Abstract
A numerical simulation of the gas-dynamic processes in the thrust vectorable nozzle of the solid rocket motor is considered. Construction of a geometric model and a generation of computational mesh, and reconstruction of model and mesh at each time step are discussed. Calculations of the flowfield of combustion products in the pre-nozzle chamber and nozzle block are carried out for various angles of nozzle rotation. The distributions of the gas dynamic quantities in the pre-nozzle volume corresponding to the outflow of the combustion products from the cylindrical channel and star-shaped channel are compared, as well as the solutions of the problem obtained with quasi-stationary and unsteady formulations. The effects of the channel shape on the distribution of flow quantities and formation of a vortical flow structure in the nozzle block are discussed.
| Original language | English |
|---|---|
| Article number | e278 |
| Journal | Fluids |
| Volume | 6 |
| Issue number | 8 |
| Early online date | 10 Aug 2021 |
| DOIs | |
| Publication status | Published - 31 Aug 2021 |
Keywords
- Mechanical, aeronautical and manufacturing engineering
- numerical simulation
- solid rocket motor
- submerged nozzle
- thrust
- vectorable nozzle
- vortical structure