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Missile initial engagement determination and terminal phase guidance
Fariz A.a, Sasongko R.A.a
a Faculty of Mechanical and Aerospace Engineering, Institut Teknologi Bandung, Bandung, Indonesia
[vc_row][vc_column][vc_row_inner][vc_column_inner][vc_separator css=”.vc_custom_1624529070653{padding-top: 30px !important;padding-bottom: 30px !important;}”][/vc_column_inner][/vc_row_inner][vc_row_inner layout=”boxed”][vc_column_inner width=”3/4″ css=”.vc_custom_1624695412187{border-right-width: 1px !important;border-right-color: #dddddd !important;border-right-style: solid !important;border-radius: 1px !important;}”][vc_empty_space][megatron_heading title=”Abstract” size=”size-sm” text_align=”text-left”][vc_column_text]Copyright © 2019. The Authors. Published by Elsevier Ltd. All rights reserved.This paper discusses an approach for determining the initial engagement point and steering missile during its terminal phase such that it can hit a ground target from predefined direction. The guidance algorithm generates maneuver reference, in terms of normal acceleration, that is fed to the flight control system. The algorithm is based on Proportional Navigation (PN) approach, with scheduled navigation gains. The navigation gains are scheduled as a function of Line of Sight (LOS) and desired flight path angles at engagement stage, hence it may be exploited for determining the initial engagement point. For a desired navigation gain value, the LOS is also related to the maximum value of normal acceleration reference, hence it can be used for limiting the maneuver that must be executed by the missile. The guidance system then is integrated with the flight maneuver controller. The flight control system regulates the normal acceleration, so that the missile will follow the desired trajectory and hit the target. The algorithm then is implemented and tested on a hypothetical cruise missile model. The simulation results show that the guidance approach can generate good maneuver reference, and that the performance of the normal acceleration tracking controller will significantly affects the accuracy of the system.[/vc_column_text][vc_empty_space][vc_separator css=”.vc_custom_1624528584150{padding-top: 25px !important;padding-bottom: 25px !important;}”][vc_empty_space][megatron_heading title=”Author keywords” size=”size-sm” text_align=”text-left”][vc_column_text]Acceleration tracking,Desired trajectories,Flight maneuvers,Flight path angle,Guidance algorithm,Impact angles,Proportional navigation,Terminal-phase guidances[/vc_column_text][vc_empty_space][vc_separator css=”.vc_custom_1624528584150{padding-top: 25px !important;padding-bottom: 25px !important;}”][vc_empty_space][megatron_heading title=”Indexed keywords” size=”size-sm” text_align=”text-left”][vc_column_text]Impact angle,Missile guidance,Terminal phase[/vc_column_text][vc_empty_space][vc_separator css=”.vc_custom_1624528584150{padding-top: 25px !important;padding-bottom: 25px !important;}”][vc_empty_space][megatron_heading title=”Funding details” size=”size-sm” text_align=”text-left”][vc_column_text][/vc_column_text][vc_empty_space][vc_separator css=”.vc_custom_1624528584150{padding-top: 25px !important;padding-bottom: 25px !important;}”][vc_empty_space][megatron_heading title=”DOI” size=”size-sm” text_align=”text-left”][vc_column_text]https://doi.org/10.1016/j.ifacol.2019.11.063[/vc_column_text][/vc_column_inner][vc_column_inner width=”1/4″][vc_column_text]Widget Plumx[/vc_column_text][/vc_column_inner][/vc_row_inner][/vc_column][/vc_row][vc_row][vc_column][vc_separator css=”.vc_custom_1624528584150{padding-top: 25px !important;padding-bottom: 25px !important;}”][/vc_column][/vc_row]