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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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PENGEMBANGAN POLIURETAN BERBASIS CPO SEBAGAI LINER ADHESIVE Heri BW,; Henny S; Geni R
Indonesian Journal of Aerospace Vol. 1 No. 1 (2003): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

In effort to increase the economic value of CPO (Crude Palm Oil), a research to use it as polyurethane raw material for the liner adhesive has been conducted. In order to get monoglyceride, CPO is glycerolized with glycerol, KOH is used as a catalyst and Pyridine solvent at 105 degree C for 4-8 hours. In the presence of isocyanate, such as TDI (Toluen Diisocyanate) monoglyceride as a diol becomes Polyurethane. Based on the adhesive strength test, this polyurethane polymer, produce a low conductivity and heat resistance up to 400 degree C(better quality compared with polyurethane to be used available in the local market). Therefore the polyurethane with CPO base a good potential material as a liner adhesive.
OPTIMASI PEMANFAATAN SISTEM PEMOMPAAN TENAGA ANGIN(SPTA) UNTUK SUMBER-SUMBER AIR DALAM DENGAN TURBIN ANGIN LISTRIK SUDU MAJEMUK SEBAGAI PENGGERAK POMPA Pakpahan, Sahat; Soeripno
Indonesian Journal of Aerospace Vol. 1 No. 1 (2003): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

The application of WInd Energy Conversion Systems (WECS) for supplying water for households, irrigation, livestock or other purposes have been developed to increase the contribution of renewable source of energy to support people, particularly at locations where accessibility to public utility networks not available or when the system itself needed by the consumer. Various WECS available in market as well as commercial pumps which can be used for bored hole., deep well or surface water and must be matched for optimal performance of the whole system; therefore, the analysis for selection of a pump due to its design characteristics for matching with an existing wind turbine that result-in optimal conditions of supply and demand has to be performed. A wind turbine with 6 blades rotor installed at BBUG samas Bantul is taken as a case study.
PREDIKSI TRAYEKTOR WAKTU-NYATA ROKET BALISTIK DENGAN MENGGUNAKAN GPS Widada, Wahyu
Indonesian Journal of Aerospace Vol. 1 No. 1 (2003): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

This paper described the real-time prediction of the trajectory of a balistic rocket based on gps data. The method was used a parabolic motion under the assumption of a constant gravitational acceleration. The algorithm was successfully applied to GPS flight data of a RX150 rocket launched at Pameungpeuk, Jawa Barat
RANCANGAN KAPAL UDARA (AIRSHIP) UNTUK VIDEO MONITORING DARI UDARA Sugiarmadji HPS; Robertus Heru T; Setiadi; Ediwan
Indonesian Journal of Aerospace Vol. 1 No. 1 (2003): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Remotely controlled non rigid helium airship type is chosen in airship design criteria for video monitoring. The design consists of airship dimensions and volume determination, maximum take of weight (MTOW) and W (weight empty plus payload) calculations, weight and structures analysis, airship stabilization analysis, airship guidance system, power plant system, position monitoring system, material and process, and payload systems. Here, Helium gas will be filled for generating a lift that is equal to the weight of the displaced air. An Airship Demonstrator Model LPN-01 is built to represent the design results. The model has length of L=8.5 m and 2.2 m diameter, so that the envelope volume is of 20 m. This Demonstrator Model will be used for studying capability or performance of airship, especially on ascent and descent manuever, airship's stability, position monitoring and payloads.
AKTIVASI LITIUM SEBAGAI KATALISATOR PADA REAKSI PEMBENTUKAN HTPB Wibowo, Heri Budi; Rosita, Geni
Indonesian Journal of Aerospace Vol. 2 No. 2 (2004): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2004.v2.a804

Abstract

HTPB usually used as propellant fuel binder. This paper studied anionic polymerization of butadiene to form HTPB (Hydroxy Terminated Polybutadiene) with litium as catalyst. In practice, litium must be reactivated to remove antioxidant that surround it. Butadiene is polymerized in a 250 mL autoklave at room temperature and free oxygen. Litium was reactivated by melting and deforming. The polymer form was terminated by ethylene oxide to form HTPB. After it was washed by benzene and aquadest, HTPB structure was analyzed with FTIR at 910 cm and 970 cm. Investigation of the polymerization could produced HTPB if litium as catalyst was reactivated. HTPB resulted contain maximum 30 percent structure cis-1,4 HTPB. The average molecule weight can be control very well based on amount of litium (catalyst).
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.

Page 35 of 37 | Total Record : 364

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