Abstract
To study the thermo-impact and the dynamical impact of the exhaust plume to the launching platform, the finite rate chemistry model and H2/CO chemistry system were used to simulate the afterburning phenomenon of plume. The temperature and pressure on the launching platform and the exhaust plume contours were obtained. The simulated results were in accordance with that of experiment. The results show that it is reasonable to calculate the close range exhaust plume in considering the afterburning. The launching platform centre region is the high temperature zone and should be defended by the high temperature resistant material. In the range of 1.4 m, 1.7 m and 2 m apart of the motor nozzle, the pressure is less influenced by the distance and the temperature decreases with the distance increase.
| Original language | English |
|---|---|
| Pages (from-to) | 373-376+395 |
| Journal | Guti Huojian Jishu/Journal of Solid Rocket Technology |
| Volume | 33 |
| Issue number | 4 |
| Publication status | Published - Aug 2010 |
Keywords
- Exhaust plume
- Finite-rate chemistry reaction model
- Impact effect
- Rocket motor