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• W3184367799 abstract "The long term, sustained exploration of Mars will require the focused efforts of a collective of national space agencies, public and private industry, and academia. The goal of this exploration will not be to just plant a flag and leave a boot print, but to continue beyond the first mission or first set of missions. Several key technologies will be required to enable both the upfront and continued exploration of Mars, one of these technologies being Nuclear Thermal Propulsion (NTP). This paper is the second in a series of studies analyzing a future Mars exploration campaign utilizing NTP as the primary propulsion option for both crew and cargo transfer. While the entire envisioned campaign includes uncrewed demonstration flights, crewed short-stay missions, and crewed long-stay missions, this paper examines the trajectory and architectural elements required for the first crewed mission to the Martian surface. Through a sequence of uncrewed and crewed missions, the Mars exploration campaign will prepare for the eventual permanent human presence on the planet’s surface. The first crewed mission to the Martian surface (third overall mission in the campaign) will be a short-stay mission utilizing an opposition class trajectory. With the proposed campaign structure, flying an opposition class trajectory for the first surface mission requires fewer logistics and surface assets to be developed and pre-deployed. This approach ensures a minimalist approach to the first surface mission, increasing reliability and safety, and spreading out the cost burden of an entire campaign. The elements required for this first mission would be the NTP Crew Mars Transport Vehicle (MTV), NTP Cargo MTV, Mars lander, Mars Ascent Vehicle (MAV), and surface habitation. The NTP Crew and Cargo MTVs would leverage design commonality across most subsystems, reducing cost and complexity. It is also envisioned that the MAV and Mars lander would have propulsion subsystem commonality. A combination of government and commercial launch vehicles are assumed for each element, utilizing the payload mass and volume capability of the Space Launch System (SLS) Block 2 along with the more frequent launch cadence of commercial vehicles. The crew transfer to Mars uses an opposition class trajectory with a total mission duration of 760 days, at the cost of higher DV and a larger transfer vehicle when compared to a conjunction class trajectory. The primary objectives of this mission would be to demonstrate the landing of large structures and short-term habitation on Mars, while also increasing experience with operating an NTP engine and human habitation in deep space." @default.
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• W3184367799 date "2021-07-28" @default.
• W3184367799 modified "2023-09-26" @default.
• W3184367799 title "NTP Human Mars Exploration Campaign: First Surface Mission" @default.
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• W3184367799 doi "https://doi.org/10.2514/6.2021-3610" @default.
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