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This work (summarizing the results of experimentation with Closed Ecological System BIOS-3, Krasnoyarsk, and Russian Siberia in 1989-1998) is an attempt to analyze the process of plant biomass incineration as a source of carbon dioxide for plant photosynthesis and growth and its effects on closed system stability. It is common knowledge that incineration of phytomass supplies into the atmosphere of a Closed Ecological System (CES) not carbon dioxide only, but also gaseous toxic agents inhibiting photosynthetic processes. Mathematical modeling has demonstrated that when the limit value of intensity of production processes and matter turnover specific for every closed ecosystem is exceeded the gaseous toxic agents destroy the system. This value is proportional to CES buffer absorption capacity and is non-linearly dependent on the tolerance of the plant component to the impact of flue gases.

As humans continue to explore the solar system, psychological problems brought about by the high stress of living in a space environment will continue to increase. Five astronauts and cosmonauts representing three space agencies: ESA, RSA, and JAXA were surveyed regarding their experiences with ten general categories of psychological stressors and eight subcategories of interpersonal conflict. Results suggest psychological stressors are more likely to increase in quantity and severity in longer duration spaceflight. A conceptual mathematical model for stress estimates is suggested. This method appears to be in agreement with qualitative estimates of stressor roles in different space mission durations.

Space is characterized by many uncertainties, natural and human induced, for manned missions in hostile environments. Therefore, human operations in space require reliable Life Support Systems (LSS) capable to maintain functionality for long durations. However, the ultimate theoretical analysis of LSS reliability for space applications is very difficult due to many unknown and possibly undiscovered factors which might affect system functional performance. In this work the conceptual approach for a complex LSS reliability analysis is reviewed. Methodology based on Fokker-Planck statistical equation is proposed and investigated. According to these preliminary considerations, a few critical variables are identified and determined: 1) average rate of material recirculation in LSS; 2) LSS and environment uncertainty level (level of material circulation rate fluctuations); and 3) human control level and its limitations.

The objective of this paper is to detail the development of the DL/H-1 full pressure suit, which was developed by De Leon Technologies LLC, with the assistance of the University of North Dakota. The DL/H-1 was specifically developed to fulfill the needs for a full pressure suit for private spaceflight in case of decompression or in the need of bailout of the spacecraft. This work also details the objectives, basis for design, problems encountered by the designers, final development of the DL/H-1 full pressure suit and testing in the high altitude chamber at the School of Aerospace Sciences at the University of North Dakota. The authors believe that during experimental flights of private spaceflight, orbital or suborbital a full pressure suit will be required to augment safety during all flight phases where in the case of cabin pressure loss, without personal protection, the loss of crew and vehicle could result.

The objective of this paper is to detail a proposal for an Androgynous Docking Airlock/Utility Module (ADAM) that would allow extravehicular (EVA) crews, working from the Orion spacecraft, to avoid depressurizing the command module of the Orion vehicle for planned EVA repair, maintenance and interdiction of orbital structures. Unlike the Space Shuttle, Russian Soyuz vehicle or the Chinese Shenzhou manned spacecraft, the proposed Orion space vehicle has no airlock. This necessitates the depressurizing of the entire Command Module cabin during EVA activity. It also means that all crewmembers will have to wear space suits during contingency and planned EVAs. This inordinately dangerous situation will require all crewmembers to be exposed to the space vacuum for as much as seven hours or more if a working EVA becomes necessary.

This work represents an extended analysis of the mathematical model which was originally developed in an attempt to analyze the process of plant biomass incineration as a source of carbon dioxide for plant photosynthesis and growth and its effects on closed ecological system stability, Mathematical modeling has demonstrated that when the limit value of intensity of production processes and matter turnover specific for every closed ecosystem is exceeded, the gaseous toxic agents destroy the system. In order to illustrate further the performance and application of the proposed model, the hypothetical optimized ecological life support system was investigated, The preliminary results suggest appropriate system parameters for further engineering implementation. The results of the theoretical analysis are verified and supported by quantitative estimates from the Russian Closed Ecosystem (CES) BIOS-3 which was tested for extended life support between 1970 and 1990.

Over a one-year period beginning in March, 2005, and with a materials budget of approximately $25,000, the North Dakota Space Grant Consortium developed a pressurized planetary space suit concept demonstrator in conjunction with institutions of higher education across the state. This project sought to combine educational instruction in space suit design and manufacturing while simultaneously developing a usable test article incorporating technical approaches appropriate to the project's schedule and budgetary constraints. The North Dakota Experimental (NDX) Suit serves as a testbed for new planetary suit materials and component assemblies. Designed around a dual-plane enclosure ring built on a composite hard upper torso (HUT), the NDX is designed for an operating differential pressure of 26.2 kPa. In order to test a two-chamber suit concept, the NDX features a neck dam assembly that divides the helmet breathing cavity from the body below the neck.

The proposed NASA Crew Exploration Vehicle (CEV) has been labeled “not as a repetition of Apollo, but instead what Apollo should have been.” While this designation is certainly ripe for debate, there is no debating that the space suit community has, up to this point, had limited or no input into the on-going design of the CEV. However, it is important that the community take the opportunity to influence the configuration of the proposed CEV so as to optimize its orbital and planetary/lunar EVA capability, flexibility and safety. This “window of opportunity” will not remain open for long, as the CEV’s configuration is rapidly congealing. This paper covers: 1. Brief space suit configurations, employment and history. 2. Brief descriptions and comparisons of IVA, EVA and IEVA space suits. 3. How history can be a guide to optimize EVA for the Crew Exploration Vehicle.