Performance Optimization of Aerospike Nozzle Geometrical Profiles

Abstract

A rocket engine nozzle is a propelling nozzle used in a rocket engine to expand and accelerate the
combustion gases produced by burning propellants so that the exhaust gases exit the nozzle at hypersonic velocities.
The primary nozzle contour is approximated by two circular arcs and a parabola. Compared with conventional rocket
engine, aerospike nozzle engine characterized by small scale, lightweight, high performance during all altitudes and
better utilization of the vehicle base is the promising candidate for the propulsion device of future advanced launching
vehicle. Aerospike nozzle technology is the key technology of aerospike nozzle rocket engine. Aerospike nozzle is a type
of nozzle with capacity of continuous altitude compensation. Aerospike nozzle is considered to have better performance
at off- design altitudes compared with that of the conventional bell-shaped nozzle since its plume is open to the
atmosphere outside and free to adjust, allowing the engine to operate at its optimum expansion at all altitudes. An
Aerospike nozzle model is selected for evaluating for maximum thrust at minimum weight therefore, a model of
aerospike rocket nozzle has been developed and for giving our main objective i.e., maximum thrust at minimum stress,
So modifying its geometrical shapes and hence the contour shape will definitely be change. These different shapes are
as, Cubical contour shape, Cubical parabolic contour profile. Semi cubical parabolic contour shape. This includes
predictions of nozzle thrust, nozzle weight, and effective vehicle gross-liftoff weight. The contour of the aerospike nozzle
has been designed for maximum thrust at one design condition out of all these three conditions