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The air breathing operates upto mach 5.14 and 28km (which is higher and faster than an SR71).

That would be about 5500km/h. The first stage of a falcoln 9 on the recent flight was 6,600kph and 91km high, so not a direct comparison but fairly close.

Re-entry heat shields is still going to be a problem if it goes to orbital velocity of 27kkph for something that's reusable.



The space plane ideas for using a Sabre engine are fairly early stage designs, since the whole engine isn't even a working prototype yet.

Of the various designs I've seen via wikipeda, Reaction Engines PR, and on-line forums, it seems that the thermal management proposals are :-

* Bigger lighter air frame will do more thermal soak than other spaceplanes (I mean, what else is there apart from Shuttle and X15?)

* Retain some fuel to be circulated through airframe during decent, and then used for powered landing

* Less intense re-entry profile to avoid sharp heat spike, but at expense of longer thermal load

* Avoid going all the way to orbit, using a small final booster for orbital insertion

If they can harvest enough LOx/air in the final ascent, then they could also do a retro burn I suppose.

Perhaps a mix of all these, plus heat shields. SpaceX are learning how to deal with similar issues right now too.


> what else is there apart from Shuttle and X15?

Buran, X-37 .


And soon hopefully Dream Chaser.


maaaaaybeee it could save enough fuel for a reentry burn?


No chance. This is more like maaaaybe single stage to orbit, though it wouldn't have a very big payload.




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