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Zuhri, Muhammad Rizki
Politeknik Negeri Bandung
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Correction Maneuver Optimization to Maintain The Local Time of Lapan-A4 Satellite Zuhri, Muhammad Rizki; Poetro, Ridanto Eko; Indriyanto, Toto; Faturrohim, Luqman
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.2023.723

Abstract

In order for a satellite to achieve a sun-synchronous orbit (SSO), it must have a nodal precession rate equal to the revolution rate of the Earth around the Sun. However, sun-synchronous satellites generally encounter significant perturbations, which lead the local time of the satellite to drift gradually. In this research, the author analyzed potential maneuvers to maintain the local time of an SSO satellite for 5 years of operation of LAPAN-A4 satellite. The analysis was conducted by simulation using GMAT (General Mission & Analysis Tools) software with the LAPAN-A4 satellite as a case study. Furthermore, this research also attempted to find the optimum maneuvering period for each potential maneuver. The results showed that the RAAN correction maneuver is ineffective. It was also found that the most optimum maneuvering plan obtained from this research was a semi-major axis correction maneuver with 4 month maneuvering period with a particular correction targeting strategy.
Flight Control Design for Rudder Failure Event on Cessna 172 Aircraft Zuhri, Muhammad Rizki
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.2025.9106

Abstract

The Cessna 172, a widely used small commercial aircraft, is renowned for its stabilityin both longitudinal and lateral-directional dimensions. Despite its intrinsic stability, arobust control system is essential to mitigate potential failures, such as rudder malfunctions.This study developed and simulated a control system for the Cessna 172 underrudder failure conditions, relying solely on aileron input for heading control. Using a linearstate-space approach implemented in Matlab/Simulink, the control system incorporatedyaw damping, roll damping, and heading hold for stability and waypoint tracking. Initialsimulations showed that the controller could guide the aircraft to the destination waypointbut exhibited significant deviations of up to 20% under constant rudder inputs. Controllermodification to the PID controller significantly improved performance, reducing deviationsto a maximum of only 0.1% for ±5° rudder input. These results demonstrate the effectivenessof the proposed control system in compensating for rudder failure, though slightoscillations observed at the start of the trajectory suggest the need for further refinement.This research underscores the potential for adaptive and unconventional control methodsto enhance safety and reliability in small aircraft operations.
Station-Keeping Simulation and Planning for LAPAN-A4 Satellite Using Finite-Burn Thruster Zuhri, Muhammad Rizki; Poetro, Ridanto Eko
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.a3474

Abstract

To be a Sun-synchronous orbit (SSO), the orbit must have a certain value of nodal precession rate, which equals to 360°/year. However, the value of nodal precession rate is usually drifted by orbit perturbations, mainly by the oblateness of the Earth and atmospheric drag, to be no longer 360°/year as expected for SSO. Thus, the local time of the satellite will change too, so it needs to be corrected by some correction maneuvers. In this research, the authors studied about station-keeping planning for SSO satellite via inclination correction maneuver by simulation using GMAT, a software developed by NASA, with a finite-burn propulsion approach. In this research, LAPAN-A4 satellite is chosen to be the satellite that will be simulated. Some alternative plans of inclination correction maneuver based on maneuvering periods are chosen, they are maneuver for every 2 months, 4 months, 6 months, 12 months, and 24 months. The simulation results show that the optimal station keeping planning is the maneuver for every 2 months. This alternative gives the lowest fuel consumption so that the fuel and launch cost will be minimum, and the local time drift that is still may be tolerated.
Co-Authors Ajeng Ayu Milanti Budi Hartono Budi Hartono Citra Asti Rosalia Citra Asti Rosalia Defrianto Pratama Destri Muliastri Devi Eka Septiyani Arifin Dewi, Yunita Citra Faturrohim, Luqman Fauzan, Nofrijal Fransisca Soetanto, Maria Hasanah, Rahmawati Indriyanto, Toto Iryani, Lenny Luthfi, Mochammad Muhammad Daffa Hauzaan Nofrijal Fauzan Poetro, Ridanto Eko Rhamadhan, Firman Sinung Nugroho, Yohanes Soetanto, Maria Fransisca Sri Widarti Suradi Kartanegara, Radi Syarif Hidayat Teguh Wibowo Wibowo, Singgih Satrio Zaim Sidqi Islami Zainuddin Zainuddin