Simulation and performance investigation of a typical guidance system with suitable modeling of the guidance system elements and its sensitivity with respect to aerodynamic coefficients

The Guidance commands are mostly generated by determining the line of sight (LOS) angle. Among the existed guidance laws, proportional navigation (PN) is the most widely used algorithm. In this way, the differentiation of LOS angle is needed. Then the LOS rate are usually found by numerical differentiation of the LOS angle. The LOS rate can be directly measured by an embedded internal seeker which it would be a differential free technique. Nowadays, in practical, guidance algorithms equipped with a seeker have been interested. Such a guidance loop includes some subsystems like vehicle dynamics, the type of flight path and also navigation sensors which each subsystems may have some parameters like aerodynamic coefficients. Therefore the guidance system performance would be affected by changing in these parameters. In this paper, in a typical vehicle equipped with a seeker, the guidance system efficiency are numerically investigated in terms of the aerodynamic coefficients change.