An Analysis of the Technical Characteristics and Performance of the Small Kosmos Launcher

B. Sanders (2001), JBIS, 54, 377-388

Refcode: 2001.54.377

Abstract:
The initial model showed a large deviation with the given performances and therefore some more detailed analyses were conducted. These included residual propellant mass estimates, hydrogen peroxide flow in the first stage, jet vane influence on the specific impulse and a fairing mass analysis. With the results a final model was constructed whose accuracy was within 5% of the reference satellite masses for various small Kosmos launcher missions. Furthermore a sensitivity analysis was performed to determine the influence of the different estimated parameters on the model performance (in terms of payload mass).