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Mars vehicle tcs and aerobrake tps
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Comer, G. |
| Copyright Year | 1986 |
| Description | General design approach, some problems and technology needs for a Mars vehicle manned module Thermal Control System (TCS) and aerobrake Thermal Protection System (TPS) are discussed. The design approach of the TCS will be similar to that of the space station. Mars atmospheric dust storms are identified as an unknown that will impact the design of the Mars landing vehicle and base facility. New technology may be needed for thermal control surfaces to functionally survive the dust storms. The TPS for the Mars aerocapture vehicle will be subject to marginal stagnation heating rates for conjunction class missions and very high heating rates for opposition class missions. New technology TPS materials or an ablative heat shield will be required for the high stagnation heating rate trajectories. No significantly new technology is needed for the manned modules that do not descent to the Mars surface. |
| File Size | 227935 |
| Page Count | 6 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19870008352 |
| Archival Resource Key | ark:/13960/t0ps2p239 |
| Language | English |
| Publisher Date | 1986-05-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Design, Testing And Performance Thermal Protection Aerodynamic Heating Mars Planet Heat Shielding Ablative Materials Mars Surface Temperature Control Manned Space Flight Aerobraking Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
