/sci/ - Science & Math

>>12389114
The RS-2200 and the other test powerhead were both based on unchanged plumbing from LOX/LH2 engines, I'm not convinced that all of the negatives associated with them are universal to the design. Even if you would have to take a hit to absolute TWR they're still useful as a "universal" engine that can be used in both stages of a two-stage rocket, since they stick close to the optimal efficiency curve at all pressures between 1 bar and vacuum.
If you design large diameter engines you can also use them as a transpiration cooled heatshield that can seamlessly transition into propulsive landing.
Your second stage can essentially be a gigantic capsule, except that instead of parachuting down it can perform a propulsive landing, presumably somewhat like what was proposed for Red Dragon.