Large diameter liquid propulsion rockets with small engines require so many rockets to generate the takeoff thrust. This makes the piping complex. I had previously proposed cascaded propellant tanks. This idea can be enhanced to solve two problems. I propose cascading multiple fuel and oxidizer tanks one after the other. Each engine would be placed on the boundary between the propellant and the oxidizer tanks. Therefore, the engine would be fed directly from the tanks with shortest possible piping. There would be no branching of pipes as well. These cascaded tanks would have thin separators while the pressure and temperature on both sides would be similar. These separators also support the dome of the propellant container which would be quite large in diameter. The cascaded tanks with same propellant will have connections between them to level out consumption differences.
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