Modeling of HTPB Regression for N2O-fed Hybrid Rocket Motor
- Paper number
IAC-07-C4.2.08
- Author
Dr. Vadim Zakirov, Tsinghua University, China
- Coauthor
Fan-li Shan, China
- Coauthor
Dr. Haiyun Zhang, Tsinghua University, China
- Year
2007
- Abstract
This paper presents a computer model simulating performance of hybrid rocket motor using hydroxyl-terminated polybutadiene (HTPB or rubber) solid fuel and nitrous oxide (N2O) oxidizer. HTPB solid fuel regression obtained during firing of lab-scale hybrid rocket motor is given in Figure 1. The experimental data were integrated into the computer model simulating solid fuel regression, hybrid rocket motor thrust and specific impulse performance during firing. The computer model results are in good agreement with the experiment. The model is intended for performance assessments of scaled N2O-fed hybrid rocket motors.
- Abstract document