Peningkatan Akurasi Lintasan Rudal dengan Waktu Optimal Menggunakan Metode Nonlinear Model Predictive Control (NMPC)

Yudhiyanto, Rafi Maulana Putra (2025) Peningkatan Akurasi Lintasan Rudal dengan Waktu Optimal Menggunakan Metode Nonlinear Model Predictive Control (NMPC). Other thesis, Institut Teknologi Sepuluh Nopember.

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Abstract

Rudal merupakan senjata yang dirancang untuk menyerang target dengan kecepatan tinggi. Penelitian ini membatasi kajian pada jenis rudal penjelajah (cruise missile). Pada penelitian ini diimplementasikan metode Nonlinear Model Predictive Control (NMPC) untuk meningkatkan akurasi lintasan rudal tanpa gangguan. Selanjutnya dianalisis hasil simulasi untuk meningkatkan kinerja kontrol dalam mencapai target. Metode NMPC memiliki beberapa keunggulan, antara lain mampu mengoptimalkan sistem tanpa proses linearisasi, dan dapat diintegrasikan secara sistematis dalam proses perancangan kendali. Simulasi dilakukan menggunakan perangkat lunak MATLAB untuk memperoleh bentuk lintasan optimal rudal. Penelitian ini dilakukan dengan berbagai skenario dan memvariasikan kecepatan akhir target (Vf ) dan sudut lintasan terbang rudal. Seluruh simulasi memiliki kondisi akhir sama, sudut lintasan (γtf ), posisi horizontal (xtf ), dan ketinggian (htf ). Berdasarkan simulasi didapatkan bahwa semakin kecil sudut lintasan akhir, waktu tempuh cenderung lebih singkat meskipun kecepatan akhir bervariasi. Hasil ini menunjukkan bahwa pada lintasan menghujam tegak lurus ke target, semakin tinggi kecepatan akhir maka waktu tempuh juga meningkat karena diperlukan waktu akselerasi lebih lama.
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Missiles are weapons designed to attack targets at high speeds. This study limits the study to the type of cruise missile. In this study, the nonlinear model predictive control (NMPC) method was implemented to improve the accuracy of the missile’s trajectory without interference. Furthermore, the simulation results were analyzed to improve control performance in achieving the target. The NMPC method has several advantages, including being able to optimize the system without a linearization process, and can be systematically integrated in the control design process. The simulation was carried out using MATLAB software to obtain the optimal trajectory shape of the missile. The study was conducted with a variety of scenarios and varied the target’s final speed (Vf ) and the angle of the missile’s flight trajectory. All simulations have the same final conditions, track angle (gammatf ), horizontal position (xtf ), and altitude (htf ). Based on the simulation, it was found that the smaller the final trajectory angle, the travel time tends to be shorter even though the final speed varies. This result shows that on a trajectory striking perpendicular to the target, the higher the final speed, the longer the travel time increases due to the longer acceleration time required.

Item Type:	Thesis (Other)
Uncontrolled Keywords:	Peningkatan Akurasi Lintasan, Nonlinear Model Predictive Control, Waktu Optimal, Rudal, Improving Trajectory Accuracy, Nonlinear Model Predictive Control, Optimal Time, Missile
Subjects:	Q Science > QA Mathematics > QA401 Mathematical models.
Divisions:	Faculty of Science and Data Analytics (SCIENTICS) > Mathematics > 44201-(S1) Undergraduate Thesis
Depositing User:	Rafi Maulana Putra Yudhiyanto
Date Deposited:	18 Jul 2025 02:17
Last Modified:	18 Jul 2025 02:17
URI:	http://repository.its.ac.id/id/eprint/119968

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