SpaceElevatorPerformance: Difference between revisions
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<tr><td colspan="3" align="center" style="background-color:#CCCCCC"><b>Title:</b> Performance</td></tr> | |||
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[Cover Img] | |||
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<b>About:</b><br /> | |||
* Moderator: [[Performance#edwards|Brad Edwards]]<br /> | |||
* Created: July 6, 2008<br /> | |||
* Modified: July 25, 2008<br /> | |||
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'''[[Article Tags|Tags]]''':<br /> | |||
* This is a collaborative article<br /> | |||
* Discipline(s): Wiki, Engineering | |||
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__TOC__ | |||
<div style='clear:right'> </div> | |||
== Performance == | == Performance == | ||
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All values in this table need to | All values in this table need to supported with solid arguments and calculations. | ||
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|width="150pt"|Desired | |width="150pt"|Desired | ||
|width="150pt"|Expected | |width="150pt"|Expected | ||
|- | |- | ||
|Payload mass || 100 || 100 | |Payload mass || 100 || 100 | ||
|- | |- | ||
|Max speed of ascent || 1000 kph || 200 kph | |Max speed of ascent || 1000 kph || 200 kph | ||
|- | |- | ||
|Time to GEO || 1 day || 1 week | |Time to GEO || 1 day || 1 week | ||
|- | |- | ||
|Time to Moon || 4 days || 10 days | |Time to Moon || 4 days || 10 days | ||
|- | |- | ||
|Time to Mars || 1 month || 3 months | |Time to Mars || 1 month || 3 months | ||
|- | |- | ||
|Size limitations || | |Size limitations || None || limited by wind loading | ||
|- | |- | ||
|Radiation load || | |Radiation load || None || TBD | ||
|- | |- | ||
|Launches per year || 365 || 200 | |Launches per year || 365 || 200 | ||
|- | |- | ||
|Cost per kg to LEO || $100 || $1000 | |Cost per kg to LEO || $100 || $1000 | ||
|- | |- | ||
|Cost per kg to GEO || $100 || $1000 | |Cost per kg to GEO || $100 || $1000 | ||
|- | |- | ||
|Cost per kg to Moon || $1000 || $1000 | |Cost per kg to Moon, Mars,... || $1000 || $1000 | ||
|} | |} | ||
== Major Development Issues Related to this Component == | |||
None at this time | |||
== Additional Work Needed == | |||
{| border="1" cellpadding="2" | |||
|- | |||
|width="200pt"| Item | |||
|width="400pt"| Notes | |||
|width="300pt"| Completed and Ongoing Efforts | |||
|- | |||
|Detailed transit calculations || Detailed orbital mechanic calculations from Earth to all conceivable destinations. Include standard orbit transfers as well as stopping at the destination. Consider rocket braking and elevator capture || | |||
*[[Need file name here| Initial spreadsheet on transfers]] | |||
*[[SEPerformance_1_1| Work Space #1 - Open for use]] | |||
*[[SEPerformance_1_2| Work Space #2 - Open for use]] | |||
*[[SEPerformance_1_3| Work Space #3 - Open for use]] | |||
|- | |||
|Cargo size for different operational scenarios || This pertains to the differences between cargo size that can be lifted from Earth to GEO vs. cargo sizes that can be assembled at GEO then thrown to their final destination || | |||
*Some work in lunar proposal by Edwards et.al. | |||
*[[SEPerformance_2_1| Work Space #1 - Open for use]] | |||
*[[SEPerformance_2_2| Work Space #2 - Open for use]] | |||
*[[SEPerformance_2_3| Work Space #3 - Open for use]] | |||
|} | |||
[[SpaceElevatorWikiOverview| Return to Overview]] | [[SpaceElevatorWikiOverview| Return to Overview]] | ||
Latest revision as of 21:39, 26 July 2008
| Title: Performance | ||
|
[Cover Img] |
About:
|
Tags:
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Performance
Here we will define the performance desired and the expected performance. This will help define what areas are most critical for development.
All values in this table need to supported with solid arguments and calculations.
| Desired | Expected | |
| Payload mass | 100 | 100 |
| Max speed of ascent | 1000 kph | 200 kph |
| Time to GEO | 1 day | 1 week |
| Time to Moon | 4 days | 10 days |
| Time to Mars | 1 month | 3 months |
| Size limitations | None | limited by wind loading |
| Radiation load | None | TBD |
| Launches per year | 365 | 200 |
| Cost per kg to LEO | $100 | $1000 |
| Cost per kg to GEO | $100 | $1000 |
| Cost per kg to Moon, Mars,... | $1000 | $1000 |
Major Development Issues Related to this Component
None at this time
Additional Work Needed
| Item | Notes | Completed and Ongoing Efforts |
| Detailed transit calculations | Detailed orbital mechanic calculations from Earth to all conceivable destinations. Include standard orbit transfers as well as stopping at the destination. Consider rocket braking and elevator capture | |
| Cargo size for different operational scenarios | This pertains to the differences between cargo size that can be lifted from Earth to GEO vs. cargo sizes that can be assembled at GEO then thrown to their final destination |
|
