Article Per Year (5 Year)
p-Index From 2021 - 2026
0.408
P-Index
This Author published in this journals
All Journal Rekayasa Mekanika: Jurnal Ilmiah Teknik Mesin Indonesian Journal of Aerospace
Ismah, Yulia Azatil
Unknown Affiliation
Aerospace Engineering Astronomy Control & Systems Engineering Energy Industrial & Manufacturing Engineering Materials Science & Nanotechnology Mechanical Engineering

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

Found 2 Documents
Search

 1 
DESAIN DAN SIMULASI KEGAGALAN STIK MANDRIL ROKET RX-100 PADA PROSES DECORING MENGGUNAKAN SOFTWARE SOLIDWORK Setiawan, Ahmad Yudi; Supardi, Nurul Iman; Ismah, Yulia Azatil
Rekayasa Mekanika: Jurnal Ilmiah Teknik Mesin Vol. 8 No. 2 (2024): Oktober 2024
Publisher : UNIB Press

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.33369/rekayasamekanika.v8i2.39390

Abstract

The substances used in rocket propellant have the ability to produce molecular gas at very high pressure and temperature during combustion. This material has great energy, and can explode so it is widely used in firearms, explosives and rockets. During the process of making rocket propellant, there is a process, namely the decorating process, which is the process of withdrawing the mandril stick from the propellant mold tube. The mandril stick is a component found at the end of the mandril itself, used as a link between the electric pulley and the mandril which is useful for pulling the mandril out of the mold tube, so that the propellant forms grains according to the mandril that has been printed in the propellant mold tube. The manufacture of mandril sticks is assisted by Solidwork software. In this research, a simulation was carried out on the mandril stick in order to determine the distribution of von Mises stress, displacement, and safety of factors on the RX-100 rocket mandril stick.
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) Dewi, Wiwiek Utami; Ismah, Yulia Azatil
Indonesian Journal of Aerospace Vol. 14 No. 1 Juni (2016): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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.
Co-Authors Dewi, Wiwiek Utami Nurul Iman Supardi Setiawan, Ahmad Yudi