Preliminary vehicle design requires prediction of both specific impulse and stage net mass. At present, specific impulse calculation including various losses can be accomplished within a narrow margin of a few seconds by use of reliable theoretical and empirical data. The situation with vehicle net mass is different, since mass prediction is much more complicated. A new mass model for stage net mass is presented which is based on analytical correlations for the major vehicle masses and numerical fit of various parameters to existing and advanced stages. This model is applied for various selected propellants, mixed or dual propellant made to give stage performance prediction and characterization of advanced missions. A sensitivity analysis points out the limitation of a realistic prediction or design.
Rocket Stage Mass Model for Performance Prediction
1977
40 pages
Report
No indication
English
Rocket stage mass model for performance prediction
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