Determining criteria for single stage to orbit

Abstract

The criteria for single stage to orbit (SSTO) vehicles are determined. The Saturn 5 launch vehicle and Space Shuttle are examined to validate the assumptions and results. This velocity is then used to determine if the selected vehicle can achieve orbit and calculate its payload capacity. The Saturn 5 launch vehicle with the following stages is examined: (1) second stage (S2) with Space Shuttle Main Engines (SSME); (2) second stage (S2) with J2 engines; (3) third stage (S4B) with SSME; and (4) third stage (S4B) with J2 engines. The Space Shuttle with the following configurations is examined: (1) external tank with SSME; (2) external tank with J2 engines; and (3) Atlas rocket booster (current configuration).