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Modelling and Simulation of Asymmetric Missile Releasing during Flight Case
Rompas R.R.a, Asalani Y.K.a, Sasongko R.A.a
a 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]© 2019 IEEE.Air superiority is a crucial thing when it comes to modern defense and conventional war because it enables one side to optimize its military operation and inhibit the enemy’s operation at the same time, whether it’s on the ground or at the sea. This enhance the development of multirole fighters which one of its properties is high maneuverability. On the other hand, this aerodynamically unstable design requires advanced flight control system which makes the development of flight control system a highly important matter. In this paper, the model of a fighter aircraft flight dynamics and the model of disturbance in terms of forces and moments caused by the missile launching are built and simulated on the open-loop system initially. From open-loop simulation, the aircraft becomes unstable after releasing right-wing missile. Furthermore, same processes are operated on two different closed-loop systems to obtain proper controller that can compensate the effect of missile releasing. Both closed-loop system are the aircraft equipped with Stability Augmentation System and aircraft equipped with Stability Augmentation System, Basic Autopilot System, and Flight Path Control System. The results show that these closed-loop systems successfully improve the response of the aircraft after launching a missile since the aircraft flight trajectory is still maintained in desired value.[/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]Aircraft flight,Autopilot systems,Missile launching,Modelling and simulations,Multirole fighter,Open loop systems,Open-loop simulations,Stability augmentation systems[/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]dynamic response,fighter aircraft,flight control system,flight dynamics,missile,simulation[/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/10.1109/ACDT47198.2019.9072842[/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]