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All Journal Teknika STTKD: : Jurnal Teknik, Elektronik, Engine
Edi Sofyan
Sekolah Tinggi Teknologi Kedirgantaraan
Electrical & Electronics Engineering Energy Industrial & Manufacturing Engineering Materials Science & Nanotechnology Mechanical Engineering

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ANALISIS KESTABILAN STATIK DAN DINAMIK PADA PESAWAT LSU-05 NG (LAPAN SURVEILLANCE UAV 05 NEW GENERATION) DENGAN MENGGUNAKAN PERANGKAT LUNAK XFLR5 Zera Angeline Rerung; Edi Sofyan; Ferry Setiawan
Teknika STTKD: : Jurnal Teknik, Elektronik, Engine Vol 6 No 2 (2020): Teknika STTKD
Publisher : Sekolah Tinggi Teknologi Kedirgantaraan

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (854.766 KB) | DOI: 10.56521/teknika.v6i2.215

Abstract

Aviation in Indonesia has progressed from time to time, both in terms of existing technology and infrastructure. One of them is the development of unmanned aircraft or commonly called unmanned aircraft which is commonly abbreviated as UAV (Unmanned Aerial Vehicle). The LSU-05NG aircraft is an unmanned aircraft designed by the LAPAN Aviation Technology Center (National Institute of Aviation and Space). This aircraft is designed to meet surveillance needs or is intended for observation of a very wide area of coverage only by installing sensor devices such as cameras and FLIR (Forward Looking Infra Red). To launch this surveillance mission, the LSU05NG aircraft must have stability. Due to the light weight and also small aircraft, the stability of this aircraft will be more easily disrupted, so there is a need for stability for the LSU-05NG aircraft to carry out its mission properly. An aircraft is said to be statically stable if the lateral dimension has a value ????ɩ???? < 0, the longitudinal dimension has a value ???????????? < 0, and on the directional dimension the value ???????????? > 0. By modeling the Lsu05 new generation aircraft and analyzing the stability of the aircraft in XFLR5 software so as to obtain the roots of aerodynamic characteristics. Based on the results of analyzes conducted on XFLR5 software, the LSU-05 new generation aircraft is statically stable and changes in speed cannot affect its stability.
SISTEM KENDALI ADAPTIF NEURO-FUZZY PID PADA KAPAL KATAMARAN TANPA AWAK Erwhin Irmawan; Tri Kuntoro Priyambodo; Edi Sofyan
Teknika STTKD: : Jurnal Teknik, Elektronik, Engine Vol 3 No 2 (2016): Teknika STTKD: Jurnal Teknik, Elektronik, Engine
Publisher : Sekolah Tinggi Teknologi Kedirgantaraan

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (412.547 KB)

Abstract

Kendali otomatis dibutuhkan oleh kapal katamaran tanpa awak dalam menavigasi menuju arah tertentu dan dapat menangani gangguan serta perubahan kondisi dengan efektif dan optimal. Kendali PID cocok untuk pengendalian kapal, namun mempunyai kelemahan dalam pencarian gain PID optimal untuk setiap kondisi. Fuzzy mampu menangani penjadawalan gain PID untuk setiap kondisi dan neural network mampu mengoptimasi desain fuzzy, sehinggadilakukan penggabungan menjadi kendali adaptif neuro fuzzy PID (N-F PID). N-F PID merupakan kendali PID dengan penjadawalan gain PID (Kp, Ki dan Kd) yang dinamis berdasarkan besarnya nilai error dan delta error oleh neuro fuzzy. Neuro fuzzy yang digunakan adalah adaptif neuro fuzzy inference system (ANFIS). ANFIS mampu melakukan pembelajaran dengan training data baru untuk memperbaiki performa. Training data baru didapatkan dari proses tuning dengan mengalikan output masing-masing fuzzy yang belum terlatih dengan konstanta tertentu hingga didapatkan settling time cepat dan persentase overshoot maksimum kecil.Simulasi N-F PID dengan Matlab dan ekperimen kapal katamaran menunjukkan N-F PID mempunyai performa yang lebih baik dari pada kendali fuzzy PID dan kendali PID, dilihat dari settling time dan persentase overshoot maksimum. N-F PID mempunyai tingkat presisi pengendalian yang lebih rendah daripada kendali fuzzy PID dan PID berdasarkan data eksperimen.
ANALISIS DAN DESAIN WING UAV VTOL MENGGUNAKAN FINITE ELEMENT ANALYSIS Andika wijaya; Edi Sofyan; Ferry setiawan; Muhammad Kevin Adam
Teknika STTKD: : Jurnal Teknik, Elektronik, Engine Vol 9 No 1 (2023): TEKNIKA STTKD: JURNAL TEKNIK, ELEKTRONIK, ENGINE
Publisher : Sekolah Tinggi Teknologi Kedirgantaraan

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.56521/teknika.v9i1.872

Abstract

Unmanned Aircraft (PTTA) or Unmanned Aerial Vehicle (UAV) is an aircraft that flies without a pilot and is controlled automatically. UAVs have a wide range of applications, including remote sensing, communication links, and natural disaster monitoring. One type of UAV being developed is LSU 05, using a composite of carbon fiber (CFRP) and glass fiber (GFRP) for its wing structure. This study aims to create a 3D model of the UAV VTOL wing, analyze the effect of material variations on the strength of the wing structure, and find the optimal wing design using the finite element analysis method. This study uses the SolidWorks 2021 software with maneuver conditions loading. The results of the analysis show that carbon fiber provides higher strength than fiberglass. In a fiberglass wing, the maximum stress is 229 MPa, while in a carbon fiber wing it is 197 MPa. The biggest displacement occurred in the fiberglass wing, which was 2.661 mm. The safety factor of the carbon fiber wing is 2.7, while that of the fiberglass is 1.9. This research provides an in-depth understanding of the behavior of VTOL UAV wing structures and contributes to the development of better wing designs. The optimized design can increase the performance, efficiency and reliability of VTOL UAV.
Co-Authors Andika Wijaya Ferry Setiawan Muhammad Kevin Adam Tri Kuntoro Priyambodo Zera Angeline Rerung