عنوان مقاله [English]
Designing automatic come back system has long been of interest to researchers and scientists worldwide because of the strategic importance of this technology. But, there are not significant resources because most of such activities and studies are often in isolated and semi-military places. A trajectory with minimum acceleration rate, the energy loss, and high precision with high reliability, the selection and implementation guidance law is required which is obtained by evaluating the mission system, support system, and also challenged environmental conditions. Hereof, guidance laws with suitable trajectory can play important and effective roles as a software in increasing reliability of system and fulfilling the objectives of the control system designer. Several strategies have been proposed to guide the direction of flight systems, which each of them has its strengths and weaknesses. One of the strengths of guidance solutions, is the satisfaction of controlling the vector of the final speed for which Kappa guidance law is one of them. Kappa guidance law is an analytical solution with minimum energy performance index based on the calculation of the acceleration required to satisfy the boundary conditions of the aerial vehicles. In this paper, generalizing kappa guidance law in order to design a come-back trajectory with minimum landing velocity constraint for an aerial passive vehicles has been derived. Designed trajectory has been improved against ``kappa guidance law with constant navigation coefficients''. This means that ``acceleration rate'' and ``final velocity in vertical plane'' are reduced to minimum. Evaluation and comparison of the results, through the case studies are carried out, confirms recovery of acceleration time history of payload and final velocity vector controlin order to increase reliability of landing sub-system for come-back aerial passive vehicles.