SpaceElevatorPerformance: Difference between revisions
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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 || $1000 || $1000 | ||
|} | |} | ||
Revision as of 18:47, 16 July 2008
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 re supported with as much information as possible.
| 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 | $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 |
