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All Journal IAES International Journal of Artificial Intelligence (IJ-AI) Jurnal Patriot Jurnal Arsitektur Journal of Regional Public Administration Indonesian Journal of Aerospace
Hidayat, Kurnia
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PERAN USAHA KESEHATAN SEKOLAH (UKS) SEBAGAI PROSES PRILAKU HIDUP BERSIH DAN SEHAT PESERTA DIDIK Hidayat, Kurnia; -, Argantos
Jurnal Patriot Vol 2 No 2 (2020): Jurnal Patriot
Publisher : Jurusan Kepelatihan, Fakultas Ilmu Keolahragaan, Universitas Negeri Padang

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.24036/patriot.v2i2.642

Abstract

Pelaksanaan Usaha Kesehatan Sekolah merupakan ujung tombak pemberdayaan dilingkungan sekolah agar berperilaku hidup bersih dan sehat. Usaha Kesehatan Sekolah dapat meningkatkan derajat kesehatan serta membentuk prilaku hidup bersih dan sehat peserta didik meliputi: pendidikan kesehatan, pelayanan kesehatan dan pembinaan lingkungan sekolah sehat sebagai langkah untuk meningkatkan mutu kesehatan peserta didik yang optimal. Tujuan UKS adalah meningkatkan mutu pendidikan dan prestasi belajar peserta didik melalui peningkatan perilaku hidup bersih jasmani dan rohani sehingga anak didik dapat tumbuh berkembang secara harmonis dan optimal seiring dengan kemandirian dalam berktifitas dan pada akhirnya menjadi manusia yang berkualitas. Keberhasilan pembinaan dan pengembangan Usaha Kesehatan Sekolah (UKS) akan terlihat atau tercermin pada perilaku hidup bersih dan sehat peserta didik, dan ini merupakan dampak yang diharapkan dari keseluruhan pola pembinaan dan pengembangan UKS. Tujuan dari artikel ini mengenai peran Usaha Kesehatan Sekolah (UKS) sebagai proses Perilaku Hidup Sehat dan Bersih peserta didik.
Predicting water resistance and pitching angle during take-off: an artificial neural network approach Fajar, Muhammad; Atmaja, Sigit Tri; Pinindriya, Sinung Tirtha; Soemaryanto, Arifin Rasyadi; Hidayat, Kurnia
IAES International Journal of Artificial Intelligence (IJ-AI) Vol 14, No 1: February 2025
Publisher : Institute of Advanced Engineering and Science

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.11591/ijai.v14.i1.pp142-150

Abstract

This research addresses the challenges faced by seaplanes and amphibious aircraft during takeoff and landing on water, emphasizing the limitations and costs associated with traditional towing tank tests and computational fluid dynamics (CFD) simulations. The study proposes an innovative approach that employs artificial neural networks (ANN) to predict water resistance and pitching angle during amphibious aircraft take-off, minimizing the reliance on expensive towing tank tests. The ANN models are developed and optimized using Bayesian optimization, showcasing improved accuracy in predicting water resistance and pitching angle. The research demonstrates the potential of machine learning, specifically ANNs, to significantly reduce the need for costly experimental tests, providing an efficient alternative for designing amphibious aircraft. The results indicate high accuracy in predicting water resistance and pitching angle, offering substantial time and resource savings during the experimental phase. However, the study highlights the need for model adaptation for different designs and test variations to enhance overall applicability.
STRATEGI DINAS PENDIDIKAN UNTUK MENINGKATKAN RATA-RATA LAMA SEKOLAH DI KABUPATEN SUMEDANG Hidayat, Kurnia; Akadun; Safaria, Anne Friday
JRPA - Journal of Regional Public Administration Vol. 10 No. 1 (2025): JRPA - Journal of Regional Public Administration
Publisher : LPPM UNSAP & FISIP UNSAP

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Abstract

This study aims to analyze the strategies implemented by the Education Office of Sumedang Regency in an effort to increase the Average Length of Schooling (RLS) in the region. RLS is an important indicator that reflects the accessibility and quality of education and has a direct impact on the socio-economic development of the community. The study employs a qualitative approach with a descriptive method, involving policy analysis, in-depth interviews with stakeholders, and a review of relevant literature. The analysis methods used are SWOT to formulate alternative strategies and QSPM to determine priority strategies. The results of the analysis show that the strategies implemented by the Education Office of Sumedang Regency play a crucial role in efforts to increase the Average Length of Schooling (RLS). Various policies and programs focused on improving access to education, developing infrastructure, and enhancing the quality of educators have had a positive impact, although challenges remain to be addressed. The SWOT and QSPM analyses of internal and external environmental factors indicate that the priority strategies for increasing RLS are integrated interventions to raise educational awareness, optimization of educational investment and operations, and improving the quality of educational facilities, infrastructure, and human resources.
Impact of Airfoil Section on Winglet Design for Enhancing Aerodynamics Performance of Aircraft using CFD Analysis Pinindriya, Sinung Tirtha; Soemaryanto, Arifin Rasyadi; Fajar, Muhammad; Hidayat, Kurnia; Hamonangan, Jefri Abner; Ramadiansyah, Mohamad Luthfi
Indonesian Journal of Aerospace Vol. 21 No. 2 (2023): Indonesian Journal Of Aerospace
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.55981/ijoa.2023.900

Abstract

This research paper investigates the influence of airfoil section on winglet design to enhance aerodynamic performance while considering structural aspects. The selection of the airfoil section significantly affects the distribution of lift and drag along the winglet, influencing the overall lift-to-drag ratio of the aircraft and its ability to reduce drag by smoothing the airflow over the wingtip. Three airfoil sections, namely NACA 0010 (symmetrical), NACA 64-009 (thin cambered), and PSU 94-047 (cambered), were compared using computational fluid dynamics (CFD) simulations. The study examines the forces and moments experienced by the winglet, including drag force, lift force, and bending moment on wing surface. The CFD simulations were conducted using a Computational Wind Tunnel (CWT) tool, which employs numerical methods and mathematical models to analyze fluid flow around objects. The solver code is based on RANS method. The wind tunnel testing is provided to validate one of CFD simulation results. The findings indicate that the installation of winglets increases both the lift-to-drag ratio and bending moment compared to the clean wing configuration. Among the studied airfoil profiles, NACA 0010 demonstrated the optimum lift-to-drag ratio, showing a 9.5% improvement over the clean wing configuration. Although it is a symmetrical airfoil, the thickness of NACA 0010 contributed to higher lift production and increased bending moment compared to the cambered airfoils (NACA 64-009 and PSU 94-047), which showed approximately 10% improvement in lift-to-drag ratio. While the differences in aerodynamic characteristics between the airfoil profiles were marginal, the overall addition of winglets proved effective in increasing lift and reducing induced drag. The research highlights the significance of airfoil shape and thickness in optimizing winglet performance. Future studies should focus on refining the winglet airfoil profile to maximize the benefits derived from both thickness and cambered shape, aiming to further enhance aerodynamic efficiency.
ANALISIS PENENTUAN POWER LOADING PADA DESAIN AWAL PESAWAT TERBANG TANPA AWAK LSU-05 NG Atmasari, Novita; Jayanti, Eries Bagita; Ula, Nur Mufidatul; Ramadiansyah, M. Luthfi; Ramadhan , Redha Akbar; Suseno, Prasetyo Ardi Probo; Rizaldi, Ardian; Hidayat, Kurnia; Septiyana , Angga
Indonesian Journal of Aerospace Vol. 17 No. 2 Desember (2019): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2019.v17.a3162

Abstract

Penelitian ini berfokus pada analisa penentuan power loading pada awal desain pesawat LSU-05 NG. Dengan menentukan power loading maka kebutuhan daya engine untuk pesawat LSU-05 NG dapat diestimasi. Artinya pemilihan engine dapat dilakukan sehingga menghasilkan gaya dorong agar pesawat dapat melakukan misi pemantauan dan foto udara dengan baik. Metode yang digunakan untuk analisa penentuan power loading adalah teknik Matching Chart atau Matching Plot dengan memilih titik optimal dari lima konstrain yaitu jarak take-off, climb rate, stall speed, cruise speed, dan landing. Hasil penelitian menunjukkan bahwa dengan massa 85 kg dan luas sayap 3,22 m2 pesawat LSU-05 NG membutuhkan daya 9.7 hp. Penjelasan lebih detail akan dijabarkan pada bagian selanjutnya.
Effect Of Rubber Damper Stiffness And Tire Pressure To Reduce Ground Reaction Load Factor On Main Landing Gear Using Multi-Body Simulation (MBS) Rigid Model Hidayat, Dony; Istiyanto, Jos; Marta, Aryandi; Hidayat, Kurnia; Sumarsono, Danardono Agus
Indonesian Journal of Aerospace Vol. 17 No. 2 Desember (2019): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2019.v17.a3131

Abstract

Landing Gear Drop Test (LGDT) utilizes the apparatus requiring a substantial time and cost. Virtual LGDT (vLGDT) using MSC ADAMS software is one of the solutions for initial stage to testing landing gear. From simulation with vsink 1.7 m/s and load 22000 N obtained contact/impact force that ensue in MSC ADAMS was 73650 N, while from experimental was 73612 N. The difference between vLGDT and LGDT result is 0.05 %. To obtain ground reaction load factor below 3 in vsink = 3.05 m/s, the rubber damper should have stiffness in the range of 1900 - 2100 N/mm and for the tire pressure of 60 - 65 psi.
Pemilihan Airfoil Pesawat Terbang Tanpa Awak LSU-05 NG dengan Menggunakan Analytical Hierarchy Process Hidayat, Kurnia; Rizaldi, Ardian; Septiyana, Angga; Ramadiansyah, M. Luthfi; Ramadhan , Redha Akbar; Suseno, Prasetyo Ardi Probo; Jayanti, Eries Bagita; Atmasari, Novita; Nurtiasto , Taufiq Satrio
Indonesian Journal of Aerospace Vol. 17 No. 2 Desember (2019): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2019.v17.a3161

Abstract

Pada perancangan pesawat terbang tanpa awak, pemilihan airfoil sangat penting untuk meningkatkan performa pesawat. Airfoil dipilih berdasarkan karakteristik geometri dan performa aerodinamikanya. Penelitian ini membahas tentang pemilihan airfoil dengan banyak kriteria berdasarkan karakteristik masing-masing airfoil. Pada tahap awal, sebanyak 1504 airfoil tersaring menjadi 5 airfoil terpilih. Airfoil tersebut dianalisis berdasarkan 7 kriteria utama, yaitu Camber, Thickness, Manufacturability, Max C_L, C_(L_0 ), Max C_L angle, dan Max L/D. Berdasarkan analisis tersebut, FX 76-MP-160 terpilih sebagai airfoil terbaik untuk pesawat terbang tanpa awak yang dirancang.
Identification of Flow-Induced Noise Sources on Two-Dimensional High Lift Devices of Commuter Aircraft Soemaryanto, Arifin Rasyadi; Fajar, M; Hakim, TMI; Hidayat, Kurnia; Tirtha, Sinung
Indonesian Journal of Aerospace Vol. 19 No. 2 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3500

Abstract

A numerical predictive tool of flow induced noise generated by deployed high-lift devices of commuter aircraft is presented in this paper. The aircraft high-lift devices are consisting of vane and flap component. The aim of this study is to identify the sources of flow induced noise on the wing and flap cross-section of the aircraft. This study is investigated only two-dimensional effects and two configuration of flap deflection. A numerical computation is carried out using a CFD software with Large Eddy Simulation fluid turbulence model and Ffowcs-Williams & Hawkings analogy for acoustic prediction. Several sound receivers have been installed on far-field and near-field region of the wing-vane-flap cross-section of aircraft to measure the sound spectra. It has been identified that on the cavity of wing and vane-flap cross-section has the highest sound pressure level than another region. There is a vortical separation and shear layer which is contributed to the generation of sound emission downward the cross-section
STABILITY AND CONTROLABILITY ANALYSIS ON LINEARIZED DYNAMIC SYSTEM EQUATION OF MOTION OF LSU 05-NG USING KALMAN RANK CONDITION METHOD Septiyana, Angga; Hidayat, Kurnia; Rizaldi, Ardian; Suseno, Prasetyo Ardi Probo; Jayanti, Eries Bagita; Atmasari, Novita; Ramadiansyah, M. Luthfi; Ramadhan, Redha Akbar
Indonesian Journal of Aerospace Vol. 18 No. 2 Desember (2020): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2020.v18.a3318

Abstract

This paper discusses the stability, control and observation of the dynamic system of the Lapan Surveillance UAV 05-NG (LSU 05-NG) aircraft equation. This analysis is important to determine the performance of aircraft when carrying out missions such as photography, surveillance, observation and as a scientific platform to test communication based on satellite. Before analyzing the dynamic system, first arranged equations of motion of the plane which includes the force equation, moment equation and kinematics equation. The equation of motion of the aircraft obtained by the equation of motion of the longitudinal and lateral directional dimensions. Each of these equations of motion will be linearized to obtain state space conditions. In this state space, A, B and C is linear matrices will be obtained in the time domain. The results of the analysis of matrices A, B and C show that the dynamic system in the LSU 05-NG motion equation is a stable system on the longitudinal dimension but on the lateral dimension directional on the unstable spiral mode. As for the analysis of the control of both the longitudinal and lateral directional dimensions, the results show that the system is controlled.
COMPARATIVE STUDY OF WING LIFT DISTRIBUTION ANALYSIS USING NUMERICAL METHOD Septiyana, Angga; Hidayat, Kurnia; Rizaldi, Ardian; Wijaya, Yusuf Giri
Indonesian Journal of Aerospace Vol. 18 No. 2 Desember (2020): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2020.v18.a3349

Abstract

This research focuses on calculating the force distribution on the wings of the LSU 05-NG aircraft by several numerical methods. Analysis of the force distribution on the wing is important because the wing has a very important role in producing sufficient lift for the aircraft. The numerical methods used to calculate the lift force distribution on the wings are Computational Flow Dynamics (CFD), Lifting Line Theory, Vortex Lattice Method and 3D Panel Method. The numerical methods used will be compared with each other to determine the accuracy and time required to calculate wing lift distribution. Because CFDs produce more accurate estimates, CFD is used as the main comparison for the other three numerical methods. Based on calculations performed, 3D Panel Method has an accuracy that is close to CFD with a shorter time. 3D Panel Method requires 400 while CFD 1210 seconds with results that are not much different. While LLT and VLM have poor accuracy, however, shorter time is needed. Therefore to analyze the distribution of lift force on the wing it is enough to use the 3D Panel Method due to accurate results and shorter computing time.
Co-Authors A'isyi, Faizah Rohadatul Akadun Anne Friday Safaria Argantos, Argantos Atmaja, Sigit Tri Atmasari, Novita Danardono Agus Sumarsono Dwianti, Abel Leony Fajar, M Hakim, TMI Hamonangan, Jefri Abner Haq, Syaiful Hidayat, Dony Jayanti, Eries Bagita Jos Istiyanto Marta, Aryandi Muhammad Fajar Nurtiasto , Taufiq Satrio Pinindriya, Sinung Tirtha Putri, Feby Febriani Ramadhan , Redha Akbar Ramadhan, Redha Akbar Ramadiansyah, M. Luthfi Ramadiansyah, Mohamad Luthfi Rizaldi, Ardian Septiyana , Angga Septiyana, Angga Soemaryanto, Arifin Rasyadi Suseno, Prasetyo Ardi Probo Tirtha, Sinung Ula, Nur Mufidatul Utami Wijaya, Yusuf Giri Yuanda, Defa