for fire research is predict- must be effective, regenerable (if applicable), and ing flammability in low-pressure and partial-g en- be able to be deployed by crew in various off-nom- vironments, as materials can burn at lower oxygen inal situations. Typically, methods to regenerate concentrations than they do in normal gravity. current materials employ heat to desorb contam- This means that materials that are non-flammable inants from the surface, thereby increasing power in normal gravity in certain configurations may requirements. Metallocenes and hybrid organic- actually allow a flame to propagate in low- or par- inorganic catalysts have been shown to immo- tial-gravity in those same configurations. Early fire bilize contaminants. Combining this capturing detection improvements to minimize false alarms ability with the ability to undergo light-induced require both particulate and gaseous species detec- conformational changes in the geometry of the tion, as well as distributed sensors. Reduced size catalyst, regenerable remediation technology may and power consumption of both particulate and be possible with very low power requirements. Al- gaseous species sensors, as well as increased infor- though these technologies are at the research lev- mation content and sensor lifetime, are also re- el, they are representative of the type of develop- quired for this capability to be realized. Potential- ment required for future missions. Improvements ly, these fire detection systems could be combined are needed to evolve coveralls and gloves that are with sensors to monitor post-fire cleanup, there- resistant to fire, chemicals, and microbes. by reducing mass and simplifying crew emergen- The major challenges of each sub-element, as cy operations. well as efforts required to overcome the challeng- The approach to environmental monitoring sen- es to develop and demonstrate the technology to sor technology development is to leverage the rap- TRL-6, are listed in Table 5. idly advancing communities in microelectronics, 2.5. Radiation biotechnology, and chem/bio terrorism defense. The radiation area is focused on developing The focus will be on adapting for reliable long- knowledge and technologies to understand and term operation in the space environment, as well quantify radiation health and performance risks, as reducing size and mass without sacrificing capa- to develop mitigation countermeasures, and to bility. In some cases, NASA-unique needs will re- minimize exposures through the use of material quire unique solutions. Leverage and overlap will shielding systems. Possible other improvements

DRAFT TA06-17 Table 5. Environmental Monitoring, Safety and Emergency Response Technical Area Details

Technology Current SOA/Practice Major Challenge(s) Recommended Milestones/Ac- tivities to Advance to TRL-6 or beyond Development of a pre- Assessment of material flammability in A low-g analog test and predictive 2019: Predictive ground-based dictive technology for normal-gravity at highest operational capability must be defined and verified low-g tests and modeling to evalu- low- and partial-gravity oxygen concentration ate material characteristics that lead material flammability Verification of the flammability limit to increased flammability hazards in at length and time scales relevant for low- and partial-gravity spacecraft 2022: Verification of the development and propagation of relevant-scale low-g fires Hybrid gaseous Non-discriminate particulate detection; Development of small, low-power gas 2016: Assessment of smoke and and particulate fire smoke filtering and dedicated instrument to and particulate sensors for fire detection gaseous fire signatures from low-g

detection and post-fire monitor CO, CO2, and HX during clean-up fires monitoring Realistic-scale fire scenarios and post-fire Realistic spacecraft fire and post-fire chal- challenge for spacecraft 2021: Development of a distributed lenge does not exist hybrid fire detection system 2022: Verification of the develop- ment and propagation of relevant-scale low-g fires Autonomous 2-kg air 55-kg Major Constituent Analyzer Need ability to analyze complex mixtures 2020: Flight test on ISS Monitor for Trace Gases capable of handling unknowns and Major Constituents 25 kg Vehicle Cabin Air Monitor (VCAM) Need system to perform sample analysis Gas chromatography-mass spectrometry and data analysis routinely, alerting crew experiment) only when necessary 3-kg Air Size about 2 kg (i.e., 70-80% size Quality Monitor (gas chromatography-dif- reduction beyond SOA; life tested for ferential mobility spectrometry, trace gases Mars mission only, ISS Detailed Test Objectives (DTO)), ground analysis of returned samples Airborne Particle Ground analysis: 0.01 mg/m3, integrated Real-time monitors with binning 2020: Flight test on ISS Monitoring mass measurement for 0.3-10 micron capability for fine (300 nm-10 microns) particles and ultrafine (30 nm-1 micron) 2030: Next Gen Tech Demo particulates Multi-analyte Technol- Cannot perform analysis in flight; cur- Need sample processing and analysis (2020): Non-chromatographic ogy for Stand-Alone rently perform Ground analysis of returned system to extract, concentrate, and method to speciate analytes Water Quality Mea- samples aerosolize samples and analyze complex surements and TOC unknown mixtures and alert crew only (2020): Complementary non-mass Monitoring when necessary spectrometric analysis capability Need low mass, low power, and no 2030: Flight test on ISS consumables Microbial Detection for Flight analysis: Microbial Air, Water, and Sur- <12 hour results equivalent to current 2020: Flight test on ISS – include Air, Water, and Surface face Sampler Kits: Plate culture enumeration culture methods; identify key organisms; sample preparation and molecular only (2-7 days), coliform test (2 days) lower mass; decreased crew time identification technology Ground analysis of returned samples Need sample processing system for automated sampling and culturing Multi-Use/Multi-Func- Ammonia / Fire Respirator Need respirator for first response to fire 2021: Flight tests on ISS of candidate tion Respirator System and chemical emergencies with technology and Mask Portable Breathing Apparatus delivering communications and ability to plug into

100% O2 for 15 minutes air source. Need multipurpose, regenerable, car- tridge for fire and chemical response Need air masks with portable air supply Portable, Activated Charcoal filters, High-Efficiency Need for portable, regenerable 2019: Integrated Regeneration Regenerable Air Particulate Air (HEPA) filters, and fan units remediation system with high system testing in flight like Remediation throughput conditions Technology Microbial Remediation Benzalkonium chloride wipes Need for contingency, remediation 2025: Integrated system testing of Technology method to ensure all affected areas are portable, non-solvent-based sufficiently cleaned microbial remediation system on ISS Post-Fire Remediation LiOH cartridges; Ambient Temperature Cata- Need for portable, regenerable 2020: Verification of post-fire and Recovery lytic Oxidizer; fan assembly; wipes; Monitor remediation system that can remove, challenge

CO, CO2, and HX (combustion products) combustion products and fire extinguishing material 2023: Test of spacecraft post-fire environment and cleanup Identification and characterization of a procedures at relevant scales relevant partial-g post-fire challenge (2025): Test a “beyond LEO” fire Identification of gaseous and particulate recovery system (separate from species to monitor for post-fire cleanup ECLSS)

TA06-18 DRAFT include combining shielding with biological flight data, radiation mitigation measures, space countermeasures for enhanced effectiveness, de- weather forecasting, radiation protection, and ra- velopment of higher-fidelity space radiation mon- diation monitoring. NASA has developed and itoring capabilities in the form of miniaturized operates the NASA Space Radiation Laborato- active personal dosimetry, and to aid in crew se- ry (NSRL) at Brookhaven to simulate GCR and lection and operations for long-duration, human SPEs. Without accurate risk projection models, missions beyond LEO. the effectiveness of shielding materials for GCR, Exposure to the space radiation environment mitigation measures, and crew selection criteria poses both acute and chronic risks to crew health are poorly defined. The accuracy of risk models and safety that have clinically-relevant, lifelong must improve as the level of risk increases from implications. The major health and performance ISS to NEO to Mars in order to achieve neces- risks from radiation exposure include radiation sary technologies and to ensure crew safety fac- carcinogenesis, acute syndromes, acute and late tors. NASA and NRC documentation12, 13, 14, provide central nervous system (CNS) effects, and degen- more details of the Radiation technology and chal- erative tissue (e.g., cardiac, gastro-intestinal, circu- lenges necessary to advance this technology area. latory) effects. The major technical challenge for 2.5.1. Major Approach and Challenges future human exploration is determining the best A major challenge for radiation will be to acquire way to protect humans from the high-charge and sufficient ground and flight data on living systems high-energy galactic cosmic radiation (GCR) per- exposed to the relevant space environment, in or- meating interplanetary space. With our current der to develop models to accurately predict radi- knowledge base, the need to proactively provide ation risks, identify genetic selection factors, and mitigation technologies (such as biological coun- develop mitigation measures for remaining risks. termeasures and/or shielding) against GCR occurs A major advance is required to reduce the biolog- beyond LEO for missions greater than ~90 to 100 ical uncertainties associated with Radiation Risk days to remain below Space Radiation Permissi- Projection Models for both NEO and Mars mis- ble Exposure Limits (PELs)11. Exposure estimates for both short-stay (600 days) and long-stay (900 sions so that an optimum use of shielding de- days) Mars missions are estimated at about three signs, mission length, crew selection and mitiga- to five times above PELs. This technical challenge tion measures, such as biological countermeasures is extremely difficult because 1) GCR-heavy ions (BCM) can be developed. Research is on-go- cause damage at the cellular and tissue levels that ing today and likely needs to continue for two is largely different from the damage caused by ter- more decades to gather sufficient data to develop restrial radiation (such as x-rays or gamma rays), as these models with acceptable uncertainty levels. it has significantly higher ionizing power and large New molecular/genetic based systems biology ap- associated uncertainties exist in quantifying bio- proaches will be needed to achieve the uncertain- logical response; and 2) shielding GCR is much ty levels required for a Mars mission. Understand- more difficult than shielding terrestrial radiation, ing the genetic/epigenetic factors for major risks due to severe mass constraints and GCR ability such as lung cancer could substantially lower mis- to penetrate shielding material (high-charge and sion costs through crew selection or BCM design high-energy). reducing shielding mass requirements. Significant Shielding from solar particle events (SPEs) is advances are required to integrate fundamental re- much easier than shielding from GCR. Protect- 12 Committee for the Decadal Survey on Biological and ing humans from SPEs may be a solvable problem Physical Sciences in Space, Aeronautics and Space Engineering Board in the near-term through technology maturation (ASEB), Division on Engineering and Physical Sciences (DEPS), of identified shielding solutions, through design National Research Council of the National Academies (NRC), 2010, “Life and Physical Sciences Research for a New Era of Space Explora- and configuration. However, mission operational tion, An Interim Report,” Washington, D.C.: The National Academies planning has a major knowledge gap of forecast- Press. ing the occurrence and magnitude, as well as all- 13 Committee on the Evaluation of Radiation Shielding for clear periods, of SPEs. Space Exploration, Aeronautics and Space Engineering Board (ASEB), Primary radiation technologies requiring ad- Division on Engineering and Physical Sciences (DEPS), National Re- vancement include those related to radiation risk search Council of the National Academies (NRC), 2008, “Managing projection models using validated ground and Space Radiation Risk in the New Era of Space Exploration,” Washing- ton, D.C.: The National Academies Press. 11 “NASA-STD-3001, NASA Space Flight Human System 14 NASA Office of Program Analysis and Evaluation, 2006, Standard - Volume 1: Crew Health,” 2007. “Report of the Radiation Study Team.” DRAFT TA06-19 search on the cell, molecular, and tissue damage will be need to be developed for long-duration caused by space radiation into modeling of major missions. Further advancements in the design and signaling pathways causative of cancer, CNS, and development of miniaturized personal dosimeters degenerative diseases. for crew and small low-power active radiation in- Advancements in the design of integrated radi- strumentation and advanced warning systems for ation protection systems will be needed and the spacecraft will also be needed to minimize and goal is to optimize systems to achieve a 20% re- monitor exposures during operations. Also, in- duction in exposure to GCR. The types of materi- sufficient knowledge exists about the amount of als that protect humans against radiation are well protection provided by the Mars atmosphere. The known but mission designers will need to take a Mars radiation environment may be more severe cross-disciplinary, integrated systems approach to than previously estimated due to the production develop lightweight, cost effective multifunction- and transport of neutrons, mesons, muons, and al materials/structures that can minimize GCR ex- electromagnetic cascades. Effects of a mixed field posure while providing other functionalities like environment (neutrons and charged particles) on thermal insulation and/or Micro-Meteoroid Or- radiobiological risks are unknown. Updates to bital Debris (MMOD) protection. It is generally transport codes and in-situ pre-cursor data are re- accepted that shielding cannot completely protect quired to validate environmental models. against GCR and that biological countermeasures The major challenges of each sub-element, as Table 6. Radiation Technical Area Details Technology Current SOA/Practice Major Challenge(s) Recommended Milestones/Activities to Advance to TRL-6 or beyond Radiation Risk As- Cancer models developed to Transition basis of radiation risk modeling from 2020: Utilize the ISS for groundbreaking sessment Modeling date have 3.5-fold uncertainty one based on terrestrial exposures (current SOA) to studies on the whether the effects of a predictive systems biology model approach for radiation modified by microgravity on No computational models exist long-duration missions cellular and metabolic activities within to quantify CNS or degenerative relevant higher order biological organ- tissue health and performance Need to reduce cancer uncertainty projections isms or systems risks. No integrated mortality for NEO mission to 100% and for Mars to 50% risk projection model exists. uncertainty 2020: Perform ground based radiation Relationship between radiation biology research to develop and validate and other space stresses needs Integrate fundamental research on space radiation risk models to be further clarified biological effects into model and data bases of major signaling pathways causative of cancer and 2030: Identify need for countermea- Current models predict organ other damage sures and/or selection of crew based on exposures to +15% accuracy individual sensitivity Need to develop new molecular/genetics-based sys- tems biology approach to achieve <50% uncertainty 2025: Flight demo to validate under- levels required for a Mars mission standing of synergistic effect of space- flight on integrated risk projections), Ground radiation facilities do not duplicate space including experiments on ISS and radiation environment in terms of combination of partnering on international flight energies and duration of exposure which indicates opportunities such as 2013/2016: Bion that flight tests are required to validate data M2/M3; 2012-2021 (ISS Annual): 2018 Biosentinels Flight Demo Develop experimental methods/techniques and models to verify integrated risk and to Understand synergistic effects of other spaceflight stressors (microgravity, reduced immune system response, etc.) combined with radiation Radiation Mitiga- Radiation exposures exceed the Need detailed understanding of the mechanisms 2035: Perform tests for a range of radia- tion/Biological NASA PELs by three to five times that cause damage tion qualities and mixed fields represen- Countermeasures for 1,000-day Mars missions, and tative of GCR and SPE for sufficient are exceeded for most NEO mis- Need to develop breakthrough biological/pharma- number of biological models to sions as well ceutical radio protective agents extrapolate to humans Some agents exist to protect Need to verify extrapolation from models to 2035: Drug discovery research against acute low LET radiation humans 2035: Develop databases and computer No countermeasures exist for Need to develop an individual sensitivity toolkit to models to determine genetic sensitivity chronic GCR or intermediate SPE optimize BCM and enable longer missions to radiation risks based on animal testing dose rates and modeling and extrapolate to crew Need to understand interaction/impact of one BCM selection and BCM optimization on other spaceflight risks 2035: Research individualized stem cell replacement therapies Space Weather No ability to predict onset and Ensure data streams needed as input for forecasting 2030: Development of real-time moni- Prediction evolution of SPE models are provided toring and forecasting space weather model(s), to include prediction of onset Real–time monitoring should be Application of SPE research and transition of and evolution of Solar Particle Event as adequate for large events since research models to real-time operational decision- well as all clear periods doses are small in first one hour making tools for 99% of historical SPEs 2030: Develop forecasting tools to define ‘all-clear’ periods for EVAs Data sets exist but need to and < 1 AU trajectories for missions develop forecasting models

TA06-20 DRAFT Technology Current SOA/Practice Major Challenge(s) Recommended Milestones/Activities to Advance to TRL-6 or beyond Radiation Protec- Radiation shielding systems must Optimize multifunctional shielding system to 2014: Development of an integrated tion Systems be developed to minimize mass achieve a 20%-30% reduction in GCR exposure systems approach to radiation shielding for SPE and GCR shielding systems that implements a smooth Integrated Systems approach to mass efficient SPE transition from research to operations Shielding alone will not com- shielding and lays the groundwork for an ‘end-to- pletely protect against GCR for end’ solution to radiation shielding long-duration missions Ultimate value of shielding material types and amounts require accurate risk projection models 2016: Development of miniaturized active personal dosimetry permitting measurement as a function of charge and energy 2017: NSRL validation data for GCR simulations 2017: Characterize the interior environ- ment of habitat on Inflatable flagship mission technology demonstration 2025: Continue development of material systems to provide maximum shielding possible Monitoring Pre-flight and EVA crew exposure Active Personal Dosimetry and Monitoring for IVA ETDD Flight Demo for testing of minia- Technology and projections (passive detectors for and EVA operations. Miniaturization of electronics turized personal dosimeters Validation individual astronaut dosimetry) and sensor technologies required for compact, low power radiation dosimeters/monitors 2017: Inflatables Flagship Mission for Comprehensive crew exposure testing of charged particle and neutron modeling capability Compact, low power, charged particle and neutron spectrometers and in situ warning spectrometers that can used on missions beyond dosimetry systems Evaluation of radiological safety LEO. Ruggedization, redundancy, and fail safe with respect to exposure to performance. Fail safe data storage and transmis- Development of measurement package isotopes and radiation produc- sion for long term use without resupply or repair to be used on robotic precursors mission ing equipment carried on the during missions to NEO, Moon, Mars spacecraft In situ active warning and monitoring dosimetry, ETDD Flight Demo for testing of miniatur- Large mass/volume instru- and passive, wherever there is a human presence ized in-flight biodosimeters technologies ments using to characterize and beyond LEO. Improved battery technology for quantify the space radiation personal dosimeters that allow long wear periods environment that utilize continu- without recharging ous vehicle power Compact biological dosimetry technologies that Laboratory based cytogenetic can be used in-flight on long duration missions. evaluations (chromosome aber- Novel techniques to determine energy and charge rations) post flight of incident radiation fields in compact form factor Determination of relevant biomarkers/biodosim- eters (HRP) for early and late radiation effects well as efforts required to overcome the challeng- 4. Possible Benefits to es to develop and demonstrate the technology to Other National Needs TRL-6, are listed in Table 6. Many of the proposed technologies identified in the roadmap can lead to improvements in the 3. Interdependency with quality of life here on Earth, creating benefits of Other Technology Areas national and global interest. First, life support and The OCT Roadmapping activity is intended habitation technologies focus on developing reli- to identify overlaps with other TAs, and for the able, closed-loop systems to minimize resources topical areas of TA06, HLHS, many such over- and energy use while maximizing self-sufficiency. laps exist. Notably, the greatest overlap occurs These systems provide significant opportunity for with TA07, HEDS, and the reader is referred to knowledge transfer in numerous terrestrial areas the start of Section 2 for a detailed delineation be- including: climate change mitigation, emergen- tween these TAs. The other priority crossover is cy response, military operations, energy efficient with TA12, Materials, Structural and Mechanical buildings and “cradle-to-cradle” manufacturing. Systems, and Manufacturing, as advanced mate- One example is the potential for complete waste- rials for radiation protection, spacesuits, etc., are water recovery to potable standards for military, addressed there. Notably, it is a critical area for remote and water-scarce regions, and disaster re- collaboration to ensure an integrated systems ap- lief, with the potential for simultaneous ener- proach for radiation shielding and other HLHS gy production. Additionally, technologies iden- technology developments and for their successful tified may provide 1) efficient methods for CO2 implementation. Further discussion and/or col- capture, conversion, sequestration, and advanced laboration across the TAs is recommended. contaminant removal/destruction and particulate

DRAFT TA06-21 Table 7. Technical Area Interdependencies Technology Area Overlapping Technology Descriptions TA02: In-Space Propulsion Systems Tanks for high pressure gas storage and/or cryogenics; if tanks are “shared” then purity is an issue for ECLSS use For cryogenics, issues include zero-g or low-g management/boil-off control (*also overlap with TA03 and TA14) TA03: Space Power and Energy Stor- Tanks for high pressure gas storage and/or cryogenics; see description under TA2 (*also overlap with TA14) age Systems Low mass, high efficiency, long life, high reliability, etc. batteries for EVA/suits and/or human habitat/vehicle power systems

High efficiency electrolyzers for production of2 O and/or potable water TA04: Robotics, Tele-robotics and Human factors (e.g., immersive visualization) and human/robot interaction and automation systems Autonomous Systems (e.g., human-robot interfaces for remote operations) Medical-assist robotics Human safety enhancement (e.g., robotic surveying and remote operations) TA5: Communication and Navigation Very high bandwidth communication systems (e.g., telemedicine, software uploads) Systems TA07: Human Exploration Destination Manufacture of components, tools, soft goods (e.g., o-rings, seals) etc/3D model Printing; see description Systems (HEDS) under TA12 Research grade water production/recycle/reuse for research platforms/needs Integrated Habitat Systems (e.g., lighting, acoustics, advanced habitat materials) EVA mobility (e.g., rovers), interfaces (e.g., suitport/lock), and tools Virtual reality/Holodeck (e.g. STAR TREK) technologies for training, etc. Radiation protection materials and/or structures/architecture using in-situ resources (*also overlap with TA12) Contamination control and housekeeping (e.g., dust) Artificial gravity devices/architecture (e.g., rotating vehicle, centrifuge chair) In- situ or remote food production and processing TA10: Nanotechnology Nano-systems/sensors for non-invasive physiological monitoring of crew and/or medical treatment Advanced batteries for EVA suits (*also overlap with TA3) Nanoporous and/or other advanced nano-engineered materials/structures for ECLSS and/or other human-related applications (e.g., CO2 removal, water filtration, radiation protection, environmental and/or constituent sensors) TA11: Modeling, Simulation, Human, environmental, subsystem and overall vehicle monitoring and data management systems Information Technology and Processing Models and simulations/simulators for human and systems performance

TA12: Materials, Structural and Materials compatible with future ECLS environment of 8 psi (reduced pressure) and 32% O2 (enriched oxygen) Mechanical Systems, and Manufacturing Multifunctional materials and/or structures, including combined structural and radiation protection, microbial control (e.g., materials and/or coatings), and other examples: • The “water wall” concept envisions incorporating water required for life support into the vehicle structure to eliminate the extra mass of water tanks and provide additional radiation shielding in specific locations (e.g., crew quarters, storm shelter) • The idea is to build spacecraft internal structures (struts, secondary structure, avionics boxes, seat cushions,

etc) out of materials that can, for example, absorb CO2. If enough of the materials could be incorporated into the spacecraft and preserved throughout ground processing (or “regenerate” its capacity prior to

launch), then for short missions the spacecraft structures could absorb all the CO2 from the atmosphere Manufacture of components, tools, soft goods (e.g., o-rings, seals) etc./3D model printing; in space for increased reliability, to reduce spares, etc., similar to a STAR TREK replicator (*also overlap with TA7) Materials Flammability associated with advanced materials testing, and update(s) to MSFC-HDBK-527, Materials Selection List for Space Hardware Systems TA14: Thermal Management Systems High-efficiency, non-degradable condensing heat exchangers and lightweight radiators Non-venting, closed heat rejection system with no consumables for EVA/suits Tanks for high pressure consumables and/or cryogenics, including issues include zero-g or low-g management/ boil-off control (*also overlap with TA02 and TA03) management for climate change mitigation, mine ployments, disaster response, and temporary re- safety, enclosed spaces, military applications and mote science lab operations; and 4) advanced synthetic fuel production; 2) advanced controlled strategies for waste minimization, “cradle-to-cra- agriculture systems, which minimize energy, water dle” manufacturing and reuse, hazard reduction use and growing area, can contribute significantly and energy recovery to decrease use of natural re- to future global food production needs; 3) light- sources and landfills weight, deployable, inflatable, interior structures Previous and recent space suit technologies have provide rapid shelter construction for military de- provided materials and manufacturing techniques TA06-22 DRAFT that have led to significant improvements in com- mercial products, like athletic shoes, and special- ized items that benefit many, like efficient man- ufacture of pharmaceuticals. Other examples include therapeutic suits for people with medi- cal needs, protective suits like those for race car drivers and firefighters, life-saving gas and chemi- cal masks, lighter-than-air (LTA) vehicles. It is an- ticipated that the spacesuit technologies identified herein could have similar impacts as well. Technologies for HHP may lead to smaller por- table analysis and imaging units that could be used in austere/harsh environments, or even in rural settings without access to large medical fa- cilities. Also, countermeasures developed for space are likely to impact clinical practice by providing a better understanding of how the body works, and new tools to influence both wellness, and treat- ment of diseases. Technologies for enhanced crew interfaces and autonomy will have the potential for use in extreme environments. Any biological innovations or breakthroughs would also be of interest to the National Institute of Health (NIH), having the potential to signifi- cantly improve life on Earth. Technologies for ra- diation may help cancer patients suffering from radiation treatments, and increase understand- ing of early onset of diseases of old age and pro- vide preventive measures to delay or block their appearance. Other example benefits are for environmental monitoring, where technological advances can im- prove fire detection and are relevant to homeland security for detection of hazardous aerosols. Also, the development of microbial and chemical sen- sors can easily translate to multiple applications, such as analysis of water sources for potability in remote locations (such as rural America), medical analysis of military personnel and the general pub- lic, submarine air/water monitors, and rapid iden- tification of bio-terrorist attacks on the military and general public.

DRAFT TA06-23 Acronyms PLSS Portable Life Support System 3-D Three Dimensional PoC Proof-of-concept AMPM Agency Mission Planning Manifest RFID Radio Frequency Identification ANC Active Noise Control SOA State-of-the-Art BCM Biological Countermeasures SPE Solar Particle Events BHP Behavioral Health and Performance TA Technology Area CFD Computational Fluid Dynamics TABS Technology Area Breakdown Structure CNS Central Nervous System TOC Total Organic Carbon D&C Display and Controls TRL Technology Readiness Level DMS Differential mobility spectrometry UI User Interface DRA Design Reference Architecture VCAM Vehicle Cabin Air Monitor DRM Design Reference Mission DTO Detailed Test Objective Acknowledgements ECLSS Environmental Control and The NASA technology area draft roadmaps were Life Support Systems developed with the support and guidance from EHS Environmental Health System the Office of the Chief Technologist. In addition ER Environmental Monitoring, Safety, and Emergency Response to the primary authors, major contributors for the ESI Electro-spray ionization TA06 roadmap included the OCT TA06 Road- EUE Experiment-Unique Equipment mapping POC, Howard Ross; the reviewers pro- EVA Extra-Vehicular Activity vided by the NASA Center Chief Technologists GCR Galactic Cosmic Radiation and NASA Mission Directorate representatives, HD High-Definition and the following individuals: Audrey Burge, HEDS Human Exploration and Development Jeannie Corte, Karen Spears, Rilla Wolf. of Space HEPA High Efficiency Particulate Air HFP Human Factors and Performance HHP Human Health and Performance HITL Human-in-the-Loop HLHS Human Health, Life Support, and Habitation Systems HRI Human-Robotic Interaction HIS Human System Integration IPS Induced Pluripotent Stem Cells ISRU In-Situ Resource Utilization ISS International Space Station JSC Johnson Space Center KSC Kennedy Space Center LEA Launch, Entry, and Abort LED Light-Emitting Diode LEO Low-Earth Orbit LST Life Support Technologies LTA Lighter-than-Air MMOD Micro-Meteoroid Orbital Debris MS Mass spectrometry MSFC Marshall Spaceflight Center NASA National Aeronautics and Space Admin. NBL Neutral Buoyancy Laboratory NEA Near-Earth Asteroid NEO Near-Earth Objects NIH National Institute of Health NSRL NASA Space Radiation Laboratory OCT Office of Chief Technologist PAS Power, Avionics, and Software PEL Permissible Exposure Limits TA06-24 DRAFT This page is intentionally left blank

DRAFT TA06-25 November 2010

National Aeronautics and Space Administration

NASA Headquarters Washington, DC 20546 www.nasa.gov TA06-26 DRAFT