/sci/ - Science & Math

I'm trying to design a reusable 2MN class RP1/LOX engine.

Should I go for oxidizer-rich staged combustion, or tap-off cycle? Alternatively, if I used propane instead of RP1 I could use the expander cycle.

From the last thread.

Describe an ideal low cost reusable launch system with a "mega-heavy" (1000+ tons) payload capacity, particularly for carrying modular segments for rotating torus habitats into orbit.