Abstract
An optimization procedure of the thrust programming is stated for a rocket which is required to reach a maximum altitude with given initial and propellant weight. The problem of thrust programming is treated as that of the pressure programming. The chamber pressure is assumed as a polygonal function of time. The problem is solved numerically by a multipe-parameter optimization technique. The analysis is performed on a rocket with arbitrary drag coefficient flying in a vertical plane wherein the gravity and the properties of atmosphere are known as functions of altitude. The relation between this method and the design procedure of a sounding rocket is stated.
