Rocket performance with constant radial thrust acceleration in vacuum

Abstract

In this paper is first found out the approximate altitude attained by the spacecraft in vacuum at any time after it is subjected to a constant radial thrust acceleration in vacuum, i.e., a variable thrust designated by constant thrust-to- weight ratio in the radial direction. The mass-variation law due to propellant consumption and the trajectory of the spacecraft in elliptic integral form in the neighborhood of the Earth  and thereafter in normal integral form with sufficient accuracy are determined