Provide graduates with hands-on training and experience in the field of aerospace propulsion and combustion.
Exploring innovative solutions in Aerospace propulsion and combustion for future space applications with sustainability in mind
The SIA ASPC hybrid rocket consists of a liquid nitrous oxide/paraffin-based fuel capable to produce 200 N thrust for research activities. the rocket is equipped with:
- C4H10 / N2O pilot flame ignitor by a spark
- pyrotechnic system based
- NiCr-Ni based K Thermocouple for Temperature Sensors: in the pre-combustion and the post-combustion chamber.
- Three pressure sensors located respectively upstream the fuel injection, in the pre-combustion and in the post-combustion chamber
- A digital flux meter sensor to measure the N2O mass flow rate
- Arduino system
- Desktop PC
- 1 relief valve in the pre-combustion chamber that opens above 30 atm
- 5 check valves
NUMERICAL SIMULATIONS OF HYBRID ROCKET
Pressure flow-field
Temperature flow-field
C2H4 Mass fraction
H2O mass fraction