About: Austere Human Missions to Mars   Sponge Permalink

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Technologically and financially the concept remains conservative, with both peak yearly and total funding to be less than the ISS up to the first mission. The plan would use standardized systems to launch a crew of 4 every four years, but accomplish the same major goals as DRA 5.0, which included a crew of six. Scaled down from DRA 5.0 and its requirements, it claims to be still acceptable from a science and exploration standpoint. Simplifications and cost cutting are obtained mainly by avoiding high risk or high cost technology development and maximizing development and production commonality:

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  • Austere Human Missions to Mars
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  • Technologically and financially the concept remains conservative, with both peak yearly and total funding to be less than the ISS up to the first mission. The plan would use standardized systems to launch a crew of 4 every four years, but accomplish the same major goals as DRA 5.0, which included a crew of six. Scaled down from DRA 5.0 and its requirements, it claims to be still acceptable from a science and exploration standpoint. Simplifications and cost cutting are obtained mainly by avoiding high risk or high cost technology development and maximizing development and production commonality:
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dbkwik:nasa/proper...iPageUsesTemplate
abstract
  • Technologically and financially the concept remains conservative, with both peak yearly and total funding to be less than the ISS up to the first mission. The plan would use standardized systems to launch a crew of 4 every four years, but accomplish the same major goals as DRA 5.0, which included a crew of six. Scaled down from DRA 5.0 and its requirements, it claims to be still acceptable from a science and exploration standpoint. Simplifications and cost cutting are obtained mainly by avoiding high risk or high cost technology development and maximizing development and production commonality: * Using a blunt-body entry vehicle having no deployable decelerators * Aerobraking rather than aerocapture for placing the crewed element into low Mars orbit * Avoiding the use of liquid hydrogen with its low temperature and large volume issues * Standard bipropellant propulsion for the landers and ascent vehicle * Radioisotope surface power systems rather than a nuclear reactor or large area deployable solar arrays * Multiple Ares V launchers used for setting up and maintaining the Mars installations
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