216. Design of Take-Off Masses of Multiple Stage, ICBM-Type Rockets With Given Range and Payload Objectives

Paper

Abstract

This paper discusses design parameters which determine the take-off masses of multiple-stage rockets and the gross and burnout masses of their individual stages. An effective mass ratio of the rocket is defined, which takes into account the finite burnout masses of the stages as well as the effect of the payload mass on each stage. This effective mass ratio is shown to be optimally expressible in terms of the number of stages, a payload ratio and a structural factor, provided that the structural factor is not a function of the stages. For given range and payload mass of a rocket, the chosen parameters enable the prediction of necessary take-off mass and required number of stages. Several example problems are worked out, which illustrate a procedure for obtaining take-off mass and individual stage masses of ICBM-type rockets. The quantities which determine these masses are: initial thrust-to-weight ratio, specific impulse of the propellants, payload mass, range and realizable structural factor. The dependence of the take-off mass as well as the achievable range on the realizable structural factor is discussed quantitatively.