Several concepts of chemical-propulsion Space Vehicles (SVs) for manned Mars landing missions are presented. For vehicle sizing purposes, several specific missions were chosen from opportunities in the late 1990's and early 2000's, and a vehicle system concept is then described which is applicable to the full range of missions and opportunities available. In general, missions utilizing planetary opposition alignments can be done with smaller vehicles than those utilizing planetary opposition alignments. The conjunction missions have a total mission time of about 3 years, including a required stay-time of about 60 days. Both types of missions might be desirable during a Mars program, the opposition type for early low-risk missions and/or for later unmanned cargo missions, and the conjunction type for more extensive science/exploration missions and/or for Mars base activities. Since the opposition missions appeared to drive the SV size more severely, there were probably more cases examined for them. Some of the concepts presented utilize all-propulsive braking, some utilize and all aerobraking approach, and some are hybrids. Weight statements are provided for various cases. Most of the work was done on 0-g vehicle concepts, but partial-g and 1-g concepts are also provided and discussed. Several options for habitable elements are shown, such as large-diameter modules and space station (SS) types of modules.
Space Vehicle Concepts
1986
26 pages
Report
Keine Angabe
Englisch
NTRS | 1986
|Mission and Space Vehicle Concepts
NTRS | 1986
|Reusable Space Launch Vehicle Concepts: Outlook 1965
SAE Technical Papers | 1965
|Reusable space launch vehicle concepts -- Outlook 1965
Engineering Index Backfile | 1965
|MISSILE AND SPACE VEHICLE NON-PROPULSIVE POWER CONCEPTS
SAE Technical Papers | 1960
|