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Jurnal Teknologi Dirgantara
Published by Lembaga Penerbangan dan Antariksa Nasional
ISSN : 14128063     EISSN : 25977849     DOI : https://doi.org/10.30536
Core Subject : Science, Engineering,
Aerospace Engineering Chemical Engineering, Chemistry & Bioengineering Computer Science & IT Mechanical Engineering Physics
Jurnal Teknologi Dirgantara (Journal of Aerospace Technology) is an Indonesian accredited scientific publication that covers topics of Rocket, satellite, and aeronautics technology, as well as a spin-off from aerospace technology, such as aerodynamics, astronautics, aerospace structure, power and thermal system of satellites, flight controls. Propulsion and energetic technologies, such as propellant, rocket static-test, thermodynamics of propulsion system. Launch vehicle technology and space operations, such as satellite telecommunication systems, space payloads, and ground station technologies.
Arjuna Subject : Teknik (semua kategori) - Teknik Ruang Angkasa
Articles 13 Documents
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Search results for , issue "Vol 19, No 1 (2021)" : 13 Documents clear
Properties Comparison of Open Hole and Non-Hole Carbon UD-Lycal Composite with Vacuum Bagging Manufacturing Method Lathifa Rusita Isna; Afid Nugroho; Rezky Agung Pratomo; Redha Akbar Ramadhan
Jurnal Teknologi Dirgantara Vol 19, No 1 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

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.
Dynamic response of the wing during UAV collision Budi Aji Warsiyanto
Jurnal Teknologi Dirgantara Vol 19, No 1 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3514

Abstract

An airborne collision between civil Unmanned Aerial Vehicles (UAVs) and manned aircraft is a potential threat to aircraft operation safety. In this paper, the UAV collision test was performed on a commuter aircraft wing section to investigate the dynamic response of this primary operation component. The projectile was a 735 g drone named ‘Mavic’. Explicit dynamic code ABAQUS was employed to simulate the collision process based on the difference of collision scenarios to assess the hazard. The results showed that 735 g drone impact at the aircraft maximum approach flap and cruising speed could cause some damage on the wing front spar and the situation is more serious than 910 g bird strike in which the hardness of drone components rather than kinetic energy is a decisive factor. The lithium-ion battery penetrated the airframe which may be a potential source of ignition.
INFORMATION EXTRACTION FROM LAPAN SATELLITE AIS DATABASE FOR SHIP CLASSIFICATION IN THE INDONESIAN TERRITORIAL WATERS Muazam Nugroho
Jurnal Teknologi Dirgantara Vol 19, No 1 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

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
Research on the Transmissibility of Wire Rope Insulators as Damping Equipment on the RX 200 Rocket Payload Ronald Gunawan Putra
Jurnal Teknologi Dirgantara Vol 19, No 1 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3556

Abstract

Wire rope insulator or steel wire rope insulator has applications for vibration isolation in equipment and structures in many industrial machinery. Steel wire rope insulators can also be used as suitable equipment to dampen vibrations in rocket loads. The disturbance acceleration as the excitation caused by the combustion process on the rocket can cause a vibration with a large amplitude which results in damage to the rocket's payload structure and the electronic equipment on the rocket's payload cannot work as desired. Based on the experience of electronic equipment, it will be damaged if the disturbance acceleration of 3 g acting on the rocket is not reduced, for this reason a vibration damping device is designed, the apparatus consists of several stainless steel wire ropes tied between two parallel binders arranged in such a way as to provides a damping effect on the rocket's payload. A wire rope insulator consists of several stainless steel wire ropes tied between two parallel straps. One application of this type of wire rope insulator is to isolate the vibrations that occur in the rocket, so that it does not interfere with the performance of the electronic equipment on the rocket's payload. Electronic equipment is used to determine the position of the rocket and its stability. In this study, the wire rope material used is stainless steel with syield = 350 e+6 N / m2 with a diameter of d = 3 mm.The research objective of the vibratory damper of wire rope insulators was to determine the magnitude of the transmissibility of the ruffler during and after resonance. Transmissibility (TR) is the ratio of the force transmitted to the disturbing or excitation force.The results of the research on a damper with a disturbance acceleration of 3 g at resonance, obtained the transmissibility value (TR) = 2.54, the spring stiffness k = 200537.3 N/m and the damping coefficient c = 331.5 N/m/sec, then after conditions  obtained transmissibility (TR) <1 This shows that the damper with steel wire isolator is good enough to dampen vibrations in the RX 200 rocket payload.
POWERED LANDING GUIDANCE ALGORITHMS USING REINFORCEMENT LEARNING METHODS FOR LUNAR LANDER CASE Larasmoyo Nugroho
Jurnal Teknologi Dirgantara Vol 19, No 1 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

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.
Effects of Bleeder Schedule to Fiber Mass Fraction and Composites Surface Topography on Wet Lay-up Manufacturing Process Wiwiek Utami Dewi
Jurnal Teknologi Dirgantara Vol 19, No 1 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3572

Abstract

The thermal protector materials of the rocket’s motor are made by a wet lay-up manufacturing process. Since the fiber mass fraction of the product is low, several experiments were conducted to solve this problem including changing the type of the epoxy resin and selecting the most suitable bleeder schedule. Bleeder cloth application results in increasing the fiber mass fraction. The fiber mass fraction of thermal protector material manufactured by hand lay-up can reach a maximum of 56,78%, whereas vacuum bagging can reach a maximum of 66,43%. Peel ply and breather fabric combination are the best bleeder schedule for the hand lay-up method meanwhile perforated release film and breather fabric are the best bleeders for the vacuum bagging method. Composite surface topography obtained from peel ply is visible on the surface. The imprints of the nylon peel ply weave are visible through SEM analysis. Meanwhile, the surface topography obtained from the perforated release film is not visible. The vacuum bagging method helped reduce the number of voids and ductile polymer fractures from the composite surface. This paper recommends peel ply usage in the thermal protector manufacturing process to replace the sanding or filling method that the author use nowadays.
The Effect of Cross-section and Elliptical Hole Ratio on Crashworthiness Parameters of Crash-Box Structure Budi Aji Warsiyanto
Jurnal Teknologi Dirgantara Vol 19, No 1 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

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.
Station-Keeping Simulation and Planning for LAPAN-A4 Satellite Using Finite-Burn Thruster Muhammad Rizki Zuhri
Jurnal Teknologi Dirgantara Vol 19, No 1 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

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.
Front Pages JTD Vol 19 No.1 June 2021 Editorial Jurnal
Jurnal Teknologi Dirgantara Vol 19, No 1 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3633

Abstract

Investigation of Wire Diameter of Helical Compression Spring for Payload Separation Shandi Prio Laksono
Jurnal Teknologi Dirgantara Vol 19, No 1 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

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.  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.

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