SIMULATING AND MAXIMIZING THE EFFECT OF JAMMING ON PROPORTIONAL NAVIGATION HOMING GUIDANCE | ||||
| International Conference on Aerospace Sciences and Aviation Technology | ||||
| Article 78, Volume 8, ASAT Conference, 4-6 May 1999, May 1999, Page 1-10 PDF (1.94 MB) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/asat.1999.25164 | ||||
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| Author | ||||
| ALADIN H. ASSISI | ||||
| PhD. , Electronic Warfare Engineering Department; Military Technical College. | ||||
| Abstract | ||||
| In this paper the kinematics of a proportional navigation homing guidance trajectory have been simulated, first without any initial heading errors or target maneuvers and then with certain inserted angular errors to simulate a jamming effect that be maximized. We demonstrate in the same paper that the inserted angular error has to be time varying; such that additional false guidance commands are continuously generated which deviate the missile from its correct trajectory. Different methods can be adopted to induce such angular errors which are out of the scope of this paper. The simulation results have been congruent with the theoretical discussion: Zero miss-distance has resulted without jamming. With constant inserted angle error the guidance system has succeeded to recover with a negligible miss-distance. Different laws of variation have been proposed for the inserted angular error and their parameters have been optimized for maximum possible miss-distance. Miss-distances in excess of 4 kilometers have been achieved. | ||||
| Keywords | ||||
| Proportional navigation; final miss-distance; impact point; target kill probability; self-protection jammer; jamming-to-signal ratio; missile seeker; speed gate stealing | ||||
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