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 364 Documents
 5   6   7   8   9 
Design Optimization of A Conventional Rocket Nozzle Using Coupled Thermo-Structural Analysis Saputra, M. Dito; Andria, Novi
Indonesian Journal of Aerospace Vol. 19 No. 2 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3570

Abstract

Thrust in a rocket is gained by expelling the combustion gas through a nozzle.  This rocket nozzle is a vital component during the conversion of chemical energy into kinetic energy. Consequently, it is exposed to extreme temperature and pressure resulted from gas combustion. Therefore to ensure a successful rocket operation, the nozzle must be able to maintain structural integrity when exposed to such environment. On the other hand, its structural weight must be kept minimum to reduce the overall weight of the rocket. Due to these circumstances, the nozzle design phase is very important since the nozzle significantly affects the whole rocket performance. LAPAN is currently developing some solid propellant based rocket. Each rocket’s nozzle is still designed using conventional configuration, consisting of a metal case and graphite insert. The nozzle relies on a thick structure geometry to maintain structural integrity. This approach induces a heavy-weight nozzle that burdens the rocket performance. This paper is attempted to optimize LAPAN’s conventional solid rocket nozzle design. A series of procedures are proposed to generate a lighter nozzle design. RX-450 rocket’s nozzle will be used as the studied model in this paper. Coupled thermo-structural analysis forms the main procedure to evaluate the proposed nozzle geometry structural integrity. The study succesfully provided an optimized nozzle geometry with sufficient strength and reduced weight.
Effect of Hybridization on Tensile, Shear and Compressive Properties of Carbon Based Fiber Reinforced Composites Abdurohman, Kosim; Adhitya, Mohammad
Indonesian Journal of Aerospace Vol. 19 No. 2 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3575

Abstract

The high specific stiffness and strength of composites make them widely used  in defence, marine, and aerospace applications. Hybrid composites have increased use in high-tech applications. The glass/carbon and KC/carbon hybrid composites manufactured by vacuum assisted resin infusion methods are used in this study. The matrix used for both composites are vinylester resin. The glass/carbon and KC/carbon hybrid laminates arrangement is [G/C/G2/C/G2/C]s and [(KC)2/C3]s, respectively. The mechanical properties are evaluated according to ASTM standards. Fracture micrograph analysis are investigated using SEM. The comparison of mechanical properties and surface fracture of both hybrid composites have been investigated. The tensile and compressive strength of KC/carbon are higher than glass/carbon hybrid composites. However, the shear strength of KC/carbon is lower than glass/carbon hybrid composites. SEM micrograph exhibits that the KC/carbon has a good fiber/matrix and interlayer bond better than glass/carbon hybrid composites.
Integrated Quality Analysis Method of Aluminum for Composite Propellant Production Sitompul, H. R.; Wibowo, H. B.; Abdillah, L. H.; Ardianingsih, R.; Restasari, A.; Budi, R. S.; Hartaya, K.; Baiquni, M.
Indonesian Journal of Aerospace Vol. 19 No. 2 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3655

Abstract

Quality analysis of Aluminum powder for solid fuel composite propellant was carried out to determine the critical parameters of the composite propellant characteristics. Two types of aluminum were analyzed for quality, including bulk density and true density using the Archimedes principle, particle shape, and size using SEM (Scanning Electron Microscope), crystallinity, and purity using XRD (Xray Diffraction), particle area with BET (Brunnauer-Emmet-Teller) and BJH (Barret-Joyner-Halenda) adsorption isotherm. To test the composite propellant made with 87.5% solid content and 18% AL content, then tested the characteristics of the propellant. The results of the analysis of the quality of aluminum for composite propellant raw materials have a very large influence on the quality of the resulting propellant, so an integrated, quick, and efficient quality analysis is needed. The critical parameters of Aluminum quality as propellant fuel are density, purity, particle shape and size, porosity/surface area, and crystallinity. Fast and efficient integrated analysis can be performed using new instruments, such as shape and size analysis with SEM, purity and crystallinity analysis with XRD, density analysis with a densitometer. AL2 which have smaller particle size, better density and shape parameters value, less pores and surface area than AL1, can be used to produce a higher quality composite propellant.
Structure Relaxation Disruption on Temperature-dependence of Polymerization of HTPB-based Polyurethane Restasari, Afni; Hamid, Nur; Marpaung, Leonard; Rusnaenah, Andi; Sukma, Adi; Sukma, Rahmawati
Indonesian Journal of Aerospace Vol. 19 No. 2 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3654

Abstract

The temperature-dependence of polymerization rate of hydroxyl-terminated polybutadiene (HTPB)-based polyurethane can be disrupted by a structure relaxation of polymer. Objective of the study is to investigate the disruption on the polyurethane (PU) formed of various molecular weight of HTPB. The study was carried out by applying temperature of 50, 60 and 70 oC in measuring viscosity until 80 minutes of reaction. The sample that were used is HTPB with various molecular weight and Toluene diisocyanate (TDI). Based on decreasing value of viscosity, it is obtained that relaxation temperature of HTPB-based PU is around 60 – 70 oC. By applying Eyring equation of flow, it is found that relaxation of structure causes the existence of relaxation dominant-time (RDT). RDT is the reaction time at which molar volume reaches the maximum value. Furthermore, by determining activation entropy, the RDT was revealed to be a borderline between two type of polymerization. Linear reaction occurs before RDT, while cross-link reaction occurs after RDT. From structure point of view, PU-polymerization type of HTPB with low molecular weight tend to be more sensitive towards structure relaxation which is originated from hard segment.
Study on The Development of Guidance System Technology for 122-140 mm Artillery Rocket Nugroho, Widianto; Riyadl, Ahmad; Muslimin, Ahmad Novi; Setiawan, Rudi; Triharjanto, Robertus Heru; Yogaswara, Y. H.
Indonesian Journal of Aerospace Vol. 19 No. 2 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3691

Abstract

The increase in rocket Artillery accuracy means there will be fewer rockets to be used to destroy a target. This could reduce the needed budget and risk of weapon mobilization. Therefore, this research investigates the advancement in the guidance system technology for Artillery rockets, especially for 122-140 mm caliber. The objective of the research is to find a direction for the development guidance system for the Indonesian Artillery rocket (RHAN). The research use the descriptive-analytic method, in which data was collected from literature studies and inductive analysis was performed. The data shows two kinds of actuators were used, a canard and thrusters. In canard mode, 2 strategies were used, i.e. with bearing to isolate the roll from the rocket, in which 5 control algorithms were used, and without bearing, which 2 control algorithms were used. In thruster mode, there was 5 control algorithms used. Further analysis shows that the best performance is obtained from 2 modes of the canard strategy with bearing, and 2 modes of the thruster strategy. Therefore, it is concluded that the 4 modes can be used to be implemented in RHAN which needs to be added to the control system.
Numerical Investigation of Supersonic and Hypersonic Shock-Wave/Boundary-Layer Interactions Bura, Romie Oktovianus; Graham T. Roberts; Yufeng Yao; Neil D. Sandham
Indonesian Journal of Aerospace Vol. 23 No. 1 (2025): Indonesian Journal Of Aerospace
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.55981/ijoa.2025.12201

Abstract

Numerical simulations of 2-D supersonic and hypersonic laminar Shock-Wave/Boundary-Layer Interactions (SBLIs) were carried out by solving the Navier-Stokes (NS)equations using a compressible flow code over a wide range of Mach numbers and shockstrengths. The results obtained at Mach 2.0 and 7.73 were compared with experimentaldata. In addition, the numerical data were further analyzed using correlation laws derivedby previous researchers based on the free interaction concept, extended here to higherMach numbers. The results indicate that this concept is valid for separated laminar hypersonicflows with SBLIs. For interference heating, the correlation technique based on thewell-established power law relationship between peak heating and peak pressures yieldedencouraging results consistent with other correlations for laminar interference heating athypersonic speeds.
The Effect of Payload Weight to Mean Coil Diameter of Helical Compression Spring for Payload Separation Laksono , Shandi Prio
Indonesian Journal of Aerospace Vol. 19 No. 2 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3565

Abstract

Weight is one of major factors in sounding rocket or launch vehicle design. Indeed, payload weight contributes to the rocket weight. Sounding rocket release the payload in the upper atmosphere at the certain altitude. Sounding rocket is intended to carry the payload as much as possible. In payload jettison/separation system, helical compression spring is commonly used. The previous study result show that in order to avoid mechanical failure of the spring, if the payload weight was 60 kg, the minimum wire diameter of helical compression spring must be 8 mm with mean coil diameter of 80-96 mm. Based on the previous study result, this study investigated the effect of payload weight to mean coil diameter of helical compression spring for payload separation. The numerical method was used in this study. In order to increase the payload weight, the mean coil diameter must be decreased. The results obtained show that the maximum payload weight that can be used was 77 kg with the maximum mean coil diameter of 80 mm, and free length of 0.417 m. In addition, safety factor of 1.65 and energy storing of 81.8 N.m was obtained.
Three-Dimensional (3D) Flight Planning Optimization Using Genetic Algorithm Considering FCOM Data Nugraha, Calvarico Bima; Ruseno, Neno
Indonesian Journal of Aerospace Vol. 19 No. 2 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3607

Abstract

Flight Planning is a document prepared by airline which consist of aircraft information, planned route, required fuel, carried load, weather forecast, etc. It needs to be submitted to ATC to get approval and then it will be used by pilot to guide the flight to reach the destination. Optimization in flight planning route is one of the essential factors in reducing fuel consumption to reduce cost and emission. The aim of this research is to optimize the flight planning route in Three-Dimensional approach using Genetic algorithm. Genetic algorithms (GA) are widely used in optimizations that includes many parameters, thus it could be used in flight planning optimization. The concept of GA is a heuristic search approach that inspired by Darwin’s theory of natural evolution which mimics “Survival of the fittestâ€. The method starts with a hexagon size containing nodes of possible points connecting departure and arrival airports. In this research the nodes are extracted using Dijkstra algorithm from previous research. The algorithm used population size of 500 individuals that generated with 0.01 mutation rate, 100 generation cycle, and 20 elite size. The case study covers routes in area of Indonesia which are flights of Jakarta – Tanjung Pinang, Jakarta – Makassar, and Jakarta – Manado. The different aircraft gross weights are analyzed to study the effect of aircraft weight to the resulted flight route. The aircraft performance database from Flight Crew Operating Manual (FCOM) of A320 aircraft was used to calculate the fuel burn. It is concluded that the algorithm able to find the optimal flight route as the best individual with range of cruise altitude from 35,000 to 39,000 ft. Results from Jakarta - Tanjung Pinang showed an average of fuel reduction of around 2.29% followed by Jakarta - Makassar with 13.28% and Jakarta - Manado with 15.68%. Although, the resulted altitude profile shows a fluctuation in the middle of route, in average it is a climb.
Full Pages JTD Vol 19 No.2 December 2021 Tekgan, Editorial Jurnal
Indonesian Journal of Aerospace Vol. 19 No. 2 (2021)
Publisher : BRIN Publishing

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

Abstract

-
Front Pages JTD Vol 17 No.1 Juni 2019 Jurnal, Redaksi
Indonesian Journal of Aerospace Vol. 17 No. 1 Juni (2019): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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

Abstract

-

Page 7 of 37 | Total Record : 364

 5   6   7   8   9 

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