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You are right. Energy management for landing on a runway will be much more difficult for the REX than in LEX because in LEX we drop from a helicopter, and in REX we drop from space. Here is an interesting and detailed video that highlights the difference between LEX and REX:-On contrary, I think REX would be more complex in nature then LEX. It would mean that you would have to consider avionics along with fluid dynamics when returning from a suborbital flight. Our first splash down test was from mere 65 km and it was a splash down test. But after LEX when we would be carrying out REX, we would be landing the RLV rather then splashing it down. So I think it would be more of a challenge to us.
Now I assume REX will not have a de-orbit burn (no engines) or a descent from LEO (no way to initiate), but will still be a very challenging task. Even so, the last part of the landing should be simple after LEX. So the only difference would be programming something similar to TAEM (Terminal Area Energy Management) as shown in this video. How long can that take? IMHO, not more than two years at the most. So if LEX is within this year, REX will be 2020? Hopefully its not delayed beyond that.
BTW any idea about the rocket they are using for the REX? And what altitude will the RLV TD reach before descent?