An Investigation into the Performance of a Homing Guided Missile with Different Aerodynamic Configurations | ||||
| International Conference on Aerospace Sciences and Aviation Technology | ||||
| Article 67, Volume 10, 10th International Conference On Aerospace Sciences & Aviation Technology, May 2003, Page 975-984 PDF (1.99 MB) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/asat.2013.24719 | ||||
 View on SCiNiTO | ||||
| Author | ||||
| G. A. EI-Sheikh | ||||
| Abstract | ||||
| The response of a guided missile as a whole depends upon the control system characteristics and the missile aerodynamic configuration. Thus, this paper tries to investigate the performance of a homing guided missile utilizing the proportional navigation guidance method with different missile aerodynamic configurations. These configurations include the variable incidence wing, the canard control, and the tail control configurations. The results obtained showed that the missile with only rate feedback and variable incidence wing configuration responds quicker than other configurations. In addition, the oscillation frequency of the response is very close to that of the missile alone. While using the rate and acceleration feedbacks together yields that the missile with tail control configuration responds faster than other configurations. In addition, the oscillation frequency of the response is higher than that of the missile alone, but with different navigation ratio corresponding to each configuration. | ||||
| Keywords | ||||
| Missile Guidance Systems; Guidance Methods; Automatic Control; and Flight Mechanics | ||||
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