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Syah, Agus Harno Nurdin
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Aerospace Engineering Astronomy

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Design and experimental Verification of Vibration Testing Fixture for Flight Control Panel Wijaya, Yusuf Giri; Ula, Nur Mufidatul; P.P., Mikhael Gilang Pribadi; Muksin, Muksin; Syah, Agus Harno Nurdin
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.a3701

Abstract

In this research, experimental design and testing of the vibration test fixture were carried out. The designed vibration test fixture is used to test the FCP, which is one of the components of avionics in aircraft. FCP vibration testing is carried out using the DO-160 test standard. The test has a test frequency range from 5 to 500 Hz. Therefore, the vibration test fixture must have a natural frequency above 600 Hz. The vibration test fixture is designed using a T-type model with modifications to get optimal results. The raw material used to make the test fixture is aluminum. The test fixture has a natural frequency value above 500 Hz, and both were tested using FEM simulation and experimental tests. Therefore, the vibration test fixture that is made meets the requirements for vibration testing on FCP. The difference in the natural frequency value from the FEM simulation and experimental test results on the vibration test fixture is 14.61% on the Z-axis, 10.61% on the X-axis, and 9.74 on the Y-axis.
PREDIKSI KEKUATAN STRUKTUR ALAT UJI GETARAN ENGINE LSU SERIES MENGGUNAKAN METODE ELEMEN HINGGA (STRENGTH PREDICTION OF THE ENGINE VIBRATION TEST STAND OF LSU SERIES USING FINITE ELEMENT METHOD) Wandono, Fajar Ari; Syah, Agus Harno Nurdin
Indonesian Journal of Aerospace Vol. 15 No. 1 Juni (2017): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2017.v15.a2505

Abstract

Untuk mengetahui karakteristik getaran dari kombinasi engine dan propeller yang digunakan pada LAPAN Surveillance UAV (LSU) series maka diperlukan sebuah alat uji yang disebut alat uji getaran engine (AUGE). Struktur AUGE harus dibuat kuat dan kaku untuk mendapatkan hasil uji getaran engine yang baik. Sebagai langkah awal telah dibuat sebuah AUGE yang terbuat dari material ASTM A36 yang berbentuk H setinggi 1 meter dengan bagian bawahnya dibaut ke sebuah lantai yang sudah diperkuat. Dengan menggunakan software metode elemen hingga dan memasukkan parameter engine DA-170 serta sifat mekanik ASTM A36 didapatkan bahwa struktur AUGE tersebut memiliki nilai faktor keamanan sebesar 26,24. Adapun lima nilai pertama frekuensi pribadi dari struktur tersebut adalah 61,94 Hz, 77,18 Hz, 93,79 Hz, 212,23 Hz dan 286,24 Hz.
Frequency Mapping of Square Head Expander for Vibration Testing Pratama, Mikhael Gilang Pribadi Putra; Muksin, Muksin; Wijaya, Yusuf Giri; Syah, Agus Harno Nurdin
Indonesian Journal of Aerospace Vol. 20 No. 1 (2022): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2022.v20.a3709

Abstract

Head expander is a component of an electro-dynamic shaker used for vibration tests in the vertical direction for large-size specimens. This study aims to determine the natural frequency distribution of the head expander across a certain number of predetermined points. This distribution map needs to be known to determine the better placement of future specimens on the head expander. In this study, the determination of natural frequency distribution is done through harmonic analysis (simulation) and experiment to form a contrast between the head expander's ideal condition and the actual condition. The frequency range in the middle of the Head Expander has almost the same value for both data types at 1550-1650 Hz. These results recommend that the best sample placement is in the middle of the Head Expander. The difference between the experimental and simulation low points has a not too far difference, which is 62.5 Hz. In contrast, at the highest value, the two have a quite far difference, which is 180.27 Hz. this difference can be caused by the improper installation of sensors on the Head Expander at certain points.
ON-BOARD FUNDAMENTAL FREQUENCY ESTIMATION OF ROCKET FLIGHT EXPERIMENTS USING DSP MICROCONTROLLER AND ACCELEROMETER Syah, Agus Harno Nurdin; Kliwati, Sri; Widada, Wahyu
Indonesian Journal of Aerospace Vol. 7 No. 1 Juni (2009): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Fundamental frequency vibrasi roket pada saat terbang sangat penting diukur untuk pengembangan sistem elektronik maupun mekanik muatan roket. Tulisan ini membahas metode pengukuran fundamental frekuensi tersebut dengan menggunakan sensor accelerometer dan 32 bit DSP (Digital Signal Processor) microcontroller. CPU ini digunakan untuk akuisisi data dan perhitungan algoritma DFT (Discrete Fourier Transform) serta algoritma penentuan frekuensi fundamentalnya. Deteksi fundamental frekuensi berbasis envelope (lowpass filter) spektrum frekuensi. Sistem yang telah dibuat dapat dikombinasikan dengan radio modem untuk pengiriman data dengan kecepatan serta sampling rate yang cukup tinggi. Maksimum frekuensi yang dapat diestimasi hingga 2 kHz, cukup untuk parameter roket.
UJI VALIDASI TERMAL VIBRASI UNTUK MUATAN MISI MIKROSAT Syah, Agus Harno Nurdin
Indonesian Journal of Aerospace Vol. 2 No. 1 (2004): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2004.v2.a789

Abstract

To launching a spacecraft (rocket and satellite) including all of the systems, some rules and regulation of validation test for all the spacecraft systems is needed. Validation test mentioned is done to find out the ability of all the systems to the environmental influences of the external although internal with measurements simultaneously done. This is including possibilities the operating all of the electronic systems and epending the life times, operation time of the internal and external condition to the parameters effect of environmental the spacecraft systems. Thermal vibration is two parameters effect of environmental which would receiped simultaneously by the microsatellite or spacecraft on trajectory time when the spacecraft inside of the thermospheer zone at height about (80-500) km and the exospher zone at height about (500-1000)km under the seal level. Therefore, thermal vibration test is very important to do before a spacecraft or microsatellite would be launched, because the environmental parameters is very dangerous to the microsatellite or spacecraft mission payload.
Co-Authors Muksin Muksin P.P., Mikhael Gilang Pribadi Pratama, Mikhael Gilang Pribadi Putra Sri Kliwati Ula, Nur Mufidatul Wahyu Widada Wandono, Fajar Ari Wijaya, Yusuf Giri