Experimental Study of Ejectors’ Effect on the Performance of Pulse Detonation Rocket Engine


Article Preview

Experimental studies were performed to investigate the ejector’s effect on the performance of a pulse detonation rocket engine (PDRE). The PDRE employed in the experiments utilizes gasoline as fuel and air as oxidizer. The operating frequency of the PDRE is 10 and 20 Hz respectively. Performance is quantified by thrust measurements, and the average thrust of the PDRE is obtained by integration of the thrust measured in the experiment. The experimental results show that the PDRE can increase thrust augmentation with an ejector, a maximum thrust augmentation is measured by 18.7% at 10 Hz operating frequency. In the experiment, axial placement (X/DPDRE) of the ejector is varied downstream the PDRE tube of 0.5,1 and 2 respectively. It is found that the thrust augmentation obviously increases when the relative position at 1 and 2, and also the thrust augmentation increases at higher operating frequency. The experiment result is useful for the development of a PDRE producing higher thrust.



Edited by:

Fangping Zhang




Q. D. Bai and C. S. Weng, "Experimental Study of Ejectors’ Effect on the Performance of Pulse Detonation Rocket Engine", Applied Mechanics and Materials, Vol. 628, pp. 293-298, 2014

Online since:

September 2014




* - Corresponding Author

[1] A. J. Glaser, N. Caldwell, E. Gutmark, J. Hoke, R Bradley and F. Schauer, 2007, Experimental study of ejectors driven by a pulse detonation engine, AIAA, 2007-447.

[2] T. H. Yi, D. R. Wilsony, F. K. Lu, Detonation wave propagation in an ejector-augmented pulse detonation rocket, AIAA, 2006-953.

DOI: https://doi.org/10.2514/6.2006-953

[3] X. Huang, C. Yan, Z. Wang, W. Fan and B. Jiang, Effect of operating frequency on performance of pulse detonation engine driven ejector, Journal of Aerospace Power, 23(2008) 401-405. [in Chinese].

[4] Y. Wang, W. Fan, C. Yan, X. Huang and K. Xie, 2008, Experimental investigation on ejector mode of a pulse detonation rocket engine, Journal of Projectiles,Rockets,Missiles and Guidance, 28(2008)139-141. [in Chinese].

[5] Y. Fan, J. Wang, J. Li, and Y. Zhang, Experimental investigation on thrust augmentation of pulsed detonation engine, Journal of Aerospace Power, 20(2005)983-988. [in Chinese].

[6] Y. Qin, J. Yu, G. Gao, Computational Analysis on the nozzle performance of pulse detonation engines, Journal of Aerospace Power, 25(2010) 366-372. [in Chinese].

[7] C. Weng, J. Wang, Q. Bai, and D. Ma, Experimental study on effect of inlet pressure on detonation in pulse detonation engine, Journal of Ballistics, 3(2008)1-4. [in Chinese].