Paper
Launching Process for Variable-Mass Rockets by Series Solution
- Authors:
- M. Gorji; D. D. Ganji; M. Hatami; A. Hasanpour; A. K. Hossein
- Abstract
- In this study, the mathematical investigation of rocket motion path is presented using analytical and numerical methods. Differential transform method and fourth-order Runge-Kutta method are used for solving the current problem. A parametric study is performed which includes the effect of exhaust velocity (Ce), burn rate (BR) of fuel and diameter of cylindrical rocket (d) on the motion of a sample rocket. Also a realistic comparison of four on-line and active rockets is presented and the result is discussed. The main results indicate that the present analytical technique has high accuracy in comparison with the numerical solution. It is illustrated that the rocket velocity and altitude are increased with increasing the Ce and BR and decreased with increasing the rocket diameter. Finally it is concluded that Mu-3S-II rocket reaches to higher velocities and altitudes faster in comparison with the other introduced rockets.
- Keywords
- Modeling; Exhaust Velocity; Burn Rate; Rocket Motion Path
- StartPage
- 13
- EndPage
- 20
- Doi
- 10.18005/JMET0101003