Research Article
Robust Design Optimization of an Aerospace Vehicle Prolusion System
Table 3
Propellant and nozzle parameters.
| Parameters | Value | Units |
| Propellant density | 1745 | kg/m3 | Grain burning rate | 8.5@7 MPa ± 1 | mm/sec | Characteristic velocity | 1560 | m/sec | Nozzle throat diameter | 90 | mm | Nozzle area expansion ratio () | 9 | — |
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