Title:
Sizing of an Entry, Descent, and Landing System for Human Mars Exploration
Sizing of an Entry, Descent, and Landing System for Human Mars Exploration
| dc.contributor.author | Christian, John A., III | |
| dc.contributor.author | Wells, Grant William | |
| dc.contributor.author | Lafleur, Jarret M. | |
| dc.contributor.author | Manyapu, Kavya | |
| dc.contributor.author | Verges, Amanda | |
| dc.contributor.author | Lewis, Charity | |
| dc.contributor.author | Braun, Robert D. | |
| dc.contributor.corporatename | American Institute of Aeronautics and Astronautics | |
| dc.date.accessioned | 2007-06-08T18:00:23Z | |
| dc.date.available | 2007-06-08T18:00:23Z | |
| dc.date.issued | 2006-09 | |
| dc.description | AIAA Space 2006 Conference September 2006, San Jose, CA. | en_US |
| dc.description.abstract | The human exploration of Mars presents many challenges, not least of which is the task of entry, descent, and landing (EDL). Because human-class missions are expected to have landed masses on the order of 40 to 80 metric tons, significant challenges arise that have not been seen to date in robotic missions. This study provides insight into the challenges encountered as well as potential solutions through parametric trade studies on vehicle size and mass. Aerocapture and entry-from-orbit analyses of 10 and 15 m diameter aeroshells with a lift-to-drag ratio of 0.3 or 0.5 were investigated. Results indicate that in the limit, a crew capsule used only for descent could have an initial mass as low as 20 t. For larger landed payloads, such as a 20 t surface power system, a vehicle with an initial mass on the order of 80 t may be required. In addition, no feasible EDL systems were obtained with the capability to deliver more than approximately 25 t of landed payload to the Mars surface for initial masses less than 100 t. This suggests that an aeroshell diameter of 15 m may not be sufficient for human Mars exploration. | en_US |
| dc.identifier.uri | http://hdl.handle.net/1853/14740 | |
| dc.language.iso | en_US | en_US |
| dc.publisher | Georgia Institute of Technology | en_US |
| dc.publisher.original | American Institute of Aeronautics and Astronautics (AIAA) | |
| dc.relation.ispartofseries | SSDL ; AIAA 2006-7427 | en_US |
| dc.subject | Aerocapture trajectories | en_US |
| dc.subject | Entry, descent and landing (EDL) technology | en_US |
| dc.subject | Entry-from-orbit | en_US |
| dc.subject | Orbital maneuvering | en_US |
| dc.subject | Payloads | en_US |
| dc.subject | Robotic missions | en_US |
| dc.subject | Spacecraft | en_US |
| dc.subject | Trajectories | en_US |
| dc.title | Sizing of an Entry, Descent, and Landing System for Human Mars Exploration | en_US |
| dc.type | Text | |
| dc.type.genre | Paper | |
| dspace.entity.type | Publication | |
| local.contributor.corporatename | Space Systems Design Laboratory (SSDL) | |
| local.contributor.corporatename | Daniel Guggenheim School of Aerospace Engineering | |
| relation.isOrgUnitOfPublication | dc68da3d-4cfe-4508-a4b0-35ba8de923fb | |
| relation.isOrgUnitOfPublication | a348b767-ea7e-4789-af1f-1f1d5925fb65 |