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All Journal Angkasa: Jurnal Ilmiah Bidang Teknologi Al-Fath Ideguru: Jurnal Karya Ilmiah Guru Vortex Asketik: Jurnal Agama dan Perubahan Sosial Mestaka: Jurnal Pengabdian Kepada Masyarakat Tasyri' Risalah Iqtisadiyah: Journal of Sharia Economics
Dwi Hartini
Institut Teknologi Dirgantara Adisutjipto
Religion Aerospace Engineering Agriculture, Biological Sciences & Forestry Humanities Computer Science & IT Earth & Planetary Sciences Economics, Econometrics & Finance Education Energy Environmental Science Languange, Linguistic, Communication & Media Law, Crime, Criminology & Criminal Justice Materials Science & Nanotechnology Mechanical Engineering Physics Social Sciences Other

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GPS Signal Performance Testing Based on Material Variations Of Portable On-Demand (POD) And GPS Placement For Aerial Photography Missions Kehi, De Richi; Hartini, Dwi; Mardwianta, Benedictus; Prattiwi, Elisabeth Anna; Santoso, Djarot Wahju
Vortex Vol 6, No 1 (2025)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.28989/vortex.v6i1.3118

Abstract

In aerial photography, the use of camera systems integrated with GPS signals is crucial for determining the position and velocity of an aircraft or drone. The Portable On-Demand (POD) serves as a payload container for equipment such as cameras, and the POD material can influence GPS signal quality. This study aims to evaluate the quality of received GPS signals and to assess the effect of camera distance on GPS performance. Experimental tests were conducted using three POD material types (original, E-glass, and carbon) and two GPS systems (Emlid Reach and Pixhawk). The results indicate that the E-glass POD provides the best performance, achieving signal-to-noise ratio (SNR) values above 45 dB and a PDOP value of 1.7. Additionally, the E-glass POD detected up to 34 satellites at a camera distance of 0 cm. In contrast, the original and carbon PODs exhibited inferior performance, including occurrences of a “No Solution” status. Therefore, the E-glass POD is more reliable in maintaining GPS signal quality and positioning accuracy for aerial photography missions.
Optimization of Turn Around Time Calculation for C05-Check Aircraft Maintenance Using Critical Path Method (CPM) On Boeing 737-900er Aircraft Islami, Alfi Daffa; Rahmawati, Fajar Khanif; Mulyani, Sri; Prakoso, Agung; Hartini, Dwi; Prattiwi, Elisabeth Anna
Vortex Vol 6, No 2 (2025)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.28989/vortex.v6i2.3644

Abstract

Boeing 737-900 ER maintenance in Indonesia emphasizes timely, efficient routines to minimize risks. Using the Critical Path Method (CPM), the analysis calculates the Turn Around Time (TAT) for C05-Check maintenance. The CPM results estimate a TAT of 20.47 days (rounded to 20 days), while the company's data shows 21.73 days (rounded to 22 days), indicating a 2-day difference. This discrepancy highlights potential areas for improving maintenance efficiency. The TAT efficiency for the maintenance process is calculated at 0.057%. Optimizing mechanic workload based on this analysis can enhance turnaround times and ensure aircraft safety and operational scheduling. Accurate TAT predictions are vital for balancing maintenance quality with airline efficiency, making CPM a valuable tool in operational planning and resource allocation. Continued comparison with company data ensures maintenance practices remain precise, reducing unexpected delays and maintaining flight safety standards.
Pelatihan Desain dengan Software CATIA untuk Mengembangkan Kompetensi Teknologi bagi Santri Al Muthi’in Yogyakarta Hartini, Dwi; Junaidin, Buyung; Santoso, Djarot Wahju; Prattiwi, Elisabeth Anna
Mestaka: Jurnal Pengabdian Kepada Masyarakat Vol. 5 No. 1 (2026): Februari 2026
Publisher : Pakis Journal Institute

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.58184/mestaka.v5i1.857

Abstract

The rapid development of digital technology has brought significant changes to both education and industry. One of the technological competencies highly required in modern industries is Computer Aided Design (CAD), which enables product design processes to be carried out efficiently and with high precision. Computer Aided Three-dimensional Interactive Application (CATIA) is a CAD software widely used in various industrial sectors, including manufacturing, automotive, and aerospace. However, opportunities to learn industry-level design software are still limited for many santri. This community service activity aims to enhance technological literacy and basic design skills through CATIA software training for santri of Al Muthi’in. The training was conducted using a hands-on learning approach at the Institut Teknologi Dirgantara Adisutjipto. The training materials covered the introduction to basic CAD concepts, CATIA interface recognition, two-dimensional sketch creation, and simple three-dimensional modeling. The results of the activity indicate an improvement in the santri’s understanding of CAD concepts and their ability to independently create basic three-dimensional designs. This activity is expected to serve as an initial step in strengthening the technological competencies of santri.
Structural Design Optimization of Bellcrank 3 in the N219 Aircraft Flap Flight Control System Using the Finite Element Method Hartini, Dwi; Bachtiar, Muhamad Irfan; Nugroho, Fajar; Anna Prattiwi, Elisabeth Anna; Santoso, Djarot Wahju
Vortex Vol 7, No 1 (2026)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.28989/vortex.v7i1.3819

Abstract

The flap control system is a critical subsystem in aircraft that directly affects aerodynamic performance and flight safety. One of the key mechanical components in this system is the bellcrank, which functions to transmit and redirect loads from the actuator to the flap mechanism. In this study, structural optimization of bellcrank 3 in the flap control system of the N219 aircraft was performed using the Finite Element Method (FEM). Three design configurations were analyzed, namely the base model, optimization model 1 with thickness reduction, and optimization model 2 with the addition of holes in non-critical areas. Structural evaluation was conducted based on mass reduction, displacement, von Mises stress, and margin of safety (MS). The simulation results show that both optimization approaches successfully reduce structural mass compared to the base model. Optimization model 1 achieves the largest mass reduction but results in higher stress levels and lower margin of safety. Optimization model 2 provides a more balanced structural performance, with stress, displacement, and margin of safety values comparable to the base model while maintaining mass reduction. All analyzed configurations exhibit positive margin of safety values, indicating that the structures remain safe under the applied operational loads. Based on the overall structural performance, optimization model 2 is considered the most suitable design for application in the flap control system of the N219 aircraft.
Analisis Komponen Rear Back-Up Fitting Terhadap Damage Tolerance dan Durability Pada Vertical Tail Pesawat Nugroho, Fajar; Hartini, Dwi; Ahmadi, Nurfi; Ilahi, Resa Fadhol
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 Agung Prakoso Anna Prattiwi, Elisabeth Anna Arfandi Achmad Arifqi M, Muh. Nadlah Azhar, Azwari Bachtiar, Muhamad Irfan Bangga Dirgantara Adiputra Benedictus Mardwianta, Benedictus Buyung Junaidin, Buyung Djarot Wahju Santoso E.Nasution, M.Ridlo FAJAR NUGROHO Freddy Kurniawan Habibi Habibi Ilahi, Resa Fadhol Ilhami, Nuzula Imanda, Rafly Indah Lestari, Dwi Islami, Alfi Daffa Istyawan Priyahapsara Kamila, Amalia Kehi, De Richi Mai Fransiska, Helga Mubarak, Pramuda Naufal Noviyanto F, Hendrix Nurfi Ahmadi, Nurfi Pangkey, Calvin Delano Immanuel Pinandita, Lazuardy Rahendra Prasetyo Edi, Prasetyo Prattiwi, Elisabeth Anna Rahmawati, Fajar Khanif Sahuburua, Stevward Norenssio Santo Herlambang Santoso, Prasidananto Nur Satriana, Desmi Seran Luan, Randi Edward Setiawan, Paulus Sri Mulyani Sri Mulyani Suhanto, Suhanto Suyoko Suyoko Taufiqurohman, Taufiqurohman Teguh Wibowo Wibowo, Irfan Yasrin Zabidi, Yasrin Yenni Astuti, Yenni