|کد مقاله||کد نشریه||سال انتشار||مقاله انگلیسی||ترجمه فارسی||نسخه تمام متن|
|648357||1457194||2010||9 صفحه PDF||سفارش دهید||دانلود رایگان|
As the propagation time of detonation is very short in the actual operation process of a pulse detonation rocket engine (PDRE), the gases expelled slightly from the detonation chamber in this process is negligible. Therefore, a mathematical model of constant volume cycle (CVC) can be used to approximately depict the operation process of PDRE. Based on CVC model, a systematic analysis of PDRE’s performance is conducted in this paper. Combined CVC model with Chemical Equilibrium and Applications (CEA) code, the specific impulse of PDRE using different propellants could be obtained. Utilizing this model, the specific impulse of kerosene/oxygen PDRE in vacuum and at finite backpressures is estimated. When the backpressure exists, there is an optimum nozzle area expansion ratio in the nozzle design of PDRE, similar to conventional steady-state rocket. The performance of PDRE and conventional steady rocket is compared respectively, under the two conditions of the same supply system and the same maximum material stress. When PDRE and conventional steady rocket have a comparable performance, the filling pressure of PDRE is much lower than that of steady rocket.
Journal: Applied Thermal Engineering - Volume 30, Issues 11–12, August 2010, Pages 1496–1504