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This paper considers the cost and benefit of planetary surface ExtraVehicular Activity (EVA) on the Moon and Mars. The Exploration Systems Architecture Study (ESAS) scenarios are used as a basis. The benefits of surface EVA depend on the number of sites visited, the total duration of EVA, and the maximum distance of exploration. The costs of EVA are measured by the total emplaced mass required to support a sortie mission or to establish and support a long term base. The later lunar sorties described in the ESAS have longer duration and use rovers not provided earlier, so they are more cost-effective in surface exploration. The planned permanent lunar base provides one-sixth the cost per EVA hour and a thirty percent lower cost per kilometer of explorable distance, but exploration is limited to a single site. There is an important trade-off between the number of different sites explored and the total time spent in surface exploration.

The least expensive life support for brief human missions is direct supply of all water and oxygen from Earth without any recycling. The currently most advanced human life support system was designed for the International Space Station (ISS) and will use physicochemical systems to recycle water and oxygen. This paper compares physicochemical to direct supply air and water life support systems using Equivalent Mass (EM). EM breakeven dates and EM ratios show that physicochemical systems are more cost effective for longer mission durations.

This study describes the operational requirements for planetary surface access and compares the performance of a hatch, airlock, suitlock, and suitport. The requirements for mitigating dust, performing EVA (ExtraVehicular Activity) by only part of the crew, and use on Mars as well as the Moon are strong reasons to prefer an airlock over a simple hatch, which would require depressurizing the habitat and sending all the crew on EVA. A requirement for minimum cost would favor the hatch above all. A suitlock provides better dust mitigation than an airlock, but at higher cost and complexity. A suitlock accommodating two crew meets requirements for buddy assistance and ability to help an incapacitated crewmember. Two suitlocks would provide redundant airlocks.

This study introduces several new concepts for suited EVA astronaut ingress/egress (departure and return) from a pressurized planetary surface habitat, based on use of a rear-entry suit and a suit lock or suitport. We provide insight into key operational aspects and integration issues, as well as the results of a requirements analysis and risk assessment of the concepts. The risk assessment included hazard analysis, hazard mitigation techniques, failure mode assessment, and operational risk assessment. Also included are performance and mass estimates for the egress concepts, and concepts for integration of the egress concepts with potential planetary habitat designs.

This paper considers the design of a life support system for transit to Mars and return to Earth. Because of the extremely high cost of launching mass to Mars, the Mars transit life support system must minimize the amount of oxygen, water, and food transported. The three basic ways to provide life support are to directly supply all oxygen and water, or to recycle them using physicochemical equipment, or to produce them incidentally while growing food using crop plants. Comparing the costs of these three approaches shows that physicochemical recycling of oxygen and water is least costly for a Mars transit mission. The long mission duration also requires that the Mars transit life support system have high reliability and maintainability. Mars transit life support cannot make use of planetary resources or gravity. It should be tested in space on the International Space Station (ISS).

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

This paper considers the design of a Mars Transfer Vehicle (MTV) water processor. The Constellation Program has begun to consider the first human mission to Mars, and the MTV water processor is of special interest. Mars transit system design is not affected by Extra-Vehicular Activity (EVA) or In-Situ Resource utilization (ISRU). The total duration of Mars transit and return is relatively fixed at about four hundred days, while Mars and lunar surface stays can vary from a few days to many years. The Mars transit water processor will operate in zero gravity, like the International Space Station (ISS) Water Recovery System (WRS), so the ISS WRS design can serve as a reference baseline for the Mars transit system. The paper develops the MTV water requirements and considers the suitability of the ISS WRS for Mars transit. The ISS WRS meets MTV requirements and requires less mass than direct resupply for Mars transfer, but it has excess capacity for the requirements.

This report considers crewmembers’ life support needs for air, water, and food in a long duration lunar surface base. It also considers requirements for washing and clean-up water, waste recycling, and the crew's use of air, water, and food during Extravehicular Activity (EVA). The life support mass flow is described, including the needs of the statistical average crewmember, the expected variation between crewmembers, and the potential range of the total crew's average requirements. To develop the lowest cost, most reliable life support system that meets the crew needs, we must understand how the requirements impose design constraints and cost drivers and provide options and opportunities. We also must be aware of the degree of flexibility and potential change in requirements as their costs and implementation become defined.

Space projects are spectacular, costly, and highly visible. Their occasional failures receive extensive analysis and explanation. This paper reviews studies of failures of crewed and uncrewed missions. The explanations of these space project failures include simple oversight errors, poor project management, complex combinations of unforeseen events, and conceptual flaws that prohibited success. Failures are usually found to be caused by project management errors, based on the reasoning that the project manager and team members had the capability and responsibility to avoid them. These failure causes are well known. Why do so many projects make the same mistakes?

NASA is planning to return to the moon and then explore Mars. A permanent base at the south pole of the moon will be the test bed for Mars. At the moon base, two crewmembers are expected to conduct Extravehicular Activity (EVA) six days every week. Current spacesuits are cooled by the sublimation of water ice into vacuum. A single 7 hour EVA near the lunar equator in daylight can expend up to 5 kilograms of water. Because of the high cost of transporting spacesuit cooling water to the moon, the water for one EVA could cost hundreds of thousands of dollars. The lunar south pole and Mars have low surface temperatures that make cooling much easier than at the lunar equator. Alternate cooling methods and staying in cool environments can reduce or eliminate the use of water for spacesuit cooling. If cooling water is not needed, a recycling life support system can provide all the required crew water and oxygen without transporting additional water from Earth.

Dynamic simulation of the lunar outpost habitat life support was undertaken to investigate the impact of life support failures and to investigate possible responses. Some preparatory static analysis for the Lunar Outpost life support model, an earlier version of the model, and an investigation into the impact of Extravehicular Activity (EVA) were reported previously. (Jones, 2008-01-2184, 2008-01-2017) The earlier model was modified to include possible resupply delays, power failures, recycling system failures, and atmosphere and other material storage failures. Most failures impact the lunar outpost water balance and can be mitigated by reducing water usage. Food solids and nitrogen can be obtained only by resupply from Earth. The most time urgent failure is a loss of carbon dioxide removal capability. Life support failures might be survivable if effective operational solutions are provided in the system design.

The design and mass cost of a starship and its life support system are investigated. The mission plan for a multigenerationai interstellar voyage to colonize a new planet is used to describe the starship design, including the crew habitat, accommodations, and life support. Cost is reduced if a small crew travels slowly and lands with minimal equipment. The first human interstellar colonization voyage will probably travel about 10 light years and last hundreds of years. The required travel velocity is achievable by nuclear propulsion using near future technology. To minimize mission mass, the entire starship would not decelerate at the destination. Only small descent vehicles would land on the destination planet. The most mass efficient colonization program would use colonizing crews of only a few dozen. Highly reliable life support can be achieved by providing selected spares and full replacement systems.

This paper describes engineering rules of thumb for life support system design. One general design rule is that the longer the mission, the more the life support system should use regenerable technologies and recycling. A more specific rule is that, if plants supply more than about half the food, the plants will provide all the oxygen needed by the crew. There are many such design rules that can help in planning the analysis of life support systems or in assessing design concepts. These rules typically describe the results of steady state, “back of the envelope,” trade-off calculations. They are useful in suggesting plausible candidate life support system designs or approaches. Life support system engineers should consider the basic design rules and make quick steady state calculations as a guide before doing detailed design.

The purpose of dynamic modeling and simulation of Advanced Life Support (ALS) systems is to help design them. Static steady state systems analysis provides basic information and is necessary to guide dynamic modeling, but static analysis is not sufficient to design and compare systems. ALS systems must respond to external input variations and internal off-nominal behavior. Buffer sizing, resupply scheduling, failure response, and control system design are aspects of dynamic system design. We develop two dynamic mass flow models and use them in simulations to evaluate systems issues, optimize designs, and make system design trades. One model is of nitrogen leakage in the space station, the other is of a waste processor failure in a regenerative life support system. Most systems analyses are concerned with optimizing the cost/benefit of a system at its nominal steady-state operating point. ALS analysis must go beyond the static steady state to include dynamic system design.

The decision to develop a particular life support technology or to select it for flight usually depends on the cost to develop and fly it. Other criteria such as performance, safety, reliability, crew time, and technical and schedule risk are considered, but cost is always an important factor. Because launch cost would account for much of the cost of a future planetary mission, and because launch cost is directly proportional to the mass launched, equivalent mass has been used instead of cost to select advanced life support technology. The equivalent mass of a life support system includes the estimated mass of the hardware and of the spacecraft pressurized volume, power supply, and cooling system that the hardware requires. The equivalent mass of a system is defined as the total payload launch mass needed to provide and support the system. An extension of equivalent mass, Equivalent System Mass (ESM), has been established for use in the Advanced Life Support project.

The search for alien life in the solar system should include exploring unearthlike environments for life having an unearthly biochemistry. We expect alien life to conform to the same basic chemical and ecological constraints as terrestrial life, since inorganic chemistry and the laws of ecosystems appear to be universal. Astrobiologists usually assume alien life will use familiar terrestrial biochemistry and therefore hope to find alien life by searching near water or by supplying hydrocarbons. The assumption that alien life is likely to be based on carbon and water is traditional and plausible. It justifies high priority for missions to search for alien life on Mars and Europa, but it unduly restricts the search for alien life. Terrestrial carbon-water biochemistry is not possible on most of the bodies of our solar system, but all alien life is not necessarily based on terrestrial biochemistry.

System failures, dynamics, and nonlinearities can cause unacceptable performance and damaging instability in Advanced Life Support (ALS) systems. Much current ALS modeling assumes that ALS systems are linear, static, and failure-free. But in reality most ALS hardware is subject to failure, real ALS systems are dynamic, and many ALS processors are nonlinear beyond a limited operating range. Modeling and simulation are needed to study the stability and time behavior of nonlinear dynamic ALS systems with failures and to develop appropriate controls. The nonlinear dynamics of ALS systems has many interesting potential consequences. Different equilibrium points may be reached for different initial conditions. The system stability can depend on the exact system inputs and initial conditions. The system may oscillate or even in rare cases behave chaotically. Temporary internal hardware failures or external perturbations can lead to dynamic instability and total ALS system failure.

Industrial process control has been dominated by closed architectures and proprietary protocols for the last three decades. In the late 1990’s, the advent of open fieldbus and middleware standards has greatly changed the process control arena. Fieldbus has pushed control closer and closer to the process itself. Middleware standards have exposed real-time process data to higher level software applications. Control systems can now be designed to minimize the reconfiguration costs associated with design changes. How can Advanced Life Support (ALS) benefit from these technologies? We consider designing the control system for the BIO-Plex and evaluate how complex it will be, the effort it will require, and how much it will it cost. Various fieldbus technologies were compared and Foundation Fieldbus was chosen for detailed evaluation. This new fieldbus was integrated with an existing ALS system.

Researchers in astrobiology should develop alternate concepts for the detection of extraterrestrial life. We should search for extraterrestrial ecology, exoecology, as well as for extraterrestrial biology, exobiology. Ecology describes the interactions of living things with their environment. All ecosystems are highly constrained by their environment and conform to well-known and inescapable system design principles. An ecology could exist wherever there is an energy source and living things can employ some method to capture, store, and use the available energy. Terrestrial ecosystems use energy sources including light, organic molecules, and, in thermal vents and elsewhere, simple inorganic molecules. Ecosystem behavior is controlled by matter and energy conservation laws and is described by dynamic systems theory. Typically in an ecosystem different molecules are not in chemical equilibrium and scarce materials are conserved, stored, or recycled.

We modeled BIO-Plex designs with separate or combined atmospheres and then simulated controlling the atmosphere composition. The BIO-Plex is the Bioregenerative Planetary Life Support Systems Test Complex, a large regenerative life support test facility under development at NASA Johnson Space Center. Although plants grow better at above-normal carbon dioxide levels, humans can tolerate even higher carbon dioxide levels. Incinerator exhaust has very high levels of carbon dioxide. An elaborate BIO-Plex design would maintain different atmospheres in the crew and plant chambers and isolate the incinerator exhaust in the airlock. This design option easily controls the crew and plant carbon dioxide levels but it uses many gas processors, buffers, and controllers. If all the crew’s food is grown inside BIO-Plex, all the carbon dioxide required by the plants can be supplied by crew respiration and the incineration of plant and food waste.