NASA’s Mars Study Capability Team continues the agency’s efforts to study and refine the nation’s plan to field a sustainable human Mars campaign. One of the primary open issues left unanswered during previous analysis cycles was the uncertainty of the impact to the vehicle performance requirement to deliver crew and cargo to the same landing site across multiple mission opportunities. The Mars Study Capability Team has recently developed an integrated trajectory optimization and system closure model to solve the complex interplanetary trajectory optimization using both low-thrust and high-thrust maneuvers. This paper demonstrates the capability of this new integrated trajectory design and optimization method as it applies to the landing site accessibility problem for the Hybrid transportation architecture. The results showed that the current vehicle is capable of reaching up to +20 degree latitude and down to -20 degree latitude in every mission opportunity from 2033 to 2052. However, reaching latitudes beyond +/- 20 required more propellant than the spacecraft is currently designed to carry for many of the mission opportunities.
Hybrid Transportation System Integrated Trajectory Design and Optimization for Mars Landing Site Accessibility
2019 AIAA Propulsion and Energy Forum ; 2019 ; Indianapolis, IN, United States
2019-08-19
Aufsatz (Konferenz)
Keine Angabe
Englisch
Powered-descent trajectory optimization scheme for Mars landing
Elsevier | 2013
|Powered-descent trajectory optimization scheme for Mars landing
Online Contents | 2013
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