Comparison of guidance navigation and control design methods for a 3-DOF missile

Date

2024-8

Author

Kocadal, Tuğrul

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

32
views

26
downloads

Cite This

Guidance Navigation and Control (GNC) is the most crucial component of the missiles, which makes them one of the critical military implements; without this system, there is no difference from an uncontrolled object flying in the air and not knowing where to go. For this reason, designing a GNC system for a missile is researched in this work. The primary objective of this thesis is to design different Guidance Navigation Control algorithms for an air-to-air tactical missile. Three distinct GNC algorithms are utilized: Proportional Navigation (PN) with a seeker, Proportional Navigation (PN), and Proportional Navigation with Zero Effort Miss (ZEM). Inertial Navigation System (INS) and a Proportional-Integral-Derivative (PID) controller are applied to a nonlinear missile. Target and missile dynamic model are created and it is simulated in the Simulink. Situations where the missile with integrated GNC systems hit the target were determined in these simulations. The obtained results show the effectiveness of the algorithms and it is aimed to compare and find the algorithm that gives the best results. These findings will guide future research.

Subject Keywords

Interception, GNC, PID, PN, Seeker

URI

https://hdl.handle.net/11511/112232

Collections

Northern Cyprus Campus, Thesis