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Riyadl, Ahmad
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Aerospace Engineering Astronomy Automotive Engineering Chemical Engineering, Chemistry & Bioengineering Control & Systems Engineering Energy Engineering

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PENGARUH KETIDAKPASTIAN NILAI PARAMETER TERBANG TERHADAP TITIK JATUH ROKET R-HAN 300 Riyadl, Ahmad; Triharjanto, Robertus Heru; Widodo, Pujo
ELEMEN : JURNAL TEKNIK MESIN Vol. 10 No. 1 (2023)
Publisher : POLITALA PRESS

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.34128/je.v10i1.226

Abstract

The impact point is the main parameter of the performance of an artillery rocket. During its flight, a rocket experiences uncertainty of some parameter’s value, which is caused by the condition of the rocket when it exits the launcher, the ever-changing atmospheric conditions, and fabrication imperfections. This disturbance will cause deviation on the impact point. This study aims to determine the deviation of the impact point of an artillery rocket due to the value uncertainty of several parameters that affect its flight trajectory, and this analysis will be used as a reference for designers and users in further design processes. Six degrees of freedom simulation calculates the rocket's impact point and deviation. The results showed that to minimize the impact point’s deviation, the quality of the launcher fabrication must be improved, predicting aerodynamics with CFD and firing the rocket at low wind disturbances.
PENGARUH KETIDAKPASTIAN NILAI PARAMETER TERBANG TERHADAP TITIK JATUH ROKET R-HAN 300 Riyadl, Ahmad; Triharjanto, Robertus Heru; Widodo, Pujo
ELEMEN : JURNAL TEKNIK MESIN Vol. 10 No. 1 (2023)
Publisher : POLITALA PRESS

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.34128/je.v10i1.226

Abstract

The impact point is the main parameter of the performance of an artillery rocket. During its flight, a rocket experiences uncertainty of some parameter’s value, which is caused by the condition of the rocket when it exits the launcher, the ever-changing atmospheric conditions, and fabrication imperfections. This disturbance will cause deviation on the impact point. This study aims to determine the deviation of the impact point of an artillery rocket due to the value uncertainty of several parameters that affect its flight trajectory, and this analysis will be used as a reference for designers and users in further design processes. Six degrees of freedom simulation calculates the rocket's impact point and deviation. The results showed that to minimize the impact point’s deviation, the quality of the launcher fabrication must be improved, predicting aerodynamics with CFD and firing the rocket at low wind disturbances.
Impact Point Dispersion Prediction for 300 mm R-Han 300 Artillery Rocket Riyadl, Ahmad; Robertus Heru TriHarjanto; Pujo Widodo
Indonesian Journal of Aerospace Vol. 21 No. 1 (2023): Indonesian Journal of Aerospace
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.55981/ijoa.2023.27

Abstract

The effectiveness of artillery rocket in battlefield is the determined by its impact point dispersion, which may occur due to manufacturing and measurement inaccuracy, initial launch perturbations and atmospheric conditions. Therefore, the objective of this study is to establish model that could predict the impact point dispersion of R-Han 300 rocket using Monte Carlo method. Generic rocket of 6 Degree-of-Freedom model was implemented to investigate the impact point. Initially two simulations with 1000 iterations were carried out, first to study the effect of value uncertainty of every parameter on the impact point dispersion at launch elevation angle 50 degrees, second to study the impact point dispersion caused by value uncertainty of all the parameters at launch elevation angles ranging from 30 to 70 degrees. The second simulation is then repeated with 10000 iterations. This study showed that the dispersion increases as the launch elevation angle increases, except around the optimal launch elevation angle that give the farthest range. Monte Carlo simulation with 10000 iterations showed a better normal distributed data then the simulation with 1000 iterations, but the maximum difference in value of CEP resulted from both simulations is very small, which is 3.16%.
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.
PENGATURAN SUDUT AZIMUTH ROKET RUM UNTUK OPERASI PELUNCURAN PADA KECEPATAN ANGIN DI ATAS 10 KNOT (AZIMUTH ANGLE’S SETTING OF ROCKET RUM FOR LAUNCH OPERATION AT WIND SPEED MORE THAN 10 KNOT) Wibowo, Heri Budi; Riyadl, Ahmad; Nugroho, Yudha Agung
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.a2943

Abstract

RUM rocket is a rocket used in the payload competition among university students. The rocket is designed to bring a maximum payload of 1 kg to altitude of 600-1000 m and falls safely on a 500 m radius of the left and right rear of the center point of the launching pad of the conditions of wind speeds below 10 knots. In extreme circumstances where the wind speed is above 10 knots, the effect of speed and direction of wind to the stability of the rocket flight direction large enough to cause it to fall beyond the defined safety radius. The research aims to adjust azimuth setting of the rocket so that the fall of the rocket motor remains secure within the radius of the launch area. The study was conducted by testing a rocket RUM in extreme conditions (wind speed of 10-20 knots) with variations in shear-pin and azimuth angle. The test variables are the position of the fallen rocket motor. The results show that the wind direction and speed significantly affecting direction of rockets flight. The results show that rocket azimuth angle of 60 degrees with the direction of 90 degrees from the wind direction can make thea rocket falls on a secure area (within 500 m).
PENGARUH DARI POSISI PUSAT MASSA ROKET YANG TIDAK TERLETAK PADA SUMBU AXIS SIMETRI TERHADAP DINAMIKA TERBANG ROKET BALISTIK (THE DYNAMIC OF THE ROCKET DUE TO THE OFFSET OF ITS CENTER OF MASS RELATIVE TO THE SYMMETRIC AXIS) Riyadl, Ahmad
Indonesian Journal of Aerospace Vol. 13 No. 2 Desember (2015): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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

Abstract

Dalam uji terbang roket balistik kadang terjadi suatu gerakan wobbling yaitu suatu gerakan yang tidak linear menbentuk lintasan yang konus. Fenomena ini dapat terjadi dikarenakan berbagai sebab, dimana salah satu penyebabnya adalah posisi pusat massa roket yang tidak terletak pada sumbu axis simetri roket. Sehubungan roket LAPAN pada umumnya termasuk roket balistik maka perlu dilakukan penelitian untuk mengetahui kemungkinan dapat terjadinya gerakan wobbling pada saat uji terbang yang disebabkan oleh posisi pusat massa roket yang tidak terletak pada sumbu axis simetri. Dari hasil perhitungan pada penelitian ini terlihat bahwa posisi pusat massa roket yang tidak terletak pada sumbu axis simetri roket menyebabkan terjadinya gangguan momen roll, pitch dan yaw pada roket, dimana gangguan dari momen roll, pitch dan yaw tersebut memicu gerakan wobbling.
Co-Authors Heri Budi Wibowo Muslimin, Ahmad Novi Nugroho, Widianto Nugroho, Yudha Agung Pujo Widodo Pujo Widodo, Pujo Robertus Heru Triharjanto Rudi Setiawan Triharjanto, Robertus Heru Y. H. Yogaswara, Y. H.