Completed
This study will identify primary technical and programmatic challenges, merits, and risks for developing and demonstrating space nuclear propulsion technologies of interest to future exploration missions. The committee will also determine the key milestones and a top-level development and demonstration roadmap for each technology. Additionally, the committee will identify missions that could be enabled by successful development of each technology. Technologies of specific interest are high-performance nuclear thermal propulsion (NTP) and nuclear electric propulsion (NEP) systems.
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Consensus
·2021
Space Nuclear Propulsion for Human Mars Exploration identifies primary technical and programmatic challenges, merits, and risks for developing and demonstrating space nuclear propulsion technologies of interest to future exploration missions. This report presents key milestones and a top-level devel...
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Description
The National Academies of Sciences, Engineering, and Medicine will convene an ad hoc committee to identify primary technical and programmatic challenges, merits, and risks for developing and demonstrating space nuclear propulsion technologies of interest to future exploration missions. Nuclear propulsion has been shown to offer the potential for rapid human transit to Mars with one-way transit times less than 9 months and total roundtrip times including Mars surface stays less than 3 years. The committee will also determine the key milestones and a top-level development and demonstration roadmap for each technology. Additionally, the committee will identify missions that could be enabled by successful development of each technology.
The space nuclear propulsion technologies of specific interest are:
1. High-performance nuclear thermal propulsion that heats hydrogen propellant to 2500 K or more and produces specific thrust of at least 900 seconds.
2. Nuclear electric propulsion that converts thermal energy to electricity to power plasma thrusters for highly efficient and rapid transport of large payloads (e.g., a propulsion system with a power level of at least 1 MWe and a mass-to-power ratio (kg/kWe) that is substantially lower than the current state of the art of NEP systems).
Contributors
Committee
Co-Chair
Co-Chair
Member
Member
Member
Member
Member
Member
Member
Member
Member
Sponsors
NASA
Staff
Alan Angleman
Lead
Gaybrielle Holbert