Open Access
Table 4.
Design variables for the two-stage rocket.
| Variables | Symbol | Domain of definition | Baseline |
|---|---|---|---|
| 1st stage nozzle throat diameter | Dt1 | [0.05, 1] m | 0.75 m |
| 2nd stage nozzle throat diameter | Dt2 | [0.05, 1] m | 0.75 m |
| 1st stage nozzle exit diameter | Ds1 | [0.5, 1.4] m | 1 m |
| 2nd stage nozzle exit diameter | Ds2 | [0.5, 1.4] m | 1 m |
| 1st stage combustion pressure | Pc1 | [1, 500] bar | 100 bar |
| 2nd stage combustion pressure | Pc2 | [1, 500] bar | 100 bar |
| 1st stage propellant mass | Mp1 | [2000, 15 000] kg | 8000 kg |
| 2nd stage propellant mass | Mp1 | [2000, 15 000] kg | 8000 kg |
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