Abstract
Considering the need for accurate vaporization rates in the propellant combustion models, sublimation and vaporization rates of cyclotrimethylenetrinitramine (RDX) have been estimated over a wide range of temperatures. Simultaneous thermal analysis was carried at various slow heating rates, 5, 10, and 15°C/min, using a coupled TGA/DSC-FTIR system. In the solid phase, the mass loss occurs mainly due to the sublimation of RDX, whereas, in the liquid phase, both vaporization and thermal decomposition play a significant role. The extent of thermal decomposition was estimated using a computational model based on a recently developed detailed liquid-phase decomposition mechanism for RDX. For each of the heating rates, a suitable match between computational and experimental mass loss and species evolution profiles was achieved. As evident from the FTIR data, a major part of the mass loss occurs because of the evolution of decomposition products, such as N2 O, CH2 O, NO2, NO, HCN, H2 O, CO, and CO2 . Results show that vaporization accounts for 29.6, 34, and 35.9% of the total mass loss for the 5, 10, and 15°C/min heating rates, respectively. Relatively more RDX vaporizes at higher heating rates because of the initiation of the boiling phenomenon at higher sample temperatures.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 1098-1107 |
| Number of pages | 10 |
| Journal | Journal of Propulsion and Power |
| Volume | 35 |
| Issue number | 6 |
| DOIs | |
| State | Published - 2019 |
All Science Journal Classification (ASJC) codes
- Aerospace Engineering
- Fuel Technology
- Mechanical Engineering
- Space and Planetary Science
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