Integrated guidance and control law with impact angle constraint

Abstract

The concept of the IGC(Integrated Guidance and Control) has been introduced to overcome the performance limit of the SGC(Separated Guidance and Control) loop. A new type of IGC with impact angle constraint has been proposed in this paper. Angle of attack, pitch angle rate, pitch angle and line of sight angle are considered as state variables. A controllability analysis and equilibrium point analysis has been carried out to investigate the control characteristic of proposed IGC. The LQR(Linear Quadratic Regulator) has been adopted for the control law and detailed explanations about the adoption has been provided. The performance comparison between the IGC and the SGC has been carried out. The result of numerical simulations show that the IGC guarantees better guidance performance than the SGC when the agile maneuver is needed for specific guidance geometry. © 2011 ICROS.