CONTROL OVER BLAST WAVE AT EXIT POINT OF SUPER-SONIC PROJECTILE | ||||
| International Conference on Aerospace Sciences and Aviation Technology | ||||
| Article 26, Volume 9, ASAT Conference, 8-10 May 2001, May 2001, Page 1-11 PDF (1.28 MB) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/asat.2019.24791 | ||||
 View on SCiNiTO | ||||
| Authors | ||||
| Abu-Elkhair M. S.; Sherif H. A.; Said S. M. | ||||
| Egyptian Armed Forces. | ||||
| Abstract | ||||
| Sound field produced from explosion always attracts the scientists to deal with. Regarding to the traveling projectiles, sound field is interpreted due to two main parameters, the first parameter is owing to the effect of pressure wave and pressure difference behind the projectile at exit moment, while the second parameter is related to the sound produced by the velocity of the flying projectile. In the present work; due to difficulty in controlling the component of sound generated from hypersonic flying objects, sound wave parameter have been excluded, while the effect of pressure wave is taken into consideration. The arrangement shown hereinafter has been tested thoroughly, and the results were recorded at different velocities and distances. Results have shown that this method of control has a great effect on reducing the sound produced due to firing, and the model has been verified as tested on the Automatic Rifle 7.62x39 mm. This work aims to verify experimentally the performance of the modified silencer. | ||||
| Keywords | ||||
| Blast-Waves; Internal Ballistics; weapons; Barrel Muzzle; Discharging of gases; Silencer; Sound wave and Pressure wave | ||||
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