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INDONESIA
Indonesian Journal of Aerospace
Published by Badan Riset dan Inovasi Nasional
ISSN : -     EISSN : 30320895     DOI : https://doi.org/10.55981/ijoa
Core Subject : Science, Engineering,
Aerospace Engineering Astronomy
Indonesian Journal of Aerospace provides a broad opportunity for the scientific and engineering community to report research results, disseminate knowledge, and exchange ideas in various fields related to aerospace science, technology, and policy. Topics suitable for publication in the IJoA include (but are not limited to) Space science (astrophysics, heliophysics, magnetospheric physics, ionospheric physics, etc.), Aeronautics technology (dynamic, structure, mechanics, avionics, etc.), Space technology (rocket, satellite, payload system, control, etc.), Propulsion and energetic technology (propellant, rocket static-test, thermodynamics of propulsion system, etc.), Aeronautics and space policy, and Application of aerospace science and technology.
Arjuna Subject : Ilmu Bumi dan Planet (semua kategori) - Ruang Angkasa dan Ilmu Planet
Articles 364 Documents
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SISTEM KENDALI KOOPERATIF UAV UNTUK MENDUKUNG PENGAWASAN ILLEGAL FISHING Wiyono, 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.a3128

Abstract

Terjadinya kegiatan illegal fishing sangat merugikan bagi bangsa Indonesia, terutama bagi para nelayan. Kementerian Kelautan dan Perikanan merupakan institusi pemerintah yang memiliki kewenangan dalam melakukan pengawasan dan penindakan terhadap kegiatan illegal fishing. Salah satu kegiatan pengawasan yang dilakukan selama ini adalah dengan memanfaatkan pesawat terbang berawak. Hal tersebut memiliki beberapa kelemahan. Untuk melengkapi kekurangan yang ada dalam penggunaan pesawat terbang berawak, pengoperasian UAV dapat digunakan untuk mendukung operasi pengawasan illegal fishing. Penggunaan single-UAV tidak akan sesuai tugas pengawasan dimana area yang diawasi sangatlah luas. Aplikasi multi-UAV untuk melaksanakan tugas semacam ini akan cukup efektif. Untuk mewujudkannya suatu system kendali kooperatif telah dibangun. Pada tahap pertama, sistem kendali dibangun dan diuji dalam lingkungan virtual yaitu melalui simulasi. Perangkat lunak yang digunakan untuk membangun system kendali adalah: Matlab/Simulink untuk membangun sistem kendali terbang dan X-Plane 9 digunakan untuk pemodelan matematis pesawat dan visualisasi dinamika pesawat. Metoda kooperatif yang digunakan adalah leader-follower. Hasil yang diperoleh menunjukan bahwa simulasi multi-UAV dengan menggunakan Matlab/Simulink dan X-Plane telah berhasil digunakan untuk mengendalikan 3 UAV mengikuti topologi kooperatif.
VISUALISASI 2 DIMENSI POSISI SATELIT ORBIT RENDAH MENGGUNAKAN SGP4, MERCATOR, DAN VISUAL BASIC 6 Pratomo, Bina; Mayditia, Hasan
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.a3154

Abstract

Perkiraan posisi satelit sangat diperlukan oleh banyak penggiat satelit untuk dapat mengakses satelit tepat waktu terutama satelit orbit rendah yang posisinya tidak selalu tepat di atas sebuah daerah secara terus menerus, dengan menggunakan data TLE, algoritma SGP4, dan teknik mercator yang di implementasikan ke dalam bahasa pemrograman visual basic 6 berhasil memvisualisasikan posisi satelit dalam tampilan dua dimensi.
Back Pages JTD Vol 17 No.2 Desember 2019 Jurnal, Redaksi
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.a3284

Abstract

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Front Pages JTD Vol 19 No.1 June 2021 Jurnal, Redaksi
Indonesian Journal of Aerospace Vol. 19 No. 1 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

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The Effect of Cross-section and Elliptical Hole Ratio on Crashworthiness Parameters of Crash-Box Structure Warsiyanto, Budi Aji; Widanto, Muhammad Hadi; Musthofa, Ilham; Maulana, Ichsan; Sitompul, Sahril Afandi; Yuniarti, Endah
Indonesian Journal of Aerospace Vol. 19 No. 1 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3408

Abstract

The thin-walled column structure or crash-box with metal material and consisting of multi-cell were found to be much more efficient in energy absorption than single-cell under axial impact loads. In this study, a numerical analysis was performed using the Abaqus finite element method for the cross-section differences in thin-walled column structures. The cross-section differences are compared to get a configuration that complies with the indicator parameters using the complex proportional assessment (COPRAS) method. The chosen cross-section configuration is further enhanced by creating elliptical holes with different diameter ratios. The results show that the thin-walled column structure with nine-cell cross-section accompanied by an elliptical hole ratio of 0.3 indicates the potential corresponding to the indicator parameters for the crashworthiness application.
Investigation of Wire Diameter of Helical Compression Spring for Payload Separation Laksono, Shandi Prio
Indonesian Journal of Aerospace Vol. 19 No. 1 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3490

Abstract

The payload is designed to be separated from rocket at an altitude over 100 km. Â One of critical component in the payload separation system is the helical compression spring. The helical compression spring ensures safe release the payload. The spring must satisfy some parameters such as static failure and buckling, also spring has enough energy storing to release the payload during launch. The objective of this paper is to do investigation of wire diameter of helical compression spring which can be used in the payload separation system of sounding rocket based on several constraints. The results obtained show that with payload weight of 60 kg, minimum wire diameter should be 8 mm with mean coil diameter of 80 mm. The maximum separation velocity of 1.76 m/swas obtained by using wire diameter of 8 mm and mean coil diameter of 96 mm.
Properties Comparison of Open Hole and Non-Hole Carbon UD-Lycal Composite with Vacuum Bagging Manufacturing Method Isna, Lathifa Rusita; Nugroho, Afid; P, Rezky Agung; R, Redha Akbar
Indonesian Journal of Aerospace Vol. 19 No. 1 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3494

Abstract

Carbon fiber reinforce polymer is one of some composite materials that has the high strength with light weight material. To apply this composite to the amphibious airplane structure, it should through the experimental tensile test to know the tensile strength and modulus of elasticity of the composite. In this experiment, we use Carbon UD fiber and Lycal resin as the composite material that manufactured with Vacuum Bagging Method. Specimens and testing process refer to ASTM D3039 for non-hole specimen, and ASTM D5766 for open hole specimen of tensile test standard for composite matrix polymers. The result of the experimental test shows that the tensile modulus of elasticity for non-hole composite is 34.92 ± 0.13 GPa, with the Ultimate Tensile Strength of this composite is 1081± 0.03 MPa, and the modulus of elasticity for open hole composite is 41.87± 0.02 GPa, with the Ultimate Tensile Strength of this composite is 899.04± 0.02 MPa. The simulation yields nearly same stress-strain graph with the result of experiment. The result shows that, the open hole composite has the ultimate tensile strength lower than non-hole composite, it’s due to the open hole composite has a trigger failure that may decreasing the tensile strength value.
INFORMATION EXTRACTION FROM LAPAN SATELLITE AIS DATABASE FOR SHIP CLASSIFICATION IN THE INDONESIAN TERRITORIAL WATERS Nugroho, Muazam; Ferdiansyah, Nurrochman; Rahayu, Dicka Ariptian; Permala, Rizki; Hakim, Patria Rachman; Hasbi, Wahyudi
Indonesian Journal of Aerospace Vol. 19 No. 1 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3566

Abstract

Automatic Identification System (AIS) is a system used to monitor ship activity by sending ship information via Very High Frequency (VHF) waves. Information sent by ships around the world is recorded by AIS receivers carried by the LAPAN-A2 and LAPAN-A3 satellites along their orbital trajectories. The AIS data recorded by the satellite will then be acquired and stored at the LAPAN earth station. This study focuses on extracting information from the LAPAN satellite AIS database to obtain information on the number of vessels based on a unique Maritime Mobile Service Identity (MMSI) grouped according to the type of vessel entering Indonesian waters with coordinates 95BT / 141BT, -11LS / 6LU every month. in the period January to December 2019. The results of extracting the information are in the form of the number of ships based on unique MMSI which are grouped according to the type of ship in the territory of Indonesia with that region and time period
POWERED LANDING GUIDANCE ALGORITHMS USING REINFORCEMENT LEARNING METHODS FOR LUNAR LANDER CASE Nugroho, Larasmoyo; Zani, Novanna Rahma; Qomariyah, Nurul; Akmeliawati, Rini; Andiarti, Rika; Wijaya, Sastra Kusuma
Indonesian Journal of Aerospace Vol. 19 No. 1 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3573

Abstract

Any future planetary landing missions, just as demonstrated by Perseverance in 2021 Mars landing mission require advanced guidance, navigation, and control algorithms for the powered landing phase of the spacecraft to touch down a designated target with pinpoint accuracy (circular error precision < 5 m radius). This requires a landing system capable to estimate the craft’s states and map them to certain thrust commands for each craft’s engine. Reinforcement learning theory is used as an approach to manage the mapping guidance algorithm and translate it to engine thrust control commands. This work compares several reinforcement learning based approaches for a powered landing problem of a spacecraft in a two-dimensional (2-D) environment, and identify the advantages/disadvantages of them. Five methods in reinforcement learning, namely Q-Learning, and its extension such as DQN, DDQN, and policy optimization-based such as DDPG and PPO are utilized and benchmarked in terms of rewards and training time needed to land the Lunar Lander. It is found that Q-Learning method produced the highest efficiency. Another contribution of this paper is the use of different discount rates for terminal and shaping rewards, which significantly enhances optimization performance. We present simulation results demonstrating the guidance and control system’s performance in a 2-D simulation environment and demonstrate robustness to noise and system parameter uncertainty.
Station-Keeping Simulation and Planning for LAPAN-A4 Satellite Using Finite-Burn Thruster Zuhri, Muhammad Rizki; Poetro, Ridanto Eko
Indonesian Journal of Aerospace Vol. 19 No. 1 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3474

Abstract

To be a Sun-synchronous orbit (SSO), the orbit must have a certain value of nodal precession rate, which equals to 360°/year. However, the value of nodal precession rate is usually drifted by orbit perturbations, mainly by the oblateness of the Earth and atmospheric drag, to be no longer 360°/year as expected for SSO. Thus, the local time of the satellite will change too, so it needs to be corrected by some correction maneuvers. In this research, the authors studied about station-keeping planning for SSO satellite via inclination correction maneuver by simulation using GMAT, a software developed by NASA, with a finite-burn propulsion approach. In this research, LAPAN-A4 satellite is chosen to be the satellite that will be simulated. Some alternative plans of inclination correction maneuver based on maneuvering periods are chosen, they are maneuver for every 2 months, 4 months, 6 months, 12 months, and 24 months. The simulation results show that the optimal station keeping planning is the maneuver for every 2 months. This alternative gives the lowest fuel consumption so that the fuel and launch cost will be minimum, and the local time drift that is still may be tolerated.

Page 5 of 37 | Total Record : 364

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