Timeline for Merging Shuttle and External Tank to reduce reentry heating
Current License: CC BY-SA 4.0
9 events
| when toggle format | what | by | license | comment | |
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| Sep 7, 2021 at 13:18 | comment | added | Abdullah is not an Amalekite | @J... yes, that's a very important point that may even completeky invalidate the answer. | |
| S Aug 24, 2021 at 21:06 | history | suggested | ThatCoolCoder | CC BY-SA 4.0 |
change isolation to insulation and change 'an' to 'this' to make the char count
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| Aug 24, 2021 at 9:18 | review | Suggested edits | |||
| S Aug 24, 2021 at 21:06 | |||||
| Aug 23, 2021 at 11:49 | comment | added | DrSheldon | You're correct that mass would be transferred to the orbiter, but I don't think it would be as severe as noted in the answer. The dry weight of the ET included more than just propellant tanks. A considerable part of the dry weight was structure to transfer the SRB thrust to the orbiter. You can delete much of that structure if you move the tanks into the orbiter. In any case, you're right that it lowers the payload capacity. | |
| Aug 22, 2021 at 20:28 | history | edited | Uwe | CC BY-SA 4.0 |
added 217 characters in body
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| Aug 22, 2021 at 20:16 | history | edited | Uwe | CC BY-SA 4.0 |
added 217 characters in body
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| Aug 22, 2021 at 14:54 | comment | added | J... | The space shuttle did carry the external tank effectively all the way to orbit - it was jettisoned just short of orbital velocity with a perigee still in the atmosphere. The OMS did a final orbital insertion and circularization manoeuvre, but the total delta-v requirement there is quite small. | |
| Aug 22, 2021 at 3:06 | comment | added | Abdullah is not an Amalekite | It would be a 1.5 stage, the same way it was. | |
| Aug 21, 2021 at 19:34 | history | answered | Uwe | CC BY-SA 4.0 |