عنوان مقاله [English]
In order to overcome the nonlinear terms in the flight equations of a launch vehicle, an appropriate control strategy has to be designed. In this paper, the fundamentals of designing a simple controller in order to control a typical launch vehicle for tracking the optimum launch vehicle path is presented. The principals of this strategy are based on on-line linearization of the nonlinear equations in each sampling interval during the flight and eventually representing system equations as extended Jacobean equations. It is important to note that equations linearization does not work in some areas and equilibrium points of the system but in each sampling interval is trying the system of nonlinear equations can be transformed into linear equations and then by using the pole placement theory, a good tracking controller proposed for the system. Design and simulation results show good accuracy and proper convergence of the reference signals (speed and pitch angle signals) and eventually, the success of the mission.
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