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Andri Agus Rahman
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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 365 Documents
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METODE DOPPLER RADIO UNTUK MENGUKUR KECEPATAN ROKET RX200 [RADIO DOPPLER METHOD FOR MEASURING VELOCITY OF ROCKET RX200] Widada, Wahyu
Indonesian Journal of Aerospace Vol. 10 No. 2 Desember (2012): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

This paper discusses the methods and design of radio Doppler to measure the speed of the rocket type RX200. Doppler system consists of a radio transponder to emit a continuous radio signal from the rocket and the radio base station to measure the change in frequency of the radio signal. A change in the frequency of the radio signal caused by the speed of the rocket is used to measure the speed and position of the rocket. The design of radio frequency is 880 MHz transponder adapted to the design speed of the rocket RX200. This method is relatively easy to implement compared with the radar transponder system that has been developed. A simulation of Doppler frequency is performed using the radar data transponder rocket launch experiment RX200 and recomendation of bandwith radio receiver should be 4000 Hz. The combination of these two systems will make a more acurate and reliable tracking system.
ISOMERISASI POLIMER MELALUI REAKSI SAIN SAYEF UNTUK MENGUBAH KONFIGURASI HTPB (HYDROXYL TERMINATED POLYBUTADIENE) POLYMER ISOMERIZATION BY SAIN SAYEF REACTION TO MODIFY CONFIGURATION OF HTPB (HYDROXYL TERMINATED POLYBUTADIENE) Heru Budi Wibowo PDF 137- Wibowo , Heri Budi
Indonesian Journal of Aerospace Vol. 14 No. 2 Desember (2016): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2016.v14.a2387

Abstract

One of the problems in the synthesis of Hydroxyl Terminated Polybutadiene for propellant binders is the level of vinyl is high (up to 30%), while the desired product is 20%. Vinyl bond can be reduced if the chain can be broken with the addition of a hydroxyl group. The research objective is to reduce the amount of vinyl structure in HTPB with the addition of double bonds in the vinyl by applying Sayef Sain reaction. HTPB is reacted with concentrated hydrogen peroxide with the Sain Sayef catalyst in the 1 liter autoclave reactor with ethanol for 1-3 hours at 100° C. After being purified by extraction in hot water and drying, it is analyzed by an infrared spectrometer. The result shows that there is a change in the concentrations of vinyl within the polymers produced by observing the absorption of vinyl groups at a wavelength of 690cm-1. Optimal results obtained with vinyl content of 20% with a temperature of 100° C for 90 minutes. In general, the quality of HTPB can be increased by reducing the levels of vinyl which allowing the HTPB composition to have a vinyl content reduced to 19%.
SISTEM PENYALA NIRKABEL JARAK JAUH UNTUK MUATAN ROKET (WIRELESS SWITCHING FOR ROCKET PAYLOAD) Artono, Endro; Salman, Salman
Indonesian Journal of Aerospace Vol. 16 No. 2 Desember (2018): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2018.v16.a2976

Abstract

Proses penyalaan sistem elektronika pada muatan roket hasil litbang LAPAN selama ini masih manual, dengan menggeser atau menekan saklar pada tabung muatan roket dari posisi mati (OFF) ke posisi hidup (ON). Sistem penyala muatan roket ini dirancang untuk dapat menyalakan atau mematikan muatan roket dengan tanpa melakukan kontak fisik antara operator dengan roket. Dari hasil penelitian ini, muatan roket dapat dinyalakan ataupun dimatikan dari ruang kontrol (ground station) secara nirkabel. Sistem ini juga dapat melepaskan perangkat antarmuka untuk sistem penyalaan dari badan roket, sehingga tidak mengganggu roket saat diluncurkan.  Currently, process for turning on the LAPAN rocket’s payload still manually, by shifting or pushing the manual switch placed on the payload rocket’s body, to the OFF or ON direction/ position. This payload wireless switching system is designed for turning the rocket payload to ON or OFF wirelessly, without any phisical contact from operator to the rocket body. The experiment proof that the rocket payload can be turning ON or OFF from the control room wirelessly. The system can also release the umbilical interface from the rocket body before the rocket launched to prevent disruption.
MODEL KOREKSI GEOMETRI SISTEMATIK DATA IMAGER PUSHBROOM MENGGUNAKAN METODE PROYEKSI KOLINEAR [PUSHBROOM IMAGER DATA SYSTEMATIC GEOMETRIC CORRECTION MODEL USING COLLINEAR PROJECTION METHOD] Hakim, Patria Rachman; Rahman, Abdul; Suhermanto; Rachhim, Elvira
Indonesian Journal of Aerospace Vol. 10 No. 2 Desember (2012): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

LAPAN-A3 satellite, which is planned to be launched on 2014, will carry a 4 channels pushbroom imager. An image pre-processing is needed to assure that there will be no distortion on the output image data, particularly a systematic distortion, whether it is geometric or radiometric. Systematic geometric correction is intended to eliminate geometric distortion which are predictable such as view angle, earth curvature, earth rotation and varrying camera orientation during observation. The colinear projection method is used in order to transform every pixel on the image into earth coordinate points. Systematic geometric correction needs satellite ancillary data such as position and camera orientation from GPS and star sensor. This research simulated dummy data as substitute to distorted image and ancillary data for designing and simulation purpose. The simulation result shows that the systematic geometric correction algorithm is able to correct the distortion occured in image. A corrected image with 1000 meter accuracy can be achieved with 0,1 degree orientation data accuracy while 0,01 degree orientation data accuracy produces an even better 100 meter accuracy corrected image for nadir observation.
PENGUKURAN TURBULENSI DAN ANGULARITAS ALIRAN PADA TEROWONGAN ANGIN SUBSONIK LAPAN (THE MEASUREMENT OF TURBULENCE AND FLOW ANGULARITY IN LAPAN’S SUBSONIC WIND TUNNEL) Hartono, Firman; Bessie, Ronald; Aribowo, Agus
Indonesian Journal of Aerospace Vol. 14 No. 2 Desember (2016): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2016.v14.a2481

Abstract

This paper explains the measurement of turbulence intensity and angularity in LAPAN’s Open Loop Subsonic Wind Tunnel. The objective of the research is to find out the aerodynamic characterstic of the tunnel. Turbulence intensities were measured using 200 mm and 300 mm diameter turbulence sphere. The flow angularity in the cross section of tunnel’s test section was measured using five holes probe at two different axial position i.e. 1. above internal balance turning table and 2. above external balance turning table. The number of measured points are 110 for every cross section plane and the average velocity during angular flow measurement is 15 m/s. Turbulence measurements shows wind tunnel’s turbulence intensity of 0.26% at 25.9 m/s and 0.1% at 19 m/s. Angularity measurement shows relatively large angular flow variation in the jet, i.e. pitch angle of ±3o and achieving +7o at some locations and yaw angle of ±2.5o.
Review Perbandingan Teknik Maximum Power Point Tracker (MPPT) untuk Sistem Pengisian Daya menggunakan Sel Surya Azmi, Bayu; H, Jefri Abner; E B, Prasepvianto; Seputra, Hendrik
Indonesian Journal of Aerospace Vol. 16 No. 2 Desember (2018): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2018.v16.a2998

Abstract

Energi surya telah dianggap sebagai prospek sumber energi terbarukan untuk pembangkit tenaga listrik. Sistem fotovoltaik surya menjadi objek yang populer untuk dikembangkan oleh peneliti. Rendahnya efisiensi dalam konversi energi adalah salah satu kelemahan sistem ini. Modul fotovoltaik memiliki titik operasi tunggal di mana output tegangan dan arus menghasilkan output daya maksimum. Dalam kebanyakan sistem fotovoltaik, algoritma kontrol tertentu, yaitu Maximum Power Point Tracker (MPPT) untuk memanfaatkan secara maksimal energi surya tersebut. Ada tiga metode utama pada MPPT yaitu metode konvensional, metode kecerdasan buatan, dan metode hibrid. Setiap metode memiliki kelebihan dan juga kekurangan. Metode konvensional memiliki kelebihan seperti biaya rendah dan implementasi yang sederhana tetapi juga memiliki kerugian seperti tidak dapat beradaptasi dengan kondisi lingkungan. Metode berdasarkan kecerdasan buatan memiliki Power Point Tracking yang lebih cepat dan koreksi terhadap kondisi lingkungan sebagai kelebihannya tetapi juga memiliki kerugian seperti penerapan yang lebih rumit dan biaya yang lebih mahal.
PENGARUH NILAI KOEFISIEN AERODINAMIKA DAN PADA KESTABILAN TERBANG GERAK PERIODE PENDEK (SHORT PERIOD) RKX-200 LAPAN [EFFECT OF AERODYNAMICS COEFFICIENT VALUE AND TO THE STABILITY OF THE FLY MOTION SHORT PERIOD RKX-200 LAPAN] GS, Endang Mugia
Indonesian Journal of Aerospace Vol. 10 No. 2 Desember (2012): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

The rocket flew of short period modes of motion, can be used as a way to measure the stability of the rocket flying. By performing simulation using software Missile DATCOM obtained aerodynamic coefficient and , each of which affects the value of the natural frequency and damping motion short period. RKX-200 Lapan rocket is a quite stable rocket. And the magnitude of the aerodynamic coefficient : -0,12 to -.0,02 and value of : -2,4 to -1,2, with each value remains negative at cruising speed prediction of 0,1 M s.d 2,0 M. It’s good enough to be the guided missile with value 0,18  SM  0,46.
PERUBAHAN KARAKTERISTIK PEMBENTUKAN POLIURETAN BERBASIS HTPB DAN TDI BERDASARKAN KOMPOSISI REAKSI (CHANGES IN THE FORMATION CHARACTERISTICS OF POLYURETHANE BASED ON HTPB AND TDI REACTION COMPOSITION) Rosita , Geni
Indonesian Journal of Aerospace Vol. 14 No. 2 Desember (2016): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2016.v14.a2420

Abstract

Polyurethane formation occurs through crosslinking of a reaction between the hydroxyl group (OH) of HTPB and isocyanate (NCO) of TDI. Polymer network formation reaction will be formed from the linear bond and a combination of crosslinking. At longer reaction, the polyurethane chains are formed increasingly long and followed by changes in the characteristics. If the reaction has been perfect then the polyurethane chain is straight and it will become more flexible.  This research aimed to obtain polyurethane as fuel binder, which was indispendable in solid composite propellant manufacturing. Several samples of existing HTPB were made into a different composition of HTPB/TDI. The process used  reaction kinetics methods based on the composition in order to obtain the mechanical properties of polyurethane.  Average molecular weight, crosslinking density, hardness, and swelling were analized to determine the quality of polyurethane as fuel-binder. The analysis was a consideration for determining the most suitable fuel-binder composition. It was also to test the quality of experimental HTPB produced by LAPAN HTPB Laboratory (HTPBlocal) as an initial procedure in the propellant manufacturing. The analysis showed different results for each composition. The compositions that could be used as the fuel-binder for the formation of polyurethanes were: HTPBA at 7: 1; HTPBB at 9: 1; HTPBC at 8: 1; and HTPBD at 8: 1; whereas HTPBE could not be used because required advanced processing.
EVALUASI KINERJA SAMBUNGAN PROPELAN PADA MOTOR ROKET RX 550 [EVALUATION OF THE PROPELLANT JOINT PERFORMANCE IN ROCKET MOTOR RX 550] Sutrisno
Indonesian Journal of Aerospace Vol. 10 No. 2 Desember (2012): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

The propellant joints quality of RX 550 rocket motor using segmented HTPB propellant was become a debatable. In static test this rocket motor exploded and the nozzle was broken out at seven second after ignition. To evaluate these propellant joints the propellant installation in rocket motor was discused. The propellant joint strength was tested using Tensilon UTM III-100 test equipment. The rocket motor tube at the propellant joint position were marked and investigated before and after static test. The datas such as thrust and chamber pressure versus time were analyzed for finding the posibility of joints defect. Based on analysis it is found that the propellant joint can work well. The RX 550 rocket motor failure in static test didn’t caused by propellant joints.
Back Pages JTD Vol 14 No 2 Des 2016 Jurnal, Redaksi
Indonesian Journal of Aerospace Vol. 14 No. 2 Desember (2016): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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