Abstract

This paper gives an overview of the multi-stage rocket engine design for placing the required payload into the MARS Orbit. The design process technique including an iterative process for the stage optimization has been discussed. The optimization technique, based on the Lagrange parameter, is investigated for suitably choosing the number of stages. The primary objective of the paper is to present the various design methodology adopted while designing the launch vehicle, its propulsion system and its subsystem. Besides it also predicts engines key performance parameters. Design constrains such as structural coefficient, chamber pressure, chamber temperature etc., are considered. This paper briefly summarize the aerothermodynamics design procedure and mechanical component design aspect.