Abstract
A system analysis program for the preliminary design of a liquid rocket engine is developed to analyze performance according to the input variables and the requirements needed. It contains sub-system analysis program modules that include the main thrust chamber, gasgenerator, turbo pumps, and turbine. The hydraulic system, which includes pipes, valves, and elbows, is considered to measure mass and pressure loss. The analysis process is developed to satisfy energy balance, mass-flow balance, and pressure balance. It also determines the design parameters with a higher specific impulse and thrust-to-weight ratio based on the genetic algorithm. The results of the program analysis are consistent with the reference of existing liquid rocket engines. The developed program is acceptable as a preliminary design process for a liquid rocket engine.
| Original language | English |
|---|---|
| Pages (from-to) | 2375-2380 |
| Number of pages | 6 |
| Journal | Journal of Mechanical Science and Technology |
| Volume | 29 |
| Issue number | 6 |
| DOIs | |
| State | Published - 13 Jun 2015 |
Bibliographical note
Publisher Copyright:© 2015, The Korean Society of Mechanical Engineers and Springer-Verlag Berlin Heidelberg.
Keywords
- Design optimization
- Genetic algorithm
- Liquid rocket engine
- Space launch vehicle