Identifying and Analyzing Effects of Different Errors on a Tactical Missiles Flight Computer

Guidance and control laws of  anti-tank missile are recorded in a missile subsystem called flight computer. The flying missile diagnoses the right path using these laws(guidance) and gives essential orders according to them to put the missile in its right path(control). like all real systems, the performance of this subsystem may be perturbed by different reasons leading to a derivative of reasonable functions. In this paper, after identifying15 important ones of these reasons, their effects on missile miss distance which is a measurable and appropriate factor is investigated. In the guidance of this anti-tank missile, pure proportional navigation guidance law is used. The main focus of this paper is on analyzing effect of errors on this law. Finally, the intensity of these reasons on miss distance rate are presented by column diagrams.