Abstract:

A program for preliminary prediction of mass and performance of solid propellant rockets for space applications is presented. The prediction accuracy of the program is demonstrated by presenting the results for ARIANE 5 and TITAN 4 SRMU boosters.

As an example for a complete new design a two staged, DSL-air-launched solid propellant rocket design is performed. An estimated payload mass close to 7000 kg for ISS-orbit is achievable.

Atmospheric environmental impacts due to the combustion process are described. The deposition of the major combustion products into the different atmospheric layers is quantified.

DGLR JT-97-151 is in German