Kendali Rudal Yang Dipengaruhi Gangguan Dengan Menggunakan Metode Nonlinear Model Predictive Model (NMPC)

Indriyani, Shinta Aprillia Dwi (2024) Kendali Rudal Yang Dipengaruhi Gangguan Dengan Menggunakan Metode Nonlinear Model Predictive Model (NMPC). Other thesis, Institut Teknologi Sepuluh Nopember.

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Abstract

Rudal atau missile adalah salah satu komponen pertahanan dan keamanan suatu negara. Secara umum, rudal merupakan sistem senjata modern berteknologi tinggi yang memiliki kemampuan self-propelled yang menunjukkan bahwa suatu rudal digerakkan dan dipandu menuju sasarannya oleh sistem yang ada pada rudal itu. Dalam rudal, terdapat fungsi kendali yang berfungsi untuk memastikan stabilitas rudal dan menjalankan sinyal panduan yang diterima dari sumber eksternal atau internal. Sistem inilah yang menentukan keberhasilan suatu rudal dalam mencapai targetnya. Pada penelitian ini, rudal dihadapkan pada gangguan sehingga diperlukan suatu kendali agar rudal tetap dapat mencapai target dengan optimal. Gangguan diasumsikan bersifat deterministik dan berupa fungsi piecewise constant atau fungsi tangga, yakni fungsi yang memiliki nilai konstan pada beberapa interval waktu tertentu. Model matematika rudal yang digunakan berupa model nonlinear dan metode kendali yang digunakan adalah Nonlinear Model Predictive Control (NMPC). Langkah pertama pada penelitian ini yaitu pembentukan model matematika nonlinear rudal dengan gangguan untuk selanjutnya dilakukan diskritisasi menggunakan metode beda hingga. Selanjutnya, dilakukan desain kendali dengan metode NMPC. Dalam proses pembuatan kendali, dilakukan pembuatan fungsi objektif beserta kendala yang dilanjutkan dengan proses optimasi sesuai dengan jumlah prediksi horizon. Proses simulasi dilakukan dengan bantuan software MATLAB. Simulasi dilakukan dilakukan pada dua titik referensi, yakni (x,h) = (10000,0) dan (x,h) = (11000,0). Pada titik referensi (x,h) = (10000,0) dilakukan sebanyak empat skema simulasi dan untuk titik referensi (x,h) = (11000,0) dilakukan sebanyak tiga skema simulasi. Dari hasil simulasi diperoleh bahwa pergerakan rudal yang dipengaruhi gangguan cenderung kurang stabil apabila dibandingkan dengan pergerakan rudal tanpa adanya pengaruh gangguan. Selain itu, hasil simulasi juga menunjukkan bahwa kendali rudal menggunakan metode NMPC tidak selalu mampu untuk mengompensasi semua gangguan yang ada. Terdapat kondisi di mana rudal tidak dapat sampai pada target karena adanya pengaruh gangguan pada sistem.
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Missiles are one component of a country’s defense and security. In general, a missile is a modern, high-tech weapon system that has self-propelled capabilities, which means that a missile is driven and guided towards its target by the system on the missile. In missiles, there are control functions that serve to ensure the stability of the missile
and carry out guidance signals received from external or internal sources. This system determines the success of a missile in reaching its target. In this research, the missile is faced with interference so that control is needed so that the missile can still reach the target optimally. The disturbance is assumed to be deterministic and a piecewise constant function or a step function, namely a function that has a constant value at certain time intervals. The missile mathematical model used is a nonlinear model and the control method used is Nonlinear Model Predictive Control (NMPC). The first step in this research is the formation of a nonlinear missile mathematical model with disturbances and then discretization using the finite difference method. Next, control design was carried out using the NMPC method. In the control creation process, an objective function and constraints are created, followed by an optimization process according to the number of predicted horizons. The simulation process was carried out with the help of MATLAB software. The simulation was carried out at two reference points, namely (x,h) = (10000,0) and (x,h) = (11000,0). At the reference point (x,h) = (10000,0), four simulation schemes were performed and for the reference point (x,h) = (11000,0), three simulation schemes were performed. From the simulation results, it was found that the movement of the missile affected by disturbances tends to be less stable when compared to the movement of the missile without the influence of disturbances. In addition, the simulation results also show that missile control using the NMPC method is not always able to compensate for all existing disturbances. There are conditions where the missile cannot reach the target due to the influence of disturbances on the system.

Item Type:	Thesis (Other)
Uncontrolled Keywords:	Gangguan, Nonlinear Model Predictive Control (NMPC), Piecewise Constant, Rudal Disturbance, Missile, Nonlinear Model Predictive Control (NMPC), Piecewise Constant
Subjects:	Q Science > QA Mathematics > QA401 Mathematical models. U Military Science > U Military Science (General)
Divisions:	Faculty of Science and Data Analytics (SCIENTICS) > Mathematics > 44201-(S1) Undergraduate Thesis
Depositing User:	Shinta Aprillia Dwi Indriyani
Date Deposited:	06 Aug 2024 04:17
Last Modified:	06 Aug 2024 04:17
URI:	http://repository.its.ac.id/id/eprint/111374

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