Impact of Controller Performance on the Process of Guiding an Armour-Piercing Missile onto a Ground-Based Target

Abstract

This work presents an analysis of guiding an anti-tank missile (ATGM) onto a ground-based target. The concept presented here is the feasibility of bypassing obstacles in the path of an ATGM when the obstacle coordinates are known prior to firing the ATGM weapon. The ATGM contemplated here uses a homing algorithm to calculate the stages of the ATGM flight path with the use of polynomial curves (including third-degree polynomial curves). The start and end coordinates of the polynomial curves are determined by the position of the obstacle(s) along the flight path. A method is presented for calculating the factors of subsequent flight path stages, along with a method of equating the ATGM kinematics and dynamics. A comparison is made between the operating efficiency of various configurations of a traditional proportional integral derivative (PID) controller, and at various gain factor values of the PID controller stages. The applied mathematical model of the ATGM are used in a series of numerical simulations for different take-off and in-flight conditions of the projectile. The simulation results are presented in a graphical form.

Control Analysis with Modified LQR Method of Anti-Tank Missile with Vectorization of the Rocket Engine Thrust

“…The general idea of programmed trajectory has been taken from [25]. Determining a programmed (preset) trajectory involves finding a third-degree polynomial function, which joins the initial point and the endpoint of a flight trajectory segment.…”

“…The full spatial flight equations of dynamics for any flying object as a rigid body can be found, among others, in [25,26]. The following equations were used for this study:…”

Modified linear-quadratic regulator used for controlling anti-tank guided missile in vertical plane

“…Calculations shown in Fig. 3 Full dynamic equations of spatial flight of any flying object as a rigid solid body can be found, among others, in the papers (Koruba and Nocoń, 2016a;Nocoń and Stefański, 2016;Baranowski 2013). For the purpose of the analysis of the modified LQR method algorithm, dynamic equations of the ATGM considered herein have been simplified to the vertical plane, making the following assumptions Then, these equations have the following form It is assumed that the deflection angle of the AC and engine nozzle have the same values but opposite directions.…”