Publication Date:
2019-07-13
Description:
Earlier concepts for the Mars Sample Return mission were complex and costly, and had little chance of being funded. This paper summarizes the evolution of a concept that permitted cost to be reduced by a factor of six, and the number of spacecraft elements to be halved. The primary feature of this low cost/low complexity concept is the application of advanced lightweight propulsion, materials, power, and avionics technology to the Mars Ascent Vehicle to make a direct return from Mars feasible. Mission parameters, launch mass breakdowns, spacecraft configuration drawings, technology requirements, and cost estimates are presented.
Keywords:
ASTRONAUTICS (GENERAL)
Type:
AAS PAPER 91-498
,
AAS/AIAA Astrodynamics Conference; Aug 19, 1991 - Aug 22, 1991; Durango, CO; United States
Format:
text
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