Human exploration of Mars, Design Reference Architecture 5.0

Drake, Bret G.; Hoffman, Stephen J.; Beaty, D. W.

doi:10.1109/aero.2010.5446736

Cited by 336 publications

(326 citation statements)

References 6 publications

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“…In the Antarctic, an over-wintering crew of 10 members needs to be supplied with fresh pick and eat crops during the isolation phase of 6-7 months at the Neumayer Station III. Although the crew size is higher than anticipated for early Mars missions (4-6 members (Hoffmann and Kaplan 1997;Drake and Watts 2014;ESAS 2005)), the EDEN ISS case is still within acceptable limits.…”

Section: Introductionmentioning

confidence: 98%

Greenhouse production analysis of early mission scenarios for Moon and Mars habitats

Schubert

2017

Open Agriculture

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The In-Phase Cultivation approach where all trays start at the same time, and the Shifted Cultivation approach, where trays start in a specific sequential manner. Depending on the approach, different biomass output patterns emerged and were analysed with respect to crew consumption, crop shelf-life, and the risk of food spoilage. Crew time estimates were performed with respect to the overall production process, which resulted into 208.9 min per day for the planned cultivation area. When applying normal terrestrial worktimes, this equates to approximately 50% of a crew member day for system operation. Biomass and crew time results were analysed in relation to each other, creating specific productivity factors for each crop type. This way, future mission planning, crop selection, and greenhouse design studies can better tailor the implementation challenges of small greenhouse modules into the habitat infrastructure.Keywords: food production, greenhouse modules, bioregenerative life support systems, production lifecycle analysis, crew time estimates, crop shelf life, habitat demand function, biomass over-and under production IntroductionWith early Mars human exploration missions expected to last 500 to 600 days (Hoffmann and Kaplan 1997), the initial build-up phase of a planetary habitat infrastructure would be initiated with consideration for follow-up missions that have the goal to improve the outpost with additional habitat elements enabling longer mission durations. Even in early habitat development missions, a small Greenhouse Module (GHM) is anticipated. Such a module would provide enough edible biomass to support a supplement food strategy for the crew. Examples for these kinds of early habitat infrastructures are the Lava:Hive concept for an early Mars habitat (LavaHive 2015) and the SinterHab concept for an early Moon habitat (SinterHab 2013).Testing a dedicated greenhouse module for these habitat scenarios is required in order to fine tune expected Abstract: The establishment of planetary outposts and habitats on the Moon and Mars will help foster further exploration of the solar system. The crews that operate, live, and work in these artificial constructions will rely on bio-regenerative closed-loop systems and principles, such as algae reactors and higher plant chambers, in order to minimize resupply needs and improve system resiliency. Greenhouse modules will play a major role in closing not only the oxygen, carbon-dioxide, and water supply loops, but also by providing fresh food for the crew. In early mission scenarios, when the habitat is still in its build-up phase, only small greenhouse systems will be deployed, providing a supplemental food strategy. Small quantities of high water content crops (e.g. lettuce, cucumber, tomato) will be cultivated, improving the crew's diet plan with an add-on option to the pre-packed meals. The research results of a 400-day biomass and crew time simulation of an adapted EDEN ISS Future Exploration Greenhouse are presented. This greenhouse is an experimental cultiva...

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Section: Introductionmentioning

confidence: 98%

Greenhouse production analysis of early mission scenarios for Moon and Mars habitats

Schubert

2017

Open Agriculture

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“…To represent the IMLEO reduction, the gear ratio is shown, which is defined as the ratio of IMLEO to the landed mass on Mars. In addition, the number of launches is also shown assuming the equivalent payload as NASA Design Reference Architecture 5.0 cargo pre-deployment mission (40 mT on Martian surface 7 ) and the launches by the 130 mT Space Launch System (SLS). The results show that stopping at the DRO gas station would provide the propellant necessary for part or all of the rest of the journey to Mars, which would effectively reduce the propellant and the size of the tank that need to be launched from Earth.…”

Section: Dro Used For Mars Missionsmentioning

confidence: 99%

Earth-Mars transfers through Moon Distant Retrograde Orbits

Conte

Carlo²,

et al. 2018

Acta Astronautica

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This paper focuses on trajectory design which is relevant for missions that would follow NASA's Asteroid Redirect Mission (ARM) to further explore and utilize asteroids and eventually human Mars exploration. Assuming that a refueling gas station is present at a given Lunar Distant Retrograde Orbit (DRO), we analyze ways of departing from the Earth to Mars via that DRO. Thus, the analysis and results presented in this paper add a new cis-lunar departure orbit for Earth-Mars missions. Porkchop plots depicting the required C 3 at launch, v ∞ at arrival, Time of Flight (TOF), and total ∆V for various DRO departure and Mars arrival dates are created and compared with results obtained for low ∆V LEO to Mars trajectories. The results show that low ∆V DRO to Mars transfers generally have lower ∆V and TOF than LEO to Mars maneuvers.

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“…Published in 2009, DRA 5.0 is the latest NASA Mars reference mission, and provides an integrated design approach along with the mission goals, systems, and challenges facing the first three human expeditions to Mars. 10 Because NEP vehicles have often been proffered as a means for economical cargo delivery to the Moon, Mars, and other planetary destinations, a limited study was undertaken under the auspices of the ETDD High Efficiency…”

Section: Mars Cargo Reference Missionmentioning

confidence: 99%

MW-Class Electric Propulsion System Designs for Mars Cargo Transport

Gilland

LaPointe

Oleson

et al. 2011

AIAA SPACE 2011 Conference &Amp; Exposition

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Multi-kilowatt electric propulsion systems are well developed and have been used on commercial and military satellites in Earth orbit for several years. Ion and Hall thrusters have also propelled robotic spacecraft to encounters with asteroids, the Moon, and minor planetary bodies within the solar system. High power electric propulsion systems are currently being considered to support piloted missions to near earth asteroids, as cargo transport for sustained lunar or Mars exploration, and for very high-power piloted missions to Mars and the outer planets. Using NASA Mars Design Architecture 5.0 as a reference, a preliminary parametric analysis was performed to determine the suitability of a nuclear powered, MW-class electric propulsion system for Mars cargo transport. For this initial analysis, high power 100-kW Hall thrusters and 250-kW VASIMR engines were separately evaluated to determine optimum vehicle architecture and estimated performance. The DRA 5.0 cargo mission closed for both propulsion options, delivering a 100 t payload to Mars orbit and reducing the number of heavy lift launch vehicles from five in the baseline DRA 5.0 architecture to two using electric propulsion. Under an imposed single engine-out mission success criteria, the VASIMR system took longer to reach Mars than did the Hall system, arising from the need to operate the VASIMR thrusters in pairs during the spiral out from low Earth orbit.

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Human exploration of Mars, Design Reference Architecture 5.0

Cited by 336 publications

References 6 publications

Greenhouse production analysis of early mission scenarios for Moon and Mars habitats

Greenhouse production analysis of early mission scenarios for Moon and Mars habitats

Earth-Mars transfers through Moon Distant Retrograde Orbits

MW-Class Electric Propulsion System Designs for Mars Cargo Transport

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