A Cost Modeling Approach for Entry Systems Analysis of Human Mars Missions
Cost is one of the biggest obstacles to sending humans to Mars. However, spacecraft costs are typically not estimated until after the preliminary vehicle and mission concepts have been designed. By automating the cost estimation process, the effect of any change in vehicle or mission design on the mission cost can be determined more efficiently. This paper describes an extension to the tool Systems Analysis for Planetary Entry, Descent, and Landing which integrates the cost modeling software System Estimation and Evaluation of Resources-Hardware with a number of systems analysis tools. This new method is used to analyze several tradespaces of an entry vehicle for human Mars missions utilizing a Hypersonic Inflatable Aerodynamic Decelerator and provide preliminary results. Key findings include quantifying how ballistic coefficient, main engine specific impulse, and thrust to weight ratio affect the cost of the vehicle and how the payload per lander and number of landers affects the cost of a campaign to Mars.
P. D. Friz et al., "A Cost Modeling Approach for Entry Systems Analysis of Human Mars Missions," Proceedings of the 2018 AIAA SPACE and Astronautics Forum and Exposition (2018, Orlando, FL), American Institute of Aeronautics and Astronautics (AIAA), Sep 2018.
The definitive version is available at https://doi.org/10.2514/6.2018-5177
AIAA Space and Astronautics Forum and Exposition, 2018 (2018: Sep. 17-19, Orlando, FL)
Mechanical and Aerospace Engineering
Keywords and Phrases
Cost estimating; Hypersonic vehicles; Life support systems (spacecraft); Martian surface analysis; Space flight; Systems analysis, Aerodynamic decelerators; Ballistic coefficient; Cost estimations; Human mars mission; Mission concepts; Planetary entry; Specific impulse; Thrust-to-weight ratio, Cost benefit analysis
International Standard Book Number (ISBN)
Article - Conference proceedings
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