Abstract:
Preliminary staging studies of multi-stage space launchers
are described. Both propellant and thrust scaling factors are used, and
also cost parameters for propellant, propellant scaling units and thrust
scaling units. The general minimum cost study, including reusable
stage(s), turns out to be a generalisation of the optimisation method of
the payload ratio, for specified mission requirement. Both studies lead
to a velocity increment distribution between the stages, based upon
optimum initial acceleration for each stage. The similarity between this
analysis and that developed by Vertregt, Hall and Zambelli, and others
is pointed out. Penalties for non-optimum solutions are also considered.
