Possible engineering design solutions for development of heavy and super-heavy oxygen-kerosene space rocket

The paper presents the results of an independent design study into the feasibility of developing for the Super-Heavy Space Rocket (SHSR) with 140-170 tons payload capacity a modular Launch Vehicle (LV) in the form of a tri-pack cluster of three two-stage medium LVs Soyuz-5 and three side-mounted bi-pack clusters based on coupling together the first stages of LV Soyuz-5 based on NPO Energomash oxygen-kerosene main engines RD171MV, RD180, RD191M. In addition to this, the paper discusses the feasibility of using the tri-pack cluster from the SHSR as a standalone Heavy LV with an increased payload capacity (50-60 tons) to assure its more frequent use, and thus upkeep the operational reliability of the more powerful SHSR. The paper demonstrates the feasibility of designing the second-phase reusable versions of the first-stage clusters for SHSR and Heavy LV, as well as the feasibility of manned lunar missions using not two, but only one SHSR.