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| Aero-acoustic Analysis on Fighter Cockpit |
| Received:June 21, 2018 Revised:September 25, 2018 |
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| DOI：10.7643/ issn.1672-9242.2018.09.010 |
| KeyWord:fighter cockpit, aero-acoustic noise, aero-acoustic source, acoustic boundary element |
| Author | Institution |
| WEI Yi |
AVIC Chengdu Aircraft Design & Research Institute, Chengdu , China |
| SI Ren |
AVIC Chengdu Aircraft Design & Research Institute, Chengdu , China |
| JIA Nan-fei |
AVIC Chengdu Aircraft Design & Research Institute, Chengdu , China |
| WU Guo-qing |
AVIC Chengdu Aircraft Design & Research Institute, Chengdu , China |
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| Abstract: |
| Objective To provide approach and data to reduce the aero-acoustic noise in cockpit. Methods The cockpit of a certain aircraft was taken as the object of study. Firstly, based on the CFD method, the fore-body surface transient pressure field was obtained and dealt as the aero-acoustic external excitation. Then, the cockpit interior sound field, sound pressure, and the relationship between structure parameters and noise in cockpit were obtained with the approach of acoustic boundary element. Results The sound field of fighter cockpit cabin showed that the largest acoustic pressure appeared in frequency range lower than 500 Hz, and the acoustic pressure decreased with the increase of frequency. Change of acoustic pressure trended to flat when the frequency was higher than 2500 Hz. The maximum acoustic pressure at the head of pilot in the cockpit was 112 dB. In majority cases, the acoustic pressure at the right ear of pilot in the back cockpit was larger than that at the head of pilot in the front cockpit. Conclusion The results show that, the turbulence caused by refueling pipe fixed on forebody and the fluctuating pressure from inlet are the main noise sources in the cockpit. To reduce the noise in cockpit, apart from optimizing the shape design, adjusting the structural parameters based on analysis of acoustic transfer vector is also an effective choice. |
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