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Nonlinear Dynamic Modeling of a Fixed-Wing Unmanned Aerial Vehicle: a Case Study of Wulung Triputra, Fadjar Rahino; Trilaksono, Bambang Riyanto; Adiono, Trio; Sasongko, Rianto Adhy; Dahsyat, Mohamad
Journal of Mechatronics, Electrical Power and Vehicular Technology Vol 6, No 1 (2015)
Publisher : Research Centre for Electrical Power and Mechatronics, Indonesian Istitutes of Sciences

Developing a nonlinear adaptive control system for a fixed-wing unmanned aerial vehicle (UAV) requires a mathematical representation of the system dynamics analytically as a set of differential equations in the form of a strict-feedback systems. This paper presents a method for modeling a nonlinear flight dynamics of the fixed-wing UAV of BPPT Wulung in any conditions of the flight altitude and airspeed for the first step into designing a nonlinear adaptive controller. The model was formed into 10-DOF differential equations in the form of strict-feedback systems which separates the terms of elevator, aileron, rudder and throttle from the model. The model simulation results show the behavior of the flight dynamics of the Wulung UAV and also prove the compliance with the actual flight test results.

Nonlinear Dynamic Modeling of a Fixed-Wing Unmanned Aerial Vehicle: a Case Study of Wulung Fadjar Rahino Triputra; Bambang Riyanto Trilaksono; Trio Adiono; Rianto Adhy Sasongko; Mohamad Dahsyat
Journal of Mechatronics, Electrical Power and Vehicular Technology Vol 6, No 1 (2015)
Publisher : National Research and Innovation Agency

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.14203/j.mev.2015.v6.19-30

Developing a nonlinear adaptive control system for a fixed-wing unmanned aerial vehicle (UAV) requires a mathematical representation of the system dynamics analytically as a set of differential equations in the form of a strict-feedback systems. This paper presents a method for modeling a nonlinear flight dynamics of the fixed-wing UAV of BPPT Wulung in any conditions of the flight altitude and airspeed for the first step into designing a nonlinear adaptive controller. The model was formed into 10-DOF differential equations in the form of strict-feedback systems which separates the terms of elevator, aileron, rudder and throttle from the model. The model simulation results show the behavior of the flight dynamics of the Wulung UAV and also prove the compliance with the actual flight test results.

PENGEMBANGAN PERANGKAT LUNAK ANALISIS LINTAS TERBANG ROKET MULTI-STAGE (DEVELOPMENT OF TRAJECTORY ANALYSIS SOFTWARE FOR MULTI-STAGE ROCKET) Ridanto Eko Poetro; Yazdi I. Jenie; Rianto Adhy Sasongko; Satriya Utama
Jurnal Teknologi Dirgantara Vol 10 No.1 Juni 2012
Publisher : National Institute of Aeronautics and Space - LAPAN

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

This paper discusses the development of a computer software for simulating and analyzing flight trajectory of rocket systems. Many aspects may influence the trajectory, such as those related to the internal characteristic of the system, those representing external or environmental influence, and also the ones corresponding to the procedures of the launching and the operation during its flight. The software is developed based on the mathematical equations representing the balance of forces and moments occur during the flight of a rocket. Some conditions related to rocket internal characteristic variation, external perturbance, and flight procedure/operation are represented as parameters variations of the mathematical equations used for computing the rocket system attitude and movement variables. The software, developed using MATLAB/ SIMULINK application, is then used for simulating and analyzing the flight trajectory of a multi-stage rocket in some flight conditions. At this development stage, as the simulation results show, the software can perform its function quite well to compute the system variables during each of its flight phases and display the information required for further analysis. In future development, some validation tests still need to be accomplished for ensuring the accuracy and validity of the method used in this software. Keywords: Rocket, Flight Trajectory, Simulation

Design and Simulation of Air to Air Missile Homing System Rahmat Alfi Duhri; Rianto Adhy Sasongko; Yayom Dwi Laksmana
INSIST Vol 2, No 2 (2017)
Publisher : Universitas Lampung

This paper will talk about AIM 120 AMRAAM missile guidance for pursuing a moving target. The missile guidance system itself consists of missile dynamics, control system, seeker, and guidance methods. For general purpose, the missile dynamics approach will use non-linear equation of motions. The control surface that will be discussed follow the rule BTT (Bank-to-Turn) and control system that will be used is PID control system that widely used for control design. Lastly, the guidance method that will be studied here is proportional navigation and constant bearing course approach. The simulation will be conducted using MATLAB Simulink. The Simulink model consist of target dynamics, and guidance system. From the result of simulation, it will be shown that the missile can pursue its target quite well. Hence, the simulation system can be used well for preliminary design purpose.Keywords—Homing System, Control System, Proportional Navigation, Missile Dynamics, Seeker, Bank-to-Turn, Constant Bearing Course.

Design and Simulation of Air to Air Missile Homing System Duhri, Rahmat Alfi; Sasongko, Rianto Adhy; Laksmana, Yayom Dwi
International Series on Interdisciplinary Science and Technology Vol. 2 No. 2 (2017)
Publisher : Universitas Lampung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.23960/ins.v2i2.84

This paper will talk about AIM 120 AMRAAM missile guidance for pursuing a moving target. The missile guidance system itself consists of missile dynamics, control system, seeker, and guidance methods. For general purpose, the missile dynamics approach will use non-linear equation of motions. The control surface that will be discussed follow the rule BTT (Bank-to-Turn) and control system that will be used is PID control system that widely used for control design. Lastly, the guidance method that will be studied here is proportional navigation and constant bearing course approach. The simulation will be conducted using MATLAB Simulink. The Simulink model consist of target dynamics, and guidance system. From the result of simulation, it will be shown that the missile can pursue its target quite well. Hence, the simulation system can be used well for preliminary design purpose.Keywords—Homing System, Control System, Proportional Navigation, Missile Dynamics, Seeker, Bank-to-Turn, Constant Bearing Course.

Active Vibration Control of a Flexible Spacecraft Structure Agung, Rizqy; Kusni, Muhammad; Adhy Sasongko, Rianto; Eko Poetro, Ridanto; Gunawan, Leonardo; Akbar, Mahesa
International Journal of Aviation Science and Engineering - AVIA Vol. 6 No. 2: (December, 2024)
Publisher : FTMD Institut Teknologi Bandung

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In this paper, the spacecraft that evaluated has two motion mode, rigid body mode and flexible mode and it isoperated in low earth orbit. The rigid body mode is related to the attitude of spacecraft and flexible mode is relatedto vibration that occurs on the spacecraft structure. The vibration that occurs on the spacecraft structure may causeperformance degradation during operation. Hence, the active control vibration is applied to overcome the problemdue to the vibration phenomenon on spacecraft. The active control system was designed by using two methods,Pole-Placement Method and Linear Quadratic Regulator (LQR) Method, and those two methods are solved byusing numerical method. The result of Pole-Placement Method shows the vibration is reduce in less than 0.5 unitof time. Whereas, the most suitable control parameter input based on the LQR Method could reduce vibration inless than 8 unit of time. The LQR method provides more parameter variation; thus, the system could be controlledand adjusted due to its design requirement. Based on the LQR Method when the attenuation time is 8 unit of time,the energy required by the actuator is 84% less than that of the Pole-Placement Method.

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

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.

PENGEMBANGAN PERANGKAT LUNAK ANALISIS LINTAS TERBANG ROKET MULTI-STAGE (DEVELOPMENT OF TRAJECTORY ANALYSIS SOFTWARE FOR MULTI-STAGE ROCKET) Poetro, Ridanto Eko; Jenie, Yazdi I; Sasongko, Rianto Adhy; Utama , Satriya
Indonesian Journal of Aerospace Vol. 10 No. 1 Juni (2012): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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

This paper discusses the development of a computer software for simulating and analyzing flight trajectory of rocket systems. Many aspects may influence the trajectory, such as those related to the internal characteristic of the system, those representing external or environmental influence, and also the ones corresponding to the procedures of the launching and the operation during its flight. The software is developed based on the mathematical equations representing the balance of forces and moments occur during the flight of a rocket. Some conditions related to rocket internal characteristic variation, external perturbance, and flight procedure/operation are represented as parameters variations of the mathematical equations used for computing the rocket system attitude and movement variables. The software, developed using MATLAB/ SIMULINK application, is then used for simulating and analyzing the flight trajectory of a multi-stage rocket in some flight conditions. At this development stage, as the simulation results show, the software can perform its function quite well to compute the system variables during each of its flight phases and display the information required for further analysis. In future development, some validation tests still need to be accomplished for ensuring the accuracy and validity of the method used in this software.

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