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Comparing NASA and ESA Cost Estimating Methods for Human Missions to Mars
An RLV/ Shuttle Compatible Habitation System
Bonin, Grant1 (2004)
Luna And Mars For Less: A Medium-Lift Launch System Architecture For The Vision For Space Exploration
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In: On To Mars 2, edited by Zubrin, RM, and Crossman, F. Collector's Guide Publishing Inc.
The current Vision for Space Exploration (VSE) requires near-term, developmentally simple manned expeditions to the moon and Mars to restore confidence in American programs of human spaceflight. Pursuant to these requirements, it may be necessary that robust, cost-sustainable mission architectures be initially de-prioritized in favor of those which – while more operationally complex – are programmatically easier to initiate with current technology.
This study proposes a method of undertaking manned expeditions to the moon and Mars with existing medium-lift launch systems. In this architecture, 20-tonne high energy propulsion stages are placed individually in low-Earth orbit, where they are mated to moon or Mars-bound spacecraft and ignited at successive perigees to execute trans-planetary injections. Contrary to NASA mission plans which utilize evolved expendable launch vehicles (EELVs), this architecture does not require complex spacecraft systems integration on orbit, nor does it necessitate orbital construction beyond initial spacecraft rendezvous and docking. Most significantly, the mission architecture in this paper does not require the development of heavy-lift launch vehicles (HLLVs): highly effective yet costly prerequisites which could fatally hinder the current Vision for Space Exploration. It is concluded that the mission design herein represents a less robust, though easier to develop method of conducting manned expeditions to the moon and Mars than current EELV or HLLV-based mission designs – an alternative method by which space may be opened to humanity.
This study proposes a method of undertaking manned expeditions to the moon and Mars with existing medium-lift launch systems. In this architecture, 20-tonne high energy propulsion stages are placed individually in low-Earth orbit, where they are mated to moon or Mars-bound spacecraft and ignited at successive perigees to execute trans-planetary injections. Contrary to NASA mission plans which utilize evolved expendable launch vehicles (EELVs), this architecture does not require complex spacecraft systems integration on orbit, nor does it necessitate orbital construction beyond initial spacecraft rendezvous and docking. Most significantly, the mission architecture in this paper does not require the development of heavy-lift launch vehicles (HLLVs): highly effective yet costly prerequisites which could fatally hinder the current Vision for Space Exploration. It is concluded that the mission design herein represents a less robust, though easier to develop method of conducting manned expeditions to the moon and Mars than current EELV or HLLV-based mission designs – an alternative method by which space may be opened to humanity.
1 - Aerospace Structures and Design, Carleton University, 1938 Banff Ave., Ottawa ON. K1V 7X4, Phone: (613) 526 3650 email or homepage
Mars Mission Planning and Engineering
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by
Jean Lagarde
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last modified
2006-10-22 23:03
Copyright © 2004 by Grant Bonin. Published by The Mars Society with permission
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