Abstract
The design of the inner contour of solid propellant rocket motor nozzle is a key point to improve the efficiency of the nozzle. Based on Genetic Algorithms, a direct optimization method was used to optimize the key parameters determining the inner contour of the nozzle, to reduce the specific impulse loss and improve the efficiency of the engine. The specific impulse was obtained from two-phase flow calculation of the nozzle. Furthermore, a software interface was designed to automatically realize the contour optimization design for the general nozzle. As a result, good effect was obtained from the optimal computation for the current nozzle.
| Original language | English |
|---|---|
| Pages (from-to) | 8-14 |
| Number of pages | 7 |
| Journal | Tuijin Jishu/Journal of Propulsion Technology |
| Volume | 34 |
| Issue number | 1 |
| State | Published - Jan 2013 |
| Externally published | Yes |
Keywords
- Genetic Algorithms
- Loss of the two-phase flow
- Nozzle contour optimization