Pratama, Tommy (2019) Perancangan Pemanduan Waypoint Rudal Menggunakan Kendali Prediktif Berbasis Model. Other thesis, Institut Teknologi Sepuluh Nopember.
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Abstract
Perancangan autopilot dengan menggunakan pengaturan prediktif disajikan dalam riset ini. Rudal adalah sistem yang non-linier, multi input and multi output (MIMO) dan coupled. Perancangan pengaturan yang diajukan menggunakan discrete model predictive control (DMPC). Model sistem dibutuhkan oleh DMPC untuk memprediksi perilaku sistem yang akan datang yang digunakan untuk menyelesaikan algoritma optimisasi untuk mendapatkan sinyal kendali optimal yang menggerakan keluaran proses. Sebelumnya, model linier didapatkan dengan nonlinear feedback linearization. Tujuan utamanya adalah tercapainya kemampuan rudal menabrak sasarannya dengan mengikuti akselerasi yang diperintahkan oleh sistem pemandu. Pada tugas akhir ini, simulasi pengejaran rudal sasaran dengan mengikuti lintasan menggunakan pemanduan nonlinear guidance logic, dan mengejar sasaran bergerak menggunakan proportional navigation telah ditunjukkan dengan perancangan pengaturan yang diajukan. Simulasi menunjukkan pemanduan waypoint rudal memiliki miss distance rata-rata terkecil rudal terhadap waypoint yaitu 0.0872 m serta RMSE rudal terhadap lintasannya yaitu 0.1497 m dan 0.7263 m untuk bidang horizontal dan vertikal. Sedangkan pengejaran sasaran menunjukkan miss distance terdekat rata-rata antara sasaran dan rudal adalah 0.3232 m.
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The autopilot of missile design using predictive controller is presented in this research paper. The missile is nonlinear, Multi Input and Multi Output (MIMO) and coupled system. The proposed controller design is based on discrete model predictive control (DMPC). A model of system is needed by MPC to predict system's future behaviour and used to solve optimization algorithm to find optimal control action driving the process output. In advance, the linear model is obtained by nonlinear feedback linearization. The main goal is the achievement of the ability of missile colliding its target by following the commanded acceleration by guidance system. In this paper, the missile-target engagement simulation by following the path using nonlinear guidance logic guidance, and pursuiting the moving target using proportional navigation has been illustrated with proposed controller design. The simulation results the smallest average of waypoint guidance miss distance is 0.0872 meter and RMSE of missile-path are 0.1497 meter and 0.7263 meter on horizontal and vertical plan, respectively. While the missile-target engagement shows the average of nearest miss distance of missile and the target is 0.3232 meter.
| Item Type: | Thesis (Other) |
|---|---|
| Additional Information: | RSE 629.831 2 Pra p-1 2019 |
| Uncontrolled Keywords: | nonlinear, MIMO, coupled system, autopilot, nonlinear feedback linearization, discrete model predictive control, nonlinear guidance logic, proportional navigation |
| Subjects: | T Technology > TJ Mechanical engineering and machinery > TJ217.6 Predictive Control U Military Science > U Military Science (General) U Military Science > UG1242 Drone aircraft--Control systems. (unmanned vehicle) U Military Science > U Military Science (General) > UG Military Engineering |
| Divisions: | Faculty of Electrical Technology > Electrical Engineering > 20201-(S1) Undergraduate Thesis |
| Depositing User: | Tommy Pratama |
| Date Deposited: | 16 Mar 2023 03:38 |
| Last Modified: | 16 Mar 2023 03:38 |
| URI: | http://repository.its.ac.id/id/eprint/63706 |
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