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Study of advanced atmospheric entry systems for mars
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1978 |
| Description | 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. |
| File Size | 4992373 |
| Page Count | 94 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19780023083 |
| Archival Resource Key | ark:/13960/t8wb0002g |
| Language | English |
| Publisher Date | 1978-07-01 |
| Access Restriction | Open |
| Subject Keyword | Lunar And Planetary Exploration Aerospace Planes Space Shuttle Payloads Descent Trajectories Atmospheric Entry Aerospace Engineering Mars Exploration Mars Probes Systems Engineering Viking Lander Spacecraft Mars Sample Return Missions Mission Planning Mars Landing Space Capsules Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
