Jurnal Teknologi Dirgantara
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.
Articles
333 Documents
<![CDATA[SIMULASI KINERJA FORWARD ERROR CONTROL CODING UNTUK SATELIT MIKRO PENGINDERAAN JARAK JAUH ]]>
<![CDATA[- Dwiyanto]]>;
<![CDATA[- Sugihartono]]>
<![CDATA[ Jurnal Teknologi Dirgantara Vol 9, No. 2 Desember (2011) ]]>
Publisher : <![CDATA[National Institute of Aeronautics and Space - LAPAN ]]>
Show Abstract
|
Download Original
|
Original Source
|
Check in Google Scholar
<![CDATA[Micro satellite application for remote sensing in this time has been expanded and particularly supported by growth of electronics component that low power and small size. Large amount of image data, less of contact time and limited satellite’s power obliges of efficiency mechanism design to assured data satellite communication is accepted properly by earth station. Various of scenario of data transmissions on micro satellite have been developed in order to ensure all data that taken by payload can be delivered and accepted by station earth truly. Forward Error Control Coding or Forward Error Correction method is mechanism that added redundancy bit to delivery data with a purpose to improve error correction of received data. FEC performance can be known by compare of different value of Eb/N0 needed for Bit Error Rate (BER) in common without FEC. In this research conducted simulation performance FEC Reed Solomon by undertaking change of beet amount per symbol, code length and code ability in repairing symbol error. Simulation Result shows getting smaller code rate that used then ever greater code reinforcement. The simulation using forward error control coding Reed Solomon for data transmission remote sensing results code RS(255,223) have best performance with coderate 0,874 and coding gain 3,4dB on value of BER 10-4. Keywords: Reed Solomon, QPSK, 16-QAM, Remote sensing]]>
<![CDATA[ANALYSIS OF ELECTRICAL LOAD ASSESSMENT LSU (LAPAN SURVEILLANCE UAV) 03 ]]>
<![CDATA[Imas Tri Setyadewi]]>
<![CDATA[ Jurnal Teknologi Dirgantara Vol. 17 No. 1 Juni 2019 ]]>
Publisher : <![CDATA[National Institute of Aeronautics and Space - LAPAN ]]>
Show Abstract
|
Download Original
|
Original Source
|
Check in Google Scholar
|
DOI: 10.30536/j.jtd.2019.v17.a3108
<![CDATA[LSU 03 Aircraft was used for LSU MISI with capability cruise up to 340 km. LSU 03 has an operation for marine safety from illegal fishing. To support the monitoring mission of illegal fishing with operation range up to 250 km or 3 hours flight, several required system are needed such as autopilot system, datalink, propulsion, and payload. All of system then analysed by an ELA (Electrical Load Assessment) of the aircraft system to know the necessary power required to conduct the initial mission of the aircraft. ELA analysis is done by calculating the power requirement from each component specification and function test of the component for validation of calculation result. From the results of the study, the amount of power consumption is 35% from the spec calculation, which is 32.43 Wh which can be accommodated by a battery system up to 4.2 hours. Whereas for ignition or aircraft engines whose source of battery uses LIPO 2S 7.4 Vdc batteries can accommodate the ignition energy requirements for more than 11 hours.]]>
<![CDATA[ANALISIS NOSEL MOTOR ROKET RX - 122 LAPAN SETELAH DILAKUKAN PEMOTONGAN PANJANG DAN DIAMETER ]]>
<![CDATA[Ahmad Jamaludin]]>
<![CDATA[ Jurnal Teknologi Dirgantara Vol 6, No.1 Juni (2008) ]]>
Publisher : <![CDATA[National Institute of Aeronautics and Space - LAPAN ]]>
Show Abstract
|
Download Original
|
Original Source
|
Check in Google Scholar
<![CDATA[Telah dilakukan penelitian dan analisis ulang nosel motor roket RX - 122 milik LAPAN. Nosel tersebut didesain untuk tekanan ruang bakar 70 bar. Hasil perhitungan secara analitis menunjukkan bahwa gaya dorong yang dihasilkan seharusnya sebesar 18,6 kN. Hasil simulasi numerik memberikan gaya dorong yang lebih kecil, yaitu sebesar 18,0 kN. Perbedaan tersebut dikarenakan adanya gesekan antara aliran gas dengan permukaan bagian dalam nosel yang mana ditandai dengan penurunan tekanan total sebesar 13%. Diameter awal nosel adalah 130 mm. Oleh karena keterbatasan dimensi motor roket, maka diameter nosel harus dibatasi maksimum 100 mm. Pengurangan diameter nosel dilakukan dengan cara memotong nosel sepanjang 85 mm. Pemotongan tersebut mengakibatkan penurunan prestasi nosel. Perhitungan secara analitis dan simulasi numerik memberikan gaya dorong masing – masing 18,1 kN dan 17,7 kN. Akibat pemotongan panjang nosel tersebut, maka gaya dorong yang dihasilkan nosel berkurang hanya sekitar 2%.]]>
<![CDATA[ANALISIS HASIL PENGUJIAN DAN PREDIKSI TEORITIS AERODINAMIKA ROKET RX 300 ]]>
<![CDATA[Salam Ginting]]>
<![CDATA[ Jurnal Teknologi Dirgantara Vol 5, No.2 Desember (2007) ]]>
Publisher : <![CDATA[National Institute of Aeronautics and Space - LAPAN ]]>
Show Abstract
|
Download Original
|
Original Source
|
Check in Google Scholar
<![CDATA[LAPAN has a supersonic wind tunnel facility which could be used for research of rocket model to get aerodynamics characteristic of the model through testing with various speeds within supersonic range. The research on the RX 300 rocket model has been carried out in the above facility at velocity range of 1,5-3 Mach. Some aerodinamic are obtained from this research. Such as lift drag and moment ceofficients. Aerodynamic coefficient is shown in the curve as a function of Mach and angle of attack. This result will be compared with the theoretical calculation and the result is higher around 5 percent than theory. The approach of Quadrature Multhopp is method use in this analysis. The RX 300 rocket model is equipped with foru flaps at the back part of the rocket as a stabilizer when the rocket is launched. This rocket is designed for being able to carry a payload with dimention of 25 cm diameter and 45 cm length. Keywords: Aerodynamic rocket, Wind tunnel.]]>
<![CDATA[ALGORITMA DETEKSI FREKUENSI DTMF MENGGUNAKAN KORELASI SILANG UNTUK TELEKOMANDO WAHANA TERBANG (DTMF FREQUENCY DETECTION ALGORITHM USING CROSSCORRELATION FOR VEHICLE TELECOMMAND) ]]>
<![CDATA[Sri Kliwati]]>
<![CDATA[ Jurnal Teknologi Dirgantara Vol. 14 No. 1 Juni 2016 ]]>
Publisher : <![CDATA[National Institute of Aeronautics and Space - LAPAN ]]>
Show Abstract
|
Download Original
|
Original Source
|
Check in Google Scholar
|
DOI: 10.30536/j.jtd.2016.v14.a2942
<![CDATA[In general, the frequency DTMF detection algorithm using FFT (Fast Fourier Transform) and Goertzel Algorithm. However, in certain circumstances a more suitable signal detected by the other algorithms. For example in a non-periodic signal as the measurement sensors for flight vehicle. The purpose of this study is to develop a system telecommand for flight vehicle. And this paper discusses the frequency DTMF (Dual Tone Multi Frequency) detection method using cross correlation algorithm and data-base DTMF. The simulation results show the frequency detection successfully carried out in accordance with the accuracy of the data-base created (1 Hz) to change the frequency of zero to 1700 Hz (DTMF frequency limit). ABSTRAKDeteksi frekuensi DTMF secara umum menggunakan algoritma Fast Fourier Transform (FFT) dan Goertzel Algorithm. Akan tetapi pada kondisi tertentu sebuah sinyal lebih cocok dideteksi dengan algoritma yang lain. Misalnya pada sinyal yang non-periodik seperti pada pengukuran sensor-sensor wahana terbang. Tujuan penelitian ini adalah membangun sistem telekomando untuk wahana terbang. Dan tulisan ini membahas metode deteksi frekuensi Dual Tone Multi Frequency (DTMF) dengan menggunakan algoritma korelasi silang dan data-base DTMF. Hasil simulasi menunjukkan deteksi frekuensi berhasil dilakukan sesuai dengan akurasi database yang dibuat (1 Hz) untuk perubahan frekuensi antara nol hingga 1700 Hz (batas frekuensi DTMF).]]>
<![CDATA[Properties Comparison of Open Hole and Non-Hole Carbon UD-Lycal Composite with Vacuum Bagging Manufacturing Method ]]>
<![CDATA[Lathifa Rusita Isna]]>;
<![CDATA[Afid Nugroho]]>;
<![CDATA[Rezky Agung Pratomo]]>;
<![CDATA[Redha Akbar Ramadhan]]>
<![CDATA[ Jurnal Teknologi Dirgantara Vol 19, No 1 (2021) ]]>
Publisher : <![CDATA[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
<![CDATA[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.]]>
<![CDATA[Dynamic response of the wing during UAV collision ]]>
<![CDATA[Budi Aji Warsiyanto]]>
<![CDATA[ Jurnal Teknologi Dirgantara Vol 19, No 1 (2021) ]]>
Publisher : <![CDATA[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
<![CDATA[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.]]>
<![CDATA[INFORMATION EXTRACTION FROM LAPAN SATELLITE AIS DATABASE FOR SHIP CLASSIFICATION IN THE INDONESIAN TERRITORIAL WATERS ]]>
<![CDATA[Muazam Nugroho]]>
<![CDATA[ Jurnal Teknologi Dirgantara Vol 19, No 1 (2021) ]]>
Publisher : <![CDATA[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
<![CDATA[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]]>
<![CDATA[Research on the Transmissibility of Wire Rope Insulators as Damping Equipment on the RX 200 Rocket Payload ]]>
<![CDATA[Ronald Gunawan Putra]]>
<![CDATA[ Jurnal Teknologi Dirgantara Vol 19, No 1 (2021) ]]>
Publisher : <![CDATA[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
<![CDATA[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.]]>
<![CDATA[POWERED LANDING GUIDANCE ALGORITHMS USING REINFORCEMENT LEARNING METHODS FOR LUNAR LANDER CASE ]]>
<![CDATA[Larasmoyo Nugroho]]>
<![CDATA[ Jurnal Teknologi Dirgantara Vol 19, No 1 (2021) ]]>
Publisher : <![CDATA[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
<![CDATA[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.]]>
