Mathematics – Logic
Scientific paper
Jul 1978
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1978mmc..rept......&link_type=abstract
Final Report Martin Marietta Corp., Denver, CO.
Mathematics
Logic
Aerospace Engineering, Atmospheric Entry, Mars Probes, Mission Planning, Systems Engineering, Aerospace Planes, Descent Trajectories, Mars Landing, Mars Sample Return Missions, Space Capsules, Space Shuttle Payloads, Viking Lander Spacecraft
Scientific paper
Entry system designs are described for various advanced Mars missions including sample return, hard lander, and Mars airplane. The Mars exploration systems for sample return and the hard lander require decleration from direct approach entry velocities of about 6 km/s to terminal velocities consistent with surface landing requirements. The Mars airplane entry system is decelerated from orbit at 4.6 km/s to deployment near the surface. Mass performance characteristics of major elements of the Mass performance characteristics are estimated for the major elements of the required entry systems using Viking technology or logical extensions of technology in order to provide a common basis of comparison for the three entry modes mission mode approaches. The entry systems, although not optimized, are based on Viking designs and reflect current hardware performance capability and realistic mass relationships.
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