Space subsystems design: (navigation, control, structure and…)
Reza Sheikhbahaei; Saeed Khankalantary
Volume 14, Issue 4 , December 2021, , Pages 51-59
Abstract
In this study, on the basis of proportional navigation strategy, design of explicit optimal guidance law for missiles tracking maneuvering targets in three-dimensional space using model predictive control is addressed. The model predictive control employs a model to predict the future process behavior ...
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In this study, on the basis of proportional navigation strategy, design of explicit optimal guidance law for missiles tracking maneuvering targets in three-dimensional space using model predictive control is addressed. The model predictive control employs a model to predict the future process behavior and calculates an optimal control input at each time step through the optimization of an objective function. Generalized model predictive control approach, employed in this study, solves the optimization problem offline to obtain the closed form optimal control law. In this paper, firstly, the equations describing the missile-target relative motion kinematics are formulated. Then, the optimal control law, as an explicit function of the state vector is obtained. The evaluation of the proposed scheme is studied by the comparison of the simulation results with the augmented proportional navigation system. Simulation studies, in three different scenarios, demonstrates appropriate performance for the proposed guidance system specially against maneuvering targets.
Space subsystems design: (navigation, control, structure and…)
S. Hamid Jalali Naini; Ali Arabian Arani
Volume 13, Issue 4 , December 2020, , Pages 1-13
Abstract
In this paper, a modified proportional navigation (PN) with weighted combination of linear acceleration and line-of-sight (LOS) acceleration feedback is suggested. For this purpose, a comprehensive miss distance analysis is carried out for PN with linear acceletation feedback and PN with LOS acceleration ...
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In this paper, a modified proportional navigation (PN) with weighted combination of linear acceleration and line-of-sight (LOS) acceleration feedback is suggested. For this purpose, a comprehensive miss distance analysis is carried out for PN with linear acceletation feedback and PN with LOS acceleration feedback using a fifth-order binomial guidance and control system. The miss distance (MD) due to initial heading error, target acceleration, and seeker noise is separately analysed. As a special case, a modified PN with acceleration feedback using variable gains is suggested based on MD analysis for infra red seekers. The comparison of PN strategies is carried out using an equivalent effective navigation ratio, defined by using LOS rate profile solution. In addition, the first-order optimal guidance law is converted into PN with PD block with variable gains.
Space subsystems design: (navigation, control, structure and…)
S. Hamid Jalali-Naini; Ali Arabian Arani
Volume 13, Issue 2 , June 2020, , Pages 1-12
Abstract
In the present work, the performance of True Proportional Navigation (TPN) with different profiles for effective navigation ratio in terms of the relative velocity angle with respect to line-of-sight is investigated due to initial heading errors and target maneuvers. Since an appropriate profile of effective ...
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In the present work, the performance of True Proportional Navigation (TPN) with different profiles for effective navigation ratio in terms of the relative velocity angle with respect to line-of-sight is investigated due to initial heading errors and target maneuvers. Since an appropriate profile of effective navigation ratio for heading error is almost in contrary with the appropriate profile for maneuvering targets, a variable effective navigation ratio in terms of the relative velocity angle and its rate is introduced. In this way, the miss distance (MD) for the first two peaks of the normalized MD graph versus normalized final time, for example under an effective navigation ratio of 4, is reduced together. The analysis is carried out using normalized equations in polar coordinates for perfect and binomial fifth-order control systems without acceleration limit. Due to practical consideration, the effective navigation ratio is tuned and limited between 3 and 5.
