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All Journal JATI UNIK : Jurnal Ilmiah Teknik dan Manajemen Industri Angkasa: Jurnal Ilmiah Bidang Teknologi
Nurfi Ahmadi
Institut Teknologi Dirgantara Adisutjipto
Computer Science & IT Engineering Industrial & Manufacturing Engineering

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PITCH PROPELLER QUADCOPTER TYPE X AGAINST THRUST AND VOLTAGE MOTOR TO SUPPORT REGIONAL RESILIENCE Benedictus Mardwianta; Abdul Haris Subarjo; Nurfi Ahmadi; Daniel Setya Budi
Angkasa: Jurnal Ilmiah Bidang Teknologi Vol 14, No 1 (2022): Mei
Publisher : Institut Teknologi Dirgantara Adisutjipto

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (1057.4 KB) | DOI: 10.28989/angkasa.v14i1.1207

Abstract

The small size of the quadcopter and the low inertia of the drone allows the use of a simple flight control system, with the practicality of the Quadcopter it is hoped that it can be used for disaster management so as to increase regional resilience. Quadcopters issued by the company cannot be changed. This research is done by assembling the quadcopter itself and making changes to the propeller pitch to determine the effect of thrust and thrust motor on a quadcopter type x. From the results of research and calculations carried out, the thrust produced with a 50o pitch angle is greater than the 43o pitch angle for each movement, so the greater the pitch angle, the greater the thrust generated by the propeller. . The voltage that enters each motor will be different depending on its movement. So, the greater the voltage that enters the brushless motor, the higher the rotation of the motor so that the thrust generated is also greater.   
Optimalisasi Perawatan Pesawat Terbang dengan CPM, PERT, dan Linear Programming pada Perusahaan MRO Riani Nurdin; Uyuunul Mauidzoh; Nurfi Ahmadi
JATI UNIK : Jurnal Ilmiah Teknik dan Manajemen Industri Vol. 9 No. 2 (2026): April
Publisher : Industrial Engineering, Engineering of Faculty, Universitas Kadiri

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30737/jatiunik.v9i2.6660

Abstract

Maintenance, Repair, and Overhaul (MRO) companies face significant challenges in completing aircraft maintenance projects on time and within budget. The existing gap lies in the optimization of planning methods integration to minimize project duration and cost. This study aims to assess the balance between time and cost in aircraft maintenance projects by showing the benefits of combining CPM, PERT, and Linear Programming. Data were obtained from the A02-CHECK activity at a national MRO company. CPM and PERT were used to find the critical path and estimate project duration, while LP was used to optimize time and cost on that path. The project duration decreased from 6,199 to 4,547 minutes, with the critical path in activities A-C-E-G-H and an 84.13% success probability. Using LP, the duration dropped further to 4,090 minutes at a total cost of $202. It can be concluded that the integration of these three methods is effective in accelerating projects without exceeding the budget. The main contribution of this research is the development of an integrated approach to aircraft maintenance project planning which can capable of reducing the risk of delays and budget overruns. in addition, it also provides practical solutions for MRO companies
Analisis Komponen Rear Back-Up Fitting Terhadap Damage Tolerance dan Durability Pada Vertical Tail Pesawat Fajar Nugroho; Dwi Hartini; Nurfi Ahmadi; Resa Fadhol Ilahi
Angkasa: Jurnal Ilmiah Bidang Teknologi Vol 18, No 1 (2026): Februari
Publisher : Institut Teknologi Dirgantara Adisutjipto

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.28989/angkasa.v18i1.3403

Abstract

Aircraft structures are subjected to repetitive cyclic loading that may induce fatigue damage and crack propagation, potentially compromising structural integrity and flight safety. This study examines the damage tolerance and durability of the rear back-up fitting, a critical structural component of the aircraft vertical tail. The analysis combines the Finite Element Method (FEM) to identify stress concentration regions with crack propagation simulations using D-CRACK software under representative operational loading spectra. The results indicate that the most critical locations occur at the fastener holes of PSE V03-A and PSE V03-B. PSE V03-A reaches a critical crack length of 287.646 mm after 328,801 flight cycles, while PSE V03-B reaches a critical crack length of 283.427 mm after 756,190 flight cycles. The longer fatigue life observed in PSE V03-B is primarily attributed to the presence of a stiffener, which effectively reduces stress concentration and slows crack growth rates. In accordance with FAR 25.571, the first inspection is recommended at 12,294 flight cycles for PSE V03-A and 15,000 flight cycles for PSE V03-B, followed by periodic inspections every 2,000 cycles. These results provide a quantitative basis for determining inspection intervals and support the development of a damage-tolerance-based maintenance manual to enhance structural reliability, operational safety, and long-term aircraft durability
Co-Authors Abdul Haris Subarjo Benedictus Mardwianta, Benedictus Daniel Setya Budi Dwi Hartini Fajar Nugroho Nurdin, Riani Resa Fadhol Ilahi Uyuunul Mauidzoh