Studi Batas Siklus Osilasi Ground Resonance Helikopter AS565 MBe Panther melalui Pendekatan Matematis dan Simulasi pada Ground Vibration Test

Hadi, Abdul (2023) Studi Batas Siklus Osilasi Ground Resonance Helikopter AS565 MBe Panther melalui Pendekatan Matematis dan Simulasi pada Ground Vibration Test. Other thesis, Institut Teknologi Sepuluh Nopember.

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Abstract

Helikopter dalam gerakannya memiliki komponen yang kompleks dan rumit. Kerusakan dapat terjadi sewaktu-waktu pada bagian helikopter. Salah satu kerusakan tersebut yang terjadi pada helikopter adalah ground resonance. Pengujian terhadap helikopter AS565 MBe Panther yang dilakukan oleh PTDI hanya menggunakan 6 sensor pada 3 titik pengujian, sedangkan pada umumnya ground vibration test menggunakan sebanyak 300 hingga 500 sensor. Sehingga diperlukan suatu studi untuk menganalisis menggunakan pendekatan matematis dan simulasi yang divalidasi menggunakan data pengukuran. Pengukuran dilakukan menggunakan FTIS (Flight Test Instrumentation System) dan sensor akselerometer dengan variasi kondisi tekanan pada landing gear. Selanjutnya data pengukuran diolah menggunakan analisis dengan bantuan komputasi Matlab dan simulasi pada software Femap (Finite Element Modeling And Postprocessing). Dari penggunaan 6 sensor didapatkan error dominan frekuensi untuk matematis dan simulasi berturut-turut sebesar 2.63% dan 42.5%, kemudian dari root mean square error (RMSE) nya berturut-turut sebesar 1.7% dan 3.40%. Hasil pengolahan data hasil FTIS didapatkan kuantifikasi damping ratio sebesar 0.0542, 0.0479, 0.0433, dan 0.0505 masing-masing pada rate of roll, rate of pitch, rate of yaw dan percepatan arah sumbu-y. Setelah batas siklus osilasi didapatkan, ditemukan persentase respon frekuensi terhadap batas siklus osilasi tersebut untuk f1 (5.92-6.08Hz) sebesar 0%, f2 (23.68-24.32Hz) sebesar 15.88%, f3 (47.36-48.64Hz) sebesar 4.27% dan f4 (71.04-72.96Hz) sebesar 0.62%. Pada hasil modifikasi, secara matematis didapatkan persentase tambahan sebanyak 2% terhadap respon frekuensi helikopter tanpa modifikasi. Kemudian pada pemodelan simulasi menggunakan bentuk stik model didapatkan frekuensi pada mode ke-6 yang berkorelasi terhadap fenomena ground resonance yaitu 4.31Hz dengan persentase respon sebanyak 3.40%. Sehingga setelah serangkaian hasil pendekatan matematis dan simulasi kondisi normal serta modifikasinya dilakukan, tidak ditemukan potensi ground resonance pada helikopter AS565 MBe Panther.
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Helicopters in motion have complex and intricate components. Damage can occur at any time to any part of the helicopter. One such damage that occurs on helicopters is ground resonance. Testing of the AS565 MBe Panther helicopter conducted by PTDI only uses 6 sensors at 3 test points, while in general ground vibration tests use as many as 300 to 500 sensors. So a study is needed to analyze using mathematical and simulation approaches that are validated using measurement data. Measurements were made using FTIS (Flight Test Instrumentation System) and accelerometer sensors with varying pressure conditions on the landing gear. Furthermore, the measurement data is processed using analysis with the help of Matlab computing and simulation in Femap (Finite Element Modeling And Postprocessing) software. From the use of 6 sensors, the dominant frequency error for mathematics and simulation is 2.63% and 42.5% respectively, then from the root mean square error (RMSE) is 1.7% and 3.40% respectively. The data processing results of the FTIS results obtained damping ratio quantification of 0.0542, 0.0479, 0.0433, and 0.0505 respectively at the rate of roll, rate of pitch, rate of yaw and acceleration in the y-axis direction. After the oscillation cycle limit is obtained, the percentage of frequency response to the oscillation cycle limit is found for f1 (5.92-6.08Hz) by 0%, f2 (23.68-24.32Hz) by 15.88%, f3 (47.36-48.64Hz) by 4.27% and f4 (71.04-72.96Hz) by 0.62%. In the modification results, mathematically obtained an additional percentage of 2% against the frequency response of the chopper without modification. Then in simulation modeling using the stick model form, the frequency in the 6th mode that correlates with the ground resonance phenomenon is 4.31Hz with a response percentage of 3.40%. So that after a series of mathematical approach results and simulation of normal conditions and modifications are carried out, no potential ground resonance is found on the AS565 MBe Panther helicopter.

Item Type:	Thesis (Other)
Uncontrolled Keywords:	frekuensi, getaran, helikopter, resonance, respon, frequency, vibration, response.
Subjects:	T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL671.9 Airplanes--Maintenance and Repair T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL696.C6 Airplanes--Collision avoidance
Divisions:	Faculty of Industrial Technology and Systems Engineering (INDSYS) > Physics Engineering > 30201-(S1) Undergraduate Thesis
Depositing User:	Abdul Hadi
Date Deposited:	26 Sep 2023 02:14
Last Modified:	26 Sep 2023 02:14
URI:	http://repository.its.ac.id/id/eprint/104063

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