Article Per Year (5 Year)
p-Index From 2020 - 2025
0.408
P-Index
This Author published in this journals
All Journal Jurnal Teknologi Dirgantara Rekayasa Mekanika: Jurnal Ilmiah Teknik Mesin
Yulia Azatil Ismah
Unknown Affiliation
Aerospace Engineering Chemical Engineering, Chemistry & Bioengineering Computer Science & IT Control & Systems Engineering Energy Industrial & Manufacturing Engineering Materials Science & Nanotechnology Mechanical Engineering Physics

Published : 2 Documents Claim Missing Document
Claim Missing Document
Check
Articles

Found 2 Documents
Search

 1 
DEKOMPOSISI TERMAL PROPELAN KOMPOSIT BERBASIS AMONIUM PERKLORAT/HYDROXY TERMINATED POLYBUTADIENE (AP/HTPB) (THE THERMAL DECOMPOSITION ANALYSIS OF AMMONIUM PERCHLORATE/HYDROXYTERMINATED POLYBUTADIENE (AP/HTPB) COMPOSITE SOLID PROPELLANT) Wiwiek Utami Dewi; Yulia Azatil Ismah
Jurnal Teknologi Dirgantara Vol. 14 No. 1 Juni 2016
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2016.v14.a2944

Abstract

Thermal decomposition process of AP/HTPB solid propellant type RUM, 450 and 1220 were investigated by DTG60 (Differential Thermogravimetric) with operational parameters: temperature 30 – 400oC, nitrogen flow rate 50 ml/min, and heating rate 2.5 C/min. Thermal decomposition analysis will be the first step of decomposition kinetics research in determining life time of the propellant. TGA curve of propellant RUM was found to be two staged meanwhile the thermal decomposition of propellant 450 and 1220 has become one staged. The DTA curve/thermogram of propellant RUM show the formation of intermediate product before full-length decomposition. Unlike propellant RUM, DTA curves of propellant 450 and 1220 do not show the formation of intermediate product. Decomposition process of propellant 450 and 1220 accelerate by Al presence. The difference between AP modal on propellant 450 and 1220 show insignificance effect to the amount of decomposition energy consumption. ABSTRAKProses dekomposisi termal propelan padat AP/HTPB jenis RUM, 450 dan 1220 telah dianalisis menggunakan Differential Thermogravimetric 60 (DTG) dengan parameter operasi: suhu 30 - 400⁰C, atmosfer nitrogen berlaju alir 50 ml/menit, dan laju pemanasan 2,5⁰C/menit. Analisis dekomposisi termal adalah langkah awal penelitian kinetika dekomposisi propelan dalam menentukan life time propelan. Kurva TGA menunjukkan bahwa propelan RUM mengalami proses dekomposisi dua tahap sedangkan propelan 450 dan 1220 mengalami proses dekomposisi satu tahap. Kurva DTA/ termogram proses dekomposisi propelan RUM menunjukkan adanya pembentukan produk intermediate sebelum akhirnya terdekomposisi sempurna. Berbeda dengan propelan RUM, termogram propelan 450 dan 1220 tidak menunjukkan terbentuknya produk intermediate. Proses dekomposisi propelan 450 dan 1220 terakselerasi oleh keberadaan Al. Perbedaan modal AP pada propelan 450 dan 1220 ternyata tidak begitu berpengaruh pada nilai konsumsi energi proses dekomposisi.
DESAIN DASAR MESIN INJECTION MOLDING UNTUK PROSES CASTING SAMPEL PROPELAN PADAT MENGGUNAKAN SOFTWARE SOLIDWORKS Febriyanto, Ady; Supardi, Nurul Iman; Yulia Azatil Ismah
Rekayasa Mekanika: Jurnal Ilmiah Teknik Mesin Vol. 9 No. 1 (2025): April 2025
Publisher : UNIB Press

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.33369/rekayasamekanika.v9i1.38986

Abstract

The injection molding machine for the solid propellant sample casting process is a tool for making a sample in the form of a solid propellant sample plate, this tool is designed to make work easier when carrying out the process of making solid propellant samples. The needs of the propellant industry in Indonesia are very large and important considering the need to develop solid propellant samples and munitions for the national arsenal, namely to promote and facilitate the exchange of technical information and programs. itself consists of two molds with sizes, namely 25cm diameter, 10cm high and 17cm diameter, 5cm high, frame, cember, hydraulic. The most important component in solid propellant sample injection molding is the solid propellant sample mold. Therefore, it must be strong and sturdy to hold the solid propellant sample so that it does not come out during printing with hydraulic pressure.The manufacture of solid propellant injection molding was assisted with Solidwork Software in this research.Keyword: Rocket, Propellant, injection molding.
Co-Authors Febriyanto, Ady Nurul Iman Supardi Wiwiek Utami Dewi