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All Journal Indonesian Journal of Electrical Engineering and Computer Science Indonesian Journal of Aerospace
Laksono, Shandi Prio
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Aerospace Engineering Astronomy

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Performance of rocket data communication system using wire rope isolator on sounding rocket RX Rahardiyanti, Kandi; Laksono, Shandi Prio; Hakim, Khaula Nurul; Nugroho, Yuniarto Wimbo; Adi, Andreas Prasetya; Salman, Salman; Kurdianto, Kurdianto
Indonesian Journal of Electrical Engineering and Computer Science Vol 38, No 2: May 2025
Publisher : Institute of Advanced Engineering and Science

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.11591/ijeecs.v38.i2.pp783-793

Abstract

The rocket experiment (RX) ballistic rocket requires a reliable data communication system capable of withstanding intense vibrations and shocks during flight. This study investigates the application of wire rope isolators (WRI) to damper mechanical disturbances and protect the rocket's communication system. Installation of WRI position and direction in this experiment with compression position. A series of vibration tests were conducted using 4 WRI installed in the rocket’s 30 kg data communication compartment, vibration test results frequency between 4 Hz and 1500 Hz with acceleration of 8.37 g to 20.37 g, higher "g" readings on the test object sensor compared to vibration machine readings are usually caused by phenomena such as resonance, differences in dynamic response, non-linear behavior, sensor placement location, and swing effects when the vibration machine oscillates. This is a natural mechanical response to external vibrations during testing. While the results of flight tests rocket RX has an acceleration of 8 g to 9.3 g. The results showed that the WRI dampers are effective in protecting the data communication system and ensuring the uninterrupted transmission of flight data to the ground control station (GCS).
Investigation of Wire Diameter of Helical Compression Spring for Payload Separation Laksono, Shandi Prio
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.a3490

Abstract

The payload is designed to be separated from rocket at an altitude over 100 km. Â One of critical component in the payload separation system is the helical compression spring. The helical compression spring ensures safe release the payload. The spring must satisfy some parameters such as static failure and buckling, also spring has enough energy storing to release the payload during launch. The objective of this paper is to do investigation of wire diameter of helical compression spring which can be used in the payload separation system of sounding rocket based on several constraints. The results obtained show that with payload weight of 60 kg, minimum wire diameter should be 8 mm with mean coil diameter of 80 mm. The maximum separation velocity of 1.76 m/swas obtained by using wire diameter of 8 mm and mean coil diameter of 96 mm.
Co-Authors Andreas Prasetya Adi Khaula Nurul Hakim Kurdianto Kurdianto, Kurdianto Nugroho, Yuniarto Wimbo Rahardiyanti, Kandi Salman Salman