Solid and hybrid propulsion analysis
Although the tool was actually intended for analysis of liquid propulsion systems, it can also be used for the thermodynamic analysis and performance prediction both solid and hybrid rocket engines. RPA obtains the proper combustion composition from any type of solid/hybrid propellants, including metalized ones. The calculation of performance parameters for multiphase flows with phase transition is also possible.
Thermodynamic data library is prepackaged with a number of solid propellant components, such as ammonium perchlorate (NH4CLO4),
ammonium nitrate (NH4NO3), potassium nitrate (KNO3), aluminium, magnesium, zinc, HTPB, sorbitol, wax paraffin, and other.
Examples
P80 - first stage engine of VEGA Launcher
Design parameters
| Parameter |
Value |
Unit |
| Propellant |
HTPB 1912
| Component |
Mass fraction |
| NH4ClO4 | 0.69 |
| Al | 0.19 |
| HTPB | 0.12 |
|
- |
| Combustion chamber pressure |
9.5 |
MPa |
| Nozzle exit area ratio |
16.0 |
Ae/At |
Comparison of actual and calculated engine parameters
| Parameter |
Actual |
RPA |
Percent error |
| Specific impulse (vac), s |
279.5 |
274.71 |
1.7 % |
Download P80 configuration file
Hybrid rocket engine for Peregrine sounding rocket
Design parameters
| Parameter |
Value |
Unit |
| Oxidizer |
Nitrous oxide (Liquid) |
- |
| Fuel |
Wax paraffin |
- |
| Components mass ratio |
4.0654 |
O/F |
| Combustion chamber pressure |
700 |
psi |
| Nozzle exit area ratio |
8.4 |
Ae/At |
Comparison of actual and calculated engine parameters
| Parameter |
Actual |
RPA |
Percent error |
| Specific impulse (vac), s |
232 |
234.3 |
1.0 % |
Download Peregrine propulsion configuration file
