| FUNDAMENTAL AREAS OF PHENOMENOLOGY(INCLUDING APPLICATIONS) |
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Thrust Vectoring of a Continuous Rotating Detonation Engine by Changing the Local Injection Pressure |
| LIU Shi-Jie**, LIN Zhi-Yong, SUN Ming-Bo, LIU Wei-Dong
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Science and Technology on Scramjet Lab, National University of Defense Technology, Changsha 410073
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| Cite this article: |
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LIU Shi-Jie, LIN Zhi-Yong, SUN Ming-Bo et al 2011 Chin. Phys. Lett. 28 094704 |
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Abstract The thrust vectoring ability of a continuous rotating detonation engine is numerically investigated, which is realized via increasing local injection stagnation pressure of half of the simulation domain compared to the other half. Under the homogeneous injection condition, both the flow-field structure and the detonation wave propagation process are analyzed. Due to the same injection condition along the inlet boundary, the outlines of fresh gas zones at different moments are similar to each other. The main flow-field features under thrust vectoring cases are similar to that under the baseline condition. However, due to the heterogeneous injection system, both the height of the fresh gas zone and the pressure value of the fresh gas in the high injection pressure zone are larger than that in the low injection pressure zone. Thus the average pressure in half of the engine is larger than that in the other half and the thrust vectoring adjustment is realized.
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| Keywords:
47.40.Rs
47.70.Fw
47.40.Nm
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Received: 02 April 2011
Published: 30 August 2011
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| PACS: |
47.40.Rs
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(Detonation waves)
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47.70.Fw
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(Chemically reactive flows)
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47.40.Nm
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(Shock wave interactions and shock effects)
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