cover
Article Per Year (5 Year)
All
Home Page
OAI Link
Editorial Team
Contact
Reviewer
Google Scholar
Contact Name
Andri Agus Rahman
Contact Email
jurnal@brin.go.id
Phone
+6281239910372
Journal Mail Official
ijoa@brin.go.id
Editorial Address
Kawasan Sains dan Teknologi (KST) Bacharuddin Jusuf Habibie, Jl. Raya Puspiptek 60, Tangerang Selatan 15310
Location
Kota bogor,
Jawa barat
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
 22   23   24   25   26 
SIMULASI GERAK DAN ANALISIS KESTABILAN KOPLING INERSIA WAHANA DIRGANTARA DENGAN BENTUK BADAN RAMPING Muhammad, Hari; Samputra, Hilman; Jenie, Yazdi I; Sembiring, Javensius
Indonesian Journal of Aerospace Vol. 9 No. 1 Juni (2011): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

Inertia coupling is a motion phenomenon of a high-speed airplane having slender body and low aspect ratio. This inertia coupling happens when the aircraft performs a roll manoeuvre motion with a high roll rate. This paper will discuss the derivation of inertia coupling equations of motion, modelling equations of motion in the Matlab/Simulink software, simulating the dynamics motion, and analyzing the stability of the inertia coupling. Numerical simulation and stability analysis of the inertia coupling for a fighter aircraft will be presented in this paper.
PENGEMBANGAN METODE PENENTUAN KARAKTERISTIK RANCANGAN AWAL ROTOR TURBIN ANGIN Atmadi, Sulistyo; Fitroh, Ahmad Jamaludin
Indonesian Journal of Aerospace Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

A method for determining design characteristics of a wind turbine rotor has been developed. Given the desired power and operational wind speed, the approximate design diameter and rotor rpm can then be determined. The size of the rotor diameter is governed by the blade performance, in which is normally given as power coefficient Cp; designed rotor spedd can be known after calculating the tip spedd ratio. Using this method, the blade and rotor characteristics can be designed quickly as a preliminary design parameter. Keywords: Rancangan awal, Koefisien daya, Tip speed ratio.
Front Page JTD Vol. 13 No. 1 Juni 2015 Jurnal, Redaksi
Indonesian Journal of Aerospace Vol. 13 No. 1 Juni (2015): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

-
SIMULASI PENGGUNAAN DIFFUSER PADA TURBIN ANGIN SUMBU HORISONTAL UNTUK KENAIKAN DAYA Atmadi, Sulistyo; Fitroh, Ahmad Jamaludin
Indonesian Journal of Aerospace Vol. 9 No. 1 Juni (2011): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

One technique to improve the power output of a wind turbine is by implementing a diffuser, which is called the diffuser augmented wind turbine (DAWT). The area ratio between the inlet and outlet of the diffuser increases the flow rate inside the diffuser which in effect produces higher output power. In this research, a 2 meters rotor diameter was used. Diffuser diameter ratio variation of 2, 3, 4, and 5 were chosen which provides inlet diameter of 4, 6, 8, and 10 meter respectively. Power rotor coefficient is assumed to be constant of 0.30. Air speed distribution inside the diffuser is calculated using CFD method. The inlet speed to the diffuser is varied to give 4 different speeds. The wind angle at the inlet is also varied at 0º, 30º and 60º. The simulation result showed that at 0 degree angle, diffuser diameter ratio variation of 2, 3, 4, and 5 will increase the power output about 58, 622, 3169, and 11519 times respectively. It also showed that the increase in the output power for diameter diffuser ratio of 2 at 0º and 60º angle is 58 and 4 times respectively.
ANALISIS DESAIN, TEKNOLOGI DAN PRESTASI TURBIN ANGIN 10 KW Ginting, Dines
Indonesian Journal of Aerospace Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

Small-scale wind energy conversion systems have been developed and utilized for rural electric generation. Performance and success of the systems strongly depend on available wind power as well as the design and technologies. Recently, that alternative energy technology is more important to support the electric supply and to anticipate continously increase of electric needs. In order to increase the use of that renewable energy technology, a 10 kW wind turbine has been chosen to be developed. Analysis of the wind turbine shows that the design, technologies, and performances are specific and limited to the application and wind power availability. The adaption and improvement is needed for developing the more effective use to the wind turbine. Keywords: Wind energy, energy terbarukan, Turbine angin.
PEMBENTUKAN STRUKTUR MIKRO DAN SIFAT MAGNETIK Sm2Co17 MELALUI CARA SINTERING Siahaan, Mabe
Indonesian Journal of Aerospace Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

The studies, observation of microstructure and magnetic coercivity of the permanent magnet sample have been done through a metallurgy powders technique preparation process. The raw materials with the composition of Sm (Co, Cu, Fe, Zr)z equal 8.5 (at percent) initially in the form of powders alloys with the mean particle size of was 20-30 um. This powder is compacted through one direction pressed in the dies and the following with heat treatment steps. After sintering steps and homogeneity of each at a temperatures of 1190 degree celcius and 1130 degree celcius, the solid sample achieved with Sm2Co17 is mainly the magnetics phase. Further heat treatment that their received the next 10 degree celcius/minute until room temperature. And have succeeded to form cellular structures on the matrixs of magnetics phases while other phases in the form cellular structures on the matrixs of magnetics phases while other phases in the form of grain boundary and the magnetics coercivity. Conclution from result of this study is compared with the result of former research.
ANALISIS LOSSES PIPA LURUS BERDIAMETER 40 cm PADA TEROWONGAN ANGIN LAPAN Fitroh, Ahmad Jamaludin
Indonesian Journal of Aerospace Vol. 9 No. 1 Juni (2011): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

One of LAPAN’s programs is design and build the ramjet open tested wind tunnel. The lenght of pipe connecting between wind tunnel and storage tank was designed long enough so it was estimated there is big losses along the pipe. The object of this research is to calculation that losses, specially for the straight part only. The magnitude of the losses was gotten from simulation using software based on CFD theory. This research used two methods, i.e. based on pressure method and based on mass flow rate method. The simulation’s result using based on mass flow rate method gave the higher losses for the straight pipe so that result was chosen as the final result. That result was processed become the losses as a function of mass flow rate. The higher mass flow rate will produce the bigger losses. At mass flow rate of 60 kg/s, the losses is 0.135 %/m and at 100 kg/s the losses is 0.299 %/m. The relation between both parameter is close to linier curve.
DESAIN DAN PENGUJIAN INTAKE KONIKAL SISTEM PROPULSI RAMJET PADA KECEPATAN SUPERSONIK (DESIGN AND TEST OF CONICAL INTAKE OF RAMJET PROPULSION SYSTEM AT SUPERSONIC SPEED) Sofyan, Sofyan; Bura, Romie Oktovianus
Indonesian Journal of Aerospace Vol. 13 No. 1 Juni (2015): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

Riset ini bertujuan untuk mendesain intake supersonik untuk aplikasi sistem propulsi ramjet. Desain intake ramjet sangat penting bagi proses pembakaran dalam ruang bakar mesin ramjet. Dalam desain intake konikal ini, kondisi Mach 2 dijadikan sebagai acuan, dengan kompresi eksternal. Penelitian ini juga menguji intake ramjet dalam terowongan angin supersonik. Desain dilakukan dengan menempatkan gelombang kejut pada bibir cowl intake untuk memperoleh pressure recovery yang tinggi dan gaya hambat serendah mungkin. Hasil desain analitik dibandingkan dengan hasil numerik pada berbagai kondisi intake – subkritikal, kritikal, dan superkritikal. Hasil numerik juga divalidasi dengan eksperimen model. Intake yang didesain memberi pressure recovery sebesar 0,93, namun hasil ini cukup berbeda dengan hasil eksperimental. Ini disebabkan karena efisiensi kompresi tidak diikutkan dalam proses desain.
ANALISA AERODINAMIKA KENDALI CANARD ROKET RKX 250 Ginting, Salam
Indonesian Journal of Aerospace Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

In the framework of guided missile development in LAPAN, Center of Technology has been rocket designed, constructed and then performed a guided missile trial launching in Pameungpeuk in May 2002. However the result was still far from expectation. It has been realized that numerous of factors played a part in the failure of the missile trial launching, which are structure strenght, propulsion, propellant, guidance system and aerodynamic stability. From all the above factors, aerodynamic static stability is the initial requirement which has to be validated before stepping to the next design process. Based on the above situation, it has been carried out a analysis un RKX 250 rocket aerodynamic static stability with canard guidance which configuration is almost similiar with the one that was launched in Pameungpeuk. To find out the rocket's aerodynamic static stability, a research on lift coefficient and drag coefficient must be done first. From the lift coefficient data, a conduction the center pressure of aerodynamics rocket. Method that is used in this research is the ine which was developed by quadrature multhopp which is analytical method (Krasnov N.F.1978).
ESTIMASI BIAYA DAUR HIDUP DAN OPTIMISASI HARGA PESAWAT TERBANG Zain, Rais; Ahyarsi, Odi
Indonesian Journal of Aerospace Vol. 9 No. 1 Juni (2011): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

Since the conceptual design phase, the estimate of airplane life cycle cost (LCC) is carried out to support a decision making process. The LCC consist of research, development, testing, and evaluation cost, where an airplane estimated price (AEP) is a part of this calculation. Furthermore, AEP is employed as a non linear objective funtion for developing a constrained optimization algorthm. Rosen’s gradient projection is applyed in the development of computer program named Cost Analysis implementing object oriented approach on Microsoft Visual C++ 6.0. In order to verify the application, some data of Ourania jet airplane were utilized for carrying out a case study. The result of Cost Analysis shows that the estimated LCC are similar to the reference. Also, the optimization problems can be solved by Rosen’s algorithm less than ten iterations.

Page 24 of 37 | Total Record : 365

 22   23   24   25   26 

Filter by Year

2003 2025


Reset
Filter By Issues
All Issue Vol. 23 No. 1 (2025): Indonesian Journal Of Aerospace Vol. 22 No. 2 (2024): Indonesian Journal Of Aerospace Vol. 22 No. 1 (2024): Indonesian Journal Of Aerospace Vol. 21 No. 2 (2023): Indonesian Journal Of Aerospace Vol. 21 No. 1 (2023): Indonesian Journal of Aerospace Vol. 20 No. 2 (2022): Jurnal Teknologi Dirgantara Vol. 20 No. 1 (2022): Jurnal Teknologi Dirgantara Vol. 19 No. 2 (2021) Vol. 19 No. 1 (2021) Vol. 18 No. 2 Desember (2020): Jurnal Teknologi Dirgantara Vol. 18 No. 1 Juni (2020): Jurnal Teknologi Dirgantara Vol. 17 No. 2 Desember (2019): Jurnal Teknologi Dirgantara Vol. 17 No. 1 Juni (2019): Jurnal Teknologi Dirgantara Vol. 16 No. 2 Desember (2018): Jurnal Teknologi Dirgantara Vol. 16 No. 1 Juni (2018): Jurnal Teknologi Dirgantara Vol. 15 No. 2 Desember (2017): Jurnal Teknologi Dirgantara Vol. 15 No. 1 Juni (2017): Jurnal Teknologi Dirgantara Vol. 14 No. 2 Desember (2016): Jurnal Teknologi Dirgantara Vol. 14 No. 1 Juni (2016): Jurnal Teknologi Dirgantara Vol. 13 No. 2 Desember (2015): Jurnal Teknologi Dirgantara Vol. 13 No. 1 Juni (2015): Jurnal Teknologi Dirgantara Vol. 12 No. 2 Desember (2014): Jurnal Teknologi Dirgantara Vol. 12 No. 1 Juni (2014): Jurnal Teknologi Dirgantara Vol. 11 No. 2 Desember (2013): Jurnal Teknologi Dirgantara Vol. 11 No. 1 Juni (2013): Jurnal Teknologi Dirgantara Vol. 10 No. 2 Desember (2012): Jurnal Teknologi Dirgantara Vol. 10 No. 1 Juni (2012): Jurnal Teknologi Dirgantara Vol. 9 No. 2 Desember (2011): Jurnal Teknologi Dirgantara Vol. 9 No. 1 Juni (2011): Jurnal Teknologi Dirgantara Vol. 8 No. 2 Desember (2010): Jurnal Teknologi Dirgantara Vol. 8 No. 1 Juni (2010): Jurnal Teknologi Dirgantara Vol. 7 No. 2 (2009): Jurnal Teknologi Dirgantara Vol. 7 No. 1 Juni (2009): Jurnal Teknologi Dirgantara Vol. 6 No. 2 (2008): Jurnal Teknologi Dirgantara Vol. 6 No. 1 (2008): Jurnal Teknologi Dirgantara Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007) Vol. 5 No. 2 (2007): Jurnal Teknologi Dirgantara Vol. 4 No. 2 (2006): Jurnal Teknologi Dirgantara Vol. 4 No. 1 (2006): Jurnal Teknologi Dirgantara Vol. 3 No. 2 (2005): Jurnal Teknologi Dirgantara Vol. 2 No. 2 (2004): Jurnal Teknologi Dirgantara Vol. 2 No. 1 (2004): Jurnal Teknologi Dirgantara Vol. 1 No. 2 Desember (2003): Jurnal Teknologi Dirgantara Vol. 1 No. 1 (2003): Jurnal Teknologi Dirgantara More Issue