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Closed-form approximate solution of the nonlinear equations of motion of an aerial homing engagement under the realistic true proportional navigation guidance law is derived using the Adomian decomposition method. ADM provides an analytical approximate series solution to nonlinear differential equations, requiring no linearization or direct integration of the nonlinear terms. A novel attempt has been...
RF seekers provide the relative kinematics between the target and the pursuer in terms of LOS rates which are used for homing guidance computation. The measurement noise of the seeker is non-stationary and correlated due to eclipsing, Glint, RCS fluctuation, Radome distortion, angular noise, Gyro drift, etc. Further, the track loop dynamics originated from the receiver, signal processing and the stabilization...
Stability analysis of a realistic linearized PN homing loop has been presented in this paper with an objective to compute the allowable time constant of the guidance estimator. Bounds of estimator time constant over the flight time have been computed for a PN guidance loop comprising of a first order seeker, third order autopilot and airframe. Incorporating a third-order autopilot and airframe, the...
The traditional three-loop autopilot as presented by Zarchan suffers from coupling in pitch, yaws, roll channel as well as degraded performance due to huge aerodynamic uncertainties. Sliding mode control is applied to design autopilot for skid-to-turn missile (STT) missile systems to overcome the above stated difficulties. The design has two steps. The first step involves feedback linearization and...
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