Article Per Year (5 Year)
p-Index From 2020 - 2025
0.23
P-Index
This Author published in this journals
All Journal Mesin Indonesian Journal of Aerospace
Taufiq Mulyanto
Unknown Affiliation
Aerospace Engineering Astronomy Mechanical Engineering

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

Found 2 Documents
Search

 1 
RANCANG BANGUN MICRO AIR VEHICLE KONFIGURASI TAILLESS Taufiq Mulyanto; Arinta H Wijaya; Hari Muhammad
Mesin Vol. 23 No. 2 (2008)
Publisher : Mesin

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

Abstract

Nowadays, Micro Air Vehicle (MAV) is mostly developed for surveillance purpose, either for military or civilian. In this article, a design and building of a MAV will be presented. A tailless configuration was chosen. The design and build process started with a study of several design parameters of existing MAVs. Then, it is followed by initial sizing, detail design and production of the MAV. In general, the designed MAV could meet the design requirements and objectives stated. Some preliminary tests had shown that the basic flying characteristics was sufficiently good, although further development still has to be done. The design and build process was also able to evaluate the implementation of some aircraft design formula and method being implemented to design MAV.
Guidance and Control System Design of a Surface-to-Air Missile Based on 122 mm Rocket Yogaswara, Y. H.; Alvin Ardiansyah; Rianto Adhy Sasongko; Taufiq Mulyanto
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.2025.9041

Abstract

This paper applies and analyzes the design of a proportional navigation guidanceand control system for a 122 mm rocket platform. The research involves modeling missiledynamics, guidance systems, and control systems. The missile dynamics model relies onthe 6 DOF (Degrees of Freedom) equation for a rigid body, with aerodynamic data obtainedfrom the Missile Datcom program. The propulsion model is generated by a genericthrust profile of a 122 mm unguided rocket. The guidance system model is based on theproportional navigation guidance law, and the control system model employs the LinearQuadratic Regulator (LQR) method. Modeling is conducted using Simulink software, andsimulations encompass various scenarios. The analysis considers aspects such as missiletrajectory, acceleration command, actual acceleration, control surface deflection, and thetime required to hit the target. The simulation results indicate the missile’s capability tointercept targets under numerous conditions, although limitations are observed in specifictarget scenarios where interception is not achievable.
Co-Authors Alvin Ardiansyah Arinta H Wijaya Hari Muhammad Rianto Adhy Sasongko Y. H. Yogaswara, Y. H.