Hi there.
Well, actually this paper was submitted few months ago. You can check it here or here. Abstract is here:
This paper presents a high‐performance and simple guidance method for a short‐range missile. Missile control systems are designed along the estimated flight envelope of the missile based on coefficient diagram method. The LTI models are obtained by linearizing missile nonlinear model at specific operating points. The governing equations of motion are accurately modeled by taking into account the effect of the mass rate and the center of gravity shift. A novel algebraic approach called Coefficient Diagram Method is used to design normal acceleration and roll angle control systems. Proportional navigation law is considered as the guidance law. One case of engagement scenarios is studied and the missile performance is evaluated. The robustness of the proposed controller is tested againts parameter uncertainties and wind disturbance.
And you can download the portable document here. Should you have discussion, email me.
