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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 6 Documents
 1 
Search results for , issue "Vol. 2 No. 1 (2004): Jurnal Teknologi Dirgantara" : 6 Documents clear
PELAPISAN PERMUKAAN DALAM NOSEL ROKET RKX100 DENGAN Cr2C3-NiCr HVOF: OPTIMASI KEKUATAN LEKAT MELALUI VARIASI KEKASARAN PERMUKAAN Sofyan, Bondan T. Sofyan; Prasetyo, Yus; Ardiansyah, Sayid; Sofyan, Edy
Indonesian Journal of Aerospace Vol. 2 No. 1 (2004): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2004.v2.a788

Abstract

Nozzle of RKX100 rocket contributes 30 percent to the total weight of the structure, so that allowing further research on weight reduction. An alternative for this is by substitution of massive graphite, which is currently used as thermal protector in the nozzle, with thin layer of HVOF (High Velocity Oxy-Fuel) thermal spray layer. A series of study on the characteristics of various type of HVOF coating material have been being conducted. This paper presented the investigation on the HVOF Cr2C3-NiCr thermal spray coating, in particular, the optimization of bonding strength by varying surface roughness of substrates. Characterization included bonding strength test, micro hardness measurement and micro structural observation with optical microscope and scanning electron micriscope (SEM). The results showed that grit blasting pressure increass the surface roughness from 4,54 um to 5.72 um at the pressure of 6 bar. Average micro hardness of the coating was 631 VHN 300. Coating applied to the surface with rougness of 5.42 um possessed the highest bonding strength, 44 MPa. Microstructural observation by using optical microscope and scanning electron microscope (SEM) confirmed dense lamellae structure with variable composition. High coating adherence was found to be due to mechanical interlocking.
UJI VALIDASI TERMAL VIBRASI UNTUK MUATAN MISI MIKROSAT Syah, Agus Harno Nurdin
Indonesian Journal of Aerospace Vol. 2 No. 1 (2004): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2004.v2.a789

Abstract

To launching a spacecraft (rocket and satellite) including all of the systems, some rules and regulation of validation test for all the spacecraft systems is needed. Validation test mentioned is done to find out the ability of all the systems to the environmental influences of the external although internal with measurements simultaneously done. This is including possibilities the operating all of the electronic systems and epending the life times, operation time of the internal and external condition to the parameters effect of environmental the spacecraft systems. Thermal vibration is two parameters effect of environmental which would receiped simultaneously by the microsatellite or spacecraft on trajectory time when the spacecraft inside of the thermospheer zone at height about (80-500) km and the exospher zone at height about (500-1000)km under the seal level. Therefore, thermal vibration test is very important to do before a spacecraft or microsatellite would be launched, because the environmental parameters is very dangerous to the microsatellite or spacecraft mission payload.
PENELITIAN DAN PENGUJIAN KARAKTERISTIK AERODINAMIKA BOM LATIH PERCOBAAN BLP-500 DAN BLP 25 Markis, Yus Kadarusman; Ariwibowo, Agus; Atmadi, Sulistyo
Indonesian Journal of Aerospace Vol. 2 No. 1 (2004): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2004.v2.a790

Abstract

Research and aerodynamic testing of BLP-500 and BLP-25 have been conducted in both subsonic and supersonic wind tunnel. Aerodynamic characteristics such as Cl, Cd, and Cm for these types of bomb we obtained. By knowing the aerodynamic characteristics, the stability and trajectory of the bomb can be determined. Both analytical calculation and real tests in the wind tunnel were performed and compared. The results showed that for its static stability, the location of the centre of gravity of BLP-500 and BLP-25 to be less than 115.1 cm and 31.9 cm respectively.
RANCANGAN DAN ANALISA ANTENA DI PERMUKAAN BADAN ROKET Kliwati, Sri; Widada, Wahyu
Indonesian Journal of Aerospace Vol. 2 No. 1 (2004): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2004.v2.a791

Abstract

The antenna telemetry is usually placed in the body of LAPAN rocket for the launching campaign, which affected to the quality of radio communication. Especially, such effect increas the antenna overshadow to the surface of body rocket, which not influenced to the aerodynamic of rocket. This antenna was made by using the PCB plate with size of 1 cm width and 1 per 2 also 1 per 4 length for the frequency of 900 MHz
PENELITIAN KARAKTERISTIK AERODINAMIKA AEROFOIL SUDU SKEA NELAYAN NILA 80 Atmadi, Sulistyo
Indonesian Journal of Aerospace Vol. 2 No. 1 (2004): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2004.v2.a792

Abstract

An economical electric-small-scale wind turbine is intended for an alternative source of energy for fishermans. For the power requirment of wind turbine with the wind condition in Indonesia, an aerofoil research is needed, in particular for the case of SKEA Nelayan Nila 80, with unknown aerofoil data. The focus of the research concentrated on finding aerodynamics characteristic Cl, Cd and Cm for angle of attack regime from 4 to 16 degrees. The result would be used in the modification of existing wind turbine. With limited engineering data, several integrated softwares had been used such as AutoCad 2004, Gambit and fluent 5.2.1 AutoCad was used to digitise aerofoil geometry, gambit was used for grid generation wich then fed into Fluent 5.2.1. for load analysis. The result was quite similiar to N-60 which gives stall angle at around 13 degree-15 degree and Cl per Cd maximum equal 16.
ANALISIS MODUS NORMAL DAN KEKUATAN STRUKTUR SIRIP ROKET-168 DARI BAHAN AL-PLATE Sugiarmadji HPS; Setiadi
Indonesian Journal of Aerospace Vol. 2 No. 1 (2004): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2004.v2.a793

Abstract

Structural strength analysis on Motor Rocket-168 fins was carried out to determine static stresses due to aerodynamic loadings. Here, 90 mm of the root chord area from leading edge was unclamp (free). The analysis results showed the maximum value of von Mises stress is Q von mises = 42.40 MPa. For 90 mm condition un clamp (free) we obtained the safety factor of the material for fins structures made of Al-Plate is SF=3.39. For 67.5 mm of 90 mm root chord area constrainted at 12456 directions, it was found Qvm equal 11,26 MPa and has higher safety factor. Eigenvalues and eigenvectors of the fins structures. The results showed that the eigenvalues of the fin structures are Q1 equal 198,47 Hz, Q2 equal 616,34 Hz, Q3 equal 1080,97 Hz, Q4 equal 1704,33 Hz, Q5 equal 2386,82 Hz, dan Q6 equal 2770,94 Hz.

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