Prasetyo, Muhamad Rafif (2018) Perancangan Kendali Optimal LQT untuk Pengendalian dan Pemanduan pada Rudal. Undergraduate thesis, Institut Teknologi Sepuluh Nopember.
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Abstract
Peluru kendali (rudal) perlu dikendalikan dan dibuat untuk selalu mengikuti komando yang diberikan pemandu agar rudal dapat bergerak menuju sasarannya. Pengedalian rudal menjadi lebih rumit dikarenakan rudal memiliki persamaan dinamika yang non-linear dan coupled. Linear Quadratic Tracking (LQT) merupakan salah satu metode kendali optimal dengan tujuan membuat keluaran sistem mengikuti referensi yang diberikan sedekat mungkin dengan memperhatikan suatu indeks performansi. Sistem yang ingin dikendalikan oleh LQT harus sistem yang linier, namun rudal memiliki karakteristik yang non-linear, sehingga diperlukan linearisasi agar rudal dapat dikendalikan dengan LQT. Dalam tugas akhir ini, dirancang sebuah autopilot rudal yang terdiri dari non-linear state feedback decoupler dan pengendali LQT. Pemandu yang digunakan adalah Pemandu Pengejar (Pursuit Guidance). Simulasi pengejaran rudal menuju sasaran dirancang dengan menggunakan dua jenis sasaran, yaitu sasaran statis dan sasaran dinamis. Hasil simulasi menunjukkan dengan sasaran statis, rata-rata jarak terdekat antara rudal – sasaran sebesar 0.45 meter. Sedangkan pada sasaran dinamis, rata-rata jarak terdekat antara rudal – sasaran sebesar 2.562 meter.
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Missile needs to be controlled and made to always follow the commanded guidance in order to make it engage the target. Controlling the missile has become more complex because missile has a non-linear and coupled dynamic equation. Linear Quadratic Tracking (LQT) is one method of optimal control theory where its objective is to make the output of a system tracks its reference as close as possible while minimize or maximize a performance index. The system which wants to be controlled with LQT must be a linear system, but the missile itself has a non-linear system, so the missile needs to be linearized in order to control it using LQT. In this final project, a missile’s autopilot is designed which consists of non-linear state feedback decoupler and LQT controller. Pursuit Guidance is used for the guidance law. A missile – target engagement simulation is made and done using 2 kinds of targets; static target and dynamic target. From the simulation result’s by using static target, the mean of the closest distance between the missile and the target is 0.45 meters and from the simulation result’s by using dynamic target, the mean of the closest distance between the missile and the target is 2.562 meters.
| Item Type: | Thesis (Undergraduate) |
|---|---|
| Additional Information: | RSE 629.832 Pra p-1 3100018074780 |
| Uncontrolled Keywords: | Peluru Kendali, Non-Linear State Feedback Decoupler, Linear Quadratic Tracking (LQT), Pursuit Guidance |
| Subjects: | T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL521.3 Automatic Control U Military Science > U Military Science (General) |
| Divisions: | Faculty of Industrial Technology > Electrical Engineering > 20201-(S1) Undergraduate Thesis |
| Depositing User: | Muhamad Rafif Prasetyo |
| Date Deposited: | 27 Mar 2018 03:14 |
| Last Modified: | 24 Jul 2020 06:28 |
| URI: | http://repository.its.ac.id/id/eprint/50101 |
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