Orbital Storage of Cryogenic Propellants for Rendezvous Missions

This paper discusses analyses which have been conducted on realistic orbital launch booster vehicles utilizing cryogenic propellants. The effect on the design of the cryogenic stages of propellant performance, orbital storage period, and space environment is described, as is the influence of design variations upon the propellant loss rate in orbit of realistic orbital launch boosters. A thermal analysis from boost and transition through orbital conditions is also presented.