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All Journal Bulletin of Electrical Engineering and Informatics Journal of Robotics and Control (JRC) Indonesian Journal of Aerospace
Andiarti, Rika
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Aerospace Engineering Astronomy Computer Science & IT Control & Systems Engineering Electrical & Electronics Engineering Mechanical Engineering

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Model Predictive Control in Hardware in the Loop Simulation for the OnBoard Attitude Determination Control System Irwanto, Herma Yudhi; Yusgiantoro, Purnomo; Sahabuddin, Zainal Abidin; Bura, Romie O.; Artono, Endro; Hakim, Arif Nur; Nuryadi, Ratno; Andiarti, Rika; Mariani, Lilis
Journal of Robotics and Control (JRC) Vol 5, No 2 (2024)
Publisher : Universitas Muhammadiyah Yogyakarta

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.18196/jrc.v5i2.21613

Abstract

Rocket flight tests invariably serve a purpose, one of which involves area monitoring or aerial photography. Consequently, the rocket necessitates the installation of a camera that remains consistently oriented toward the Earth's surface throughout its trajectory. Thus, ensuring the rocket's stability and preventing any rotation becomes imperative. To achieve this, the Onboard Attitude Determination Control System (OADCS) was researched and developed, fully controlled by NI myRIO with Labview as the programming language, ensures the rocket's attitude control and maintains a rolling angle of 0 degrees during flight. The MyRIO oversees the retrieval of attitude and position data from the X-Plane flight simulator, offering feedback through actuator control. The development of the OADCS proceeded incrementally through stages utilizing the Software in the Loop Simulation (SILS) and Hardware in the Loop Simulation (HILS) techniques, to ensure the verification of the system's functionality before its application to the rocket for real flight testing. In the OADCS control scheme, Model Predictive Control (MPC) is chosen, and it is compared with a PID controller to serve as a benchmark for processing speed. Because the rocket's flight time is short and its speeds of up to Mach 4. The simulation results indicate that MPC can halt the rocket's rotation 12 times more rapidly than PID control. Additionally, the MPC's ability to maintain a zero-degree rotation can persist throughout the rocket's flight time. Employing SILS and HILS enhances the OADCS rocket development process by incorporating MPC, which holds promise for application in real rockets.
Implementing trajectory correction strategy through model prediction control for flight vehicle missions Irwanto, Herma Yudhi; Yusgiantoro, Purnomo; Abidin Sahabuddin, Zainal; Oktovianus Bura, Romie; Andiarti, Rika; Eko Putro, Idris; Sudiana, Oka; Hanif, Azizul
Bulletin of Electrical Engineering and Informatics Vol 13, No 5: October 2024
Publisher : Institute of Advanced Engineering and Science

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.11591/eei.v13i5.7798

Abstract

Modeling a high-speed flying vehicle is imperative to ensure the success of vehicle development missions. Moreover, adherence to research protocols mandates a stepwise approach to testing the vehicle model, encompassing simulation trials using software-in-the-loop simulation (SILS), hardware-in-the-loop simulation (HILS), as well as diverse ground and environmental tests prior to flight testing. This study entailed a collaborative effort between MATLAB/Simulink and LabVIEW to seamlessly integrate the model developed in MATLAB/Simulink into LabVIEW for the implementation of model predictive control (MPC) strategy, aimed at trajectory correction (TC) missions for the vehicle. This MPC strategy was directly applied to the onboard flight control system (OBFCS) of the vehicle. Simulation results indicate the successful control of roll and pitch conditions by OBFCS in both SILS and HILS, ensuring the maintenance of flight conditions in accordance with predicted trajectories despite the presence of simulated disturbances. Notably, the simulation demonstrates the independence or absence of interference between each simultaneous MPC control for roll and pitch adjustments.
Stress Analysis of Load Cell Adaptor Designs For The Caliber450mm Solid Rocket Motor Static Test Moranova, Starida; Putro, Idris Eko; Abrizal, Haryadi; Mariani, Lilis; Prianto, Bayu; Hanif, Azizul; Andiarti, Rika; Ekadj, Firza Fadlan
Indonesian Journal of Aerospace Vol. 21 No. 2 (2023): Indonesian Journal Of Aerospace
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.55981/ijoa.2023.2669

Abstract

This study presents a structural analysis of two load cell adaptor designs for a caliber-450 mm solid rocket motor. The structural analysis of a C-shape load cell adaptor and the newly designed truncated-cone shape is presented incorporates a 30-degree truncated disc section and varies the thickness to 30 mm, 25 mm, and 20 mm. The numerical simulation using PATRAN reveals that by altering the arm thickness while maintaining the constant hinge thickness, the 30 mm thickness in the disc section yields the best local maximum stress. However, considering the global maximum stress, the 25 mm thickness emerges as the optimal design. The simulation results show that the 25 mm disc section of the load cell adaptor surpasses the aerospace standard safety factor (SF = 1.5) for both local and global maximum stress.
POWERED LANDING GUIDANCE ALGORITHMS USING REINFORCEMENT LEARNING METHODS FOR LUNAR LANDER CASE Nugroho, Larasmoyo; Zani, Novanna Rahma; Qomariyah, Nurul; Akmeliawati, Rini; Andiarti, Rika; Wijaya, Sastra Kusuma
Indonesian Journal of Aerospace Vol. 19 No. 1 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3573

Abstract

Any future planetary landing missions, just as demonstrated by Perseverance in 2021 Mars landing mission require advanced guidance, navigation, and control algorithms for the powered landing phase of the spacecraft to touch down a designated target with pinpoint accuracy (circular error precision < 5 m radius). This requires a landing system capable to estimate the craft’s states and map them to certain thrust commands for each craft’s engine. Reinforcement learning theory is used as an approach to manage the mapping guidance algorithm and translate it to engine thrust control commands. This work compares several reinforcement learning based approaches for a powered landing problem of a spacecraft in a two-dimensional (2-D) environment, and identify the advantages/disadvantages of them. Five methods in reinforcement learning, namely Q-Learning, and its extension such as DQN, DDQN, and policy optimization-based such as DDPG and PPO are utilized and benchmarked in terms of rewards and training time needed to land the Lunar Lander. It is found that Q-Learning method produced the highest efficiency. Another contribution of this paper is the use of different discount rates for terminal and shaping rewards, which significantly enhances optimization performance. We present simulation results demonstrating the guidance and control system’s performance in a 2-D simulation environment and demonstrate robustness to noise and system parameter uncertainty.
SISTEM KENDALI ROKET UNTUK GERAK UNPITCHING Andiarti, Rika; Sofyan, Edi
Indonesian Journal of Aerospace Vol. 4 No. 2 (2006): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

A missile control system utilizing Proportional-Integral-Derivative (PID) controller is proposed. With this controller, the missile is constrained to flight with zero pitch angle. By choosing LAPAN's missile RKX-100 as a dynamic model, this PID controller is applied. Simulation results show that the applying controller seems to be effective in missile unpitching manuver.
TEKNIK KONTROL SLIDING MODE UNTUK AUTOPILOT ROKET Andiarti, Rika
Indonesian Journal of Aerospace Vol. 4 No. 1 (2006): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

This paper deals with autopilot for rocket tracking problem by using sliding mode controller. Rocket model is considered as a linear system with two control input; wing and tail deflection. Simulation results show that the controller effectively works and gives desired performance (fast reaching and low chattering).
KONTROLER GAIN SCHEDULING UNTUK RUDAL UDARA KE UDARA Andiarti, Rika
Indonesian Journal of Aerospace Vol. 3 No. 2 (2005): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2005.v3.a813

Abstract

A control system for an air-to-air guided missile is developed. Gain scheduling control technique is used to perform the missile flight toward a moving target. The simulation results show that the gain scheduling control technique is effective to obtain the desired missile performance.
Co-Authors Abrizal, Haryadi Artono, Endro Bura, Romie O. Edi Sofyan, Edi Ekadj, Firza Fadlan Eko Putro, Idris Hakim, Arif Nur Hanif, Azizul Irwanto, Herma Yudhi Larasmoyo Nugroho Lilis Mariani, Lilis Moranova, Starida Nurul Qomariyah Prianto, Bayu Putro, Idris Eko Ratno Nuryadi Rini Akmeliawati Sastra Kusuma Wijaya Sudiana, Oka Yusgiantoro, Purnomo Zainal Abidin Sahabuddin, Zainal Abidin Zani, Novanna Rahma