An Environmental Control and Life Support System Concept for a Pressurized Lunar Rover

Bagdigian, Robert M.; Stambaugh, Imelda

doi:10.2514/6.2010-6256

Cited by 8 publications

(3 citation statements)

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“…(1) through (5) refer to the PCM, Eqs. (6) through (8), the PUP, Eqs. (9) through (11) the LER and Eqs.…”

Section: Temporal Difference Effect Analysis Of Batch and Periodicmentioning

confidence: 99%

“…Table 1 shows the main specifications of lunar surface systems used in this study. The specifications are defined based on previous work [8][9][10] . Four crewmembers can stay at the outpost, which consists of PCM, PLM and LER, and the two groups of two crewmembers each can explore at the same time with the two-seated LERs.…”

Section: A Lunar Surface System Configurationmentioning

confidence: 99%

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Logistics and Life Support Systems Analysis for High-Mobility Exploration on a Lunar Surface

Miyajima

2013

43rd International Conference on Environmental Systems

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This paper presents a formulation of a lunar surface excursion based on planetary extra vehicular activity parameters and constraints, and analyzes the supply and collection of resources (i.e. oxygen, pure water and waste water) for the life support system during a short excursion to Malapert and a longer trip to Schrödinger Basin. In the two excursions the life support system recycling options were studied using spread sheet simulations. The results indicated that the improved whole-system recycling rate when CO 2 was collected in the Lunar Electric Rover was smaller than when CO 2 was collected in the Pressurized Excursion Module. The effects of batch and periodic supply and collection of resources were analyzed by means of a dynamic simulation model. The results indicated that periodic supply and collection can stabilize the mass changes of resources at the outpost. However in a long-range excursion, the supplies and collections could not be adequately disperse since the Portable Utility Pallet's operation is restricted to daytime use only. If that restriction can be overcome, the resulting improved stabilization will contribute to the robustness of life support system operations when the range and term of exploration are extended. NomenclatureCh CO2 = carbon dioxide discharge rate of crew Ch O2 = oxygen consumption rate of crew d LERi = position of Lunar Electric Rover (LER) i d PCM = position of Pressurized Core Module (PCM) d PUPj = position of Portable Utility Pallet (PUP) j El = production rate of electrolysis reaction i = number of LER (i=1, 2, …, I) j = number of PUP (j=1, 2, …, J) N LERi = number of crew on LER i N PCM = number of crew in PCM pC sa = carbon production rate of CO 2 reduction pH 2EI = hydrogen production rate of electrolysis reaction pH 2 O EI = water consumption rate of electrolysis reaction pO 2EI = oxygen production rate of electrolysis reaction pO 2Sa = oxygen production rate of CO 2 reduction Sa = CO 2 reduction rate sw H2O = amount of water supply 1 Professor, Faculty of Liberal Arts for Global Studies and Leadership, 1105 Tsuruma, Senior Member. Downloaded by PURDUE UNIVERSITY on March 28, 2016 | http://arc.aiaa.org | International Conference on Environmental Systems (ICES) sw O2= amount of oxygen supply sw wH2O = amount of waste water recovery t = day (t=1, 2, …, T) Ta H2OinLERi = amount of water in water tank of LER i Ta H2OinPCM = amount of water in water tank of PCM Ta H2OinPUPj = amount of water in water tank of PUP j Ta H2OmaxinLERi = capacity of water tank in LER i Ta H2OmaxinPUPj = capacity of water tank in PUP j Ta O2inLERi = amount of oxygen in oxygen tank of LER i Ta O2inPCM = amount of oxygen in oxygen tank of PCM Ta O2inPUPj = amount of oxygen in oxygen tank of PUP j Ta O2maxinLERi = capacity of oxygen tank in LER i Ta O2maxinPUPj = capacity of oxygen tank in PUP j Ta wH2OinLERi = amount of waste water in waste water tank of LER i Ta wH2OinPCM = amount of waste water in waste water tank of PCM Ta wH2OinPUPj = amount of waste water in waste water tank o...

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“…(1) through (5) refer to the PCM, Eqs. (6) through (8), the PUP, Eqs. (9) through (11) the LER and Eqs.…”

Section: Temporal Difference Effect Analysis Of Batch and Periodicmentioning

confidence: 99%

Section: A Lunar Surface System Configurationmentioning

confidence: 99%

Logistics and Life Support Systems Analysis for High-Mobility Exploration on a Lunar Surface

Miyajima

2013

43rd International Conference on Environmental Systems

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“…At the beginning of the mission, the astronaut has access to 1 Martian base, 2 surface exploration vehicles (SEV) (Bagdigian and Stambaugh 2015), 4 extra-vehicular activity suits (Boyle et al 2012), 400 sols' worth of meal rations, and several raw potatoes capable of growth.…”

Section: Case Studymentioning

confidence: 99%

Active Mission Success Estimation through PHM-Informed Probabilistic Modelling

Short

Bossuyt

2015

PHM_CONF

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Prognostics and Health Management (PHM) techniques have traditionally been used to analyze electrical and mechanical systems, but similar techniques can be adapted for less mechatronically-focused processes such as crewed space missions. By applying failure analysis techniques taken from PHM, the probability of success for missions can be calculated. Extensive work has been conducted to predict space mission failure, but many existing methods do not take full advantage of modern computing power and the potential for real-time calculation of mission failure probabilities. The Active Mission Success Estimation (AMSE) method is developed in this paper to track and calculate the probability of mission failure as the mission progresses, and is intentionally adaptable for shifting mission objectives and parameters. This form of mission modelling takes a broader view of the mission and objectives, and develops statistical probability models of success or failure for multiple possible choice combinations that is used to inform real-time decisions and maximize probability of mission success. A case study of a generalized crewed Mars mission that has turned into a survival scenario is considered where an astronaut has been left behind on the surface and must survive for an extended period of time before undertaking a long-distance journey to a new launch site for rescue and return to Earth. The AMSE method presented here aims to establish real-time probabilistic modeling of decision outcomes during an active mission and can be used to inform mission decisions.

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Mission Design Drivers for Life Support

Jones

2011

41st International Conference on Environmental Systems

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An Environmental Control and Life Support System Concept for a Pressurized Lunar Rover

Cited by 8 publications

References 1 publication

Logistics and Life Support Systems Analysis for High-Mobility Exploration on a Lunar Surface

Logistics and Life Support Systems Analysis for High-Mobility Exploration on a Lunar Surface

Active Mission Success Estimation through PHM-Informed Probabilistic Modelling

Mission Design Drivers for Life Support

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