Classical Autopilot Design for a Semiactive Homing Guided Missile | ||||
| International Conference on Aerospace Sciences and Aviation Technology | ||||
| Article 71, Volume 10, 10th International Conference On Aerospace Sciences & Aviation Technology, May 2003, Page 1031-1041 PDF (2.17 MB) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/asat.2013.24726 | ||||
 View on SCiNiTO | ||||
| Authors | ||||
| A. M. Kamel; G. A. El-Sheikh; I. Abd-ElDayem | ||||
| Abstract | ||||
| The control system of a guided missile is composed of the missile itself, equipped with an automatic pilot, and a guidance system, which is either on the missile or outside of it. The guidance system measures the missiles coordinates and out of them in addition to the target coordinates creates the control signals for deflecting the fins in such a direction that should result in the minimum deflection of the missile from the required trajectory. The main requirement imposed on the missile autopilot is the transfer of the control signals into mechanical rotation of the control fins. During missile flight, it is necessary to keep the missile's dynamic properties approximately fixed or slowly varying. Thus, any undue changes in the missile's maneuverability can be avoided using feedbacks from the angular speed and from the missile's normal acceleration to stabilize and to improve the dynamic properties of the missile and of the whole control circuit. Therefore, this paper is devoted to investigate the performance of a homing guided missile using the available compensators about that system. Then, a trial is followed to design another compensator or correction networks for enhancing the missile system performance. The performance of the guided missile is measured through the minimum miss distance and the speed of response. | ||||
| Keywords | ||||
| Missile Guidance and Classical Control | ||||
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