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Abstract
Tricycle landing gear is a landing gear configuration on an aircraft with nose landing and main landing. Strength analysis of sandwich composites with impact loads aims to determine the maximum strength that can be resisted by sandwiches with several layers of lamina arranged with variations orientation fiber to obtain stiffness, to determine the type of damage caused by excessive loading. Fiber direction optimization was carried out to obtain optimal fiber direction variations in receiving loading, the optimal fiber direction was [(0)(45)(-45)(90)(0)]s with a significant Tsai-hill value from 0.091052752 to 0.057597845 after optimization. Simulation of impact loading with vertical velocity variations of 2 m/s, 3 m/s 4 m/s, 6 m/s, 8 m/s, 10 m/s, 12 m/s, 15 m/s using the finite element method by utilizing the Abaqus CAE software on the tricycle landing gear model and conducting tests to obtain large displacem ents, stresses and strains. By doing the test, it is found that the main landing gear structure is able to withstand a landing speed of up to 12 m/s with a large X-axis stress (S11) of 447.118 Mpa, a Y-axis stress (S22) 30.4995 Mpa, a shear stress of 26.2218 Mpa with a large a displacement of 11.9461 mm and a tsai-hill value of 0.5920. At a landing speed of 15 m/s the landing gear structure fails with a tsai-hill value that has passed the failure index 1, with a large X-axis stress (S11) 477.556 mpa, Y-axis stress (S22) 44.4075 Mpa, shear stress of 35 .2047 Mpa with a large displacement of 15.8297 mm and a tsai-hill value of 1.1336 where the landing speed of this landing gear structure failed, indicated by the tsai-hill value which had exceeded the failure index value 1.
Keywords: Main Landing Gear, UAV, Drop Impact, CompositeSandwich.
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References
- Wibawa, Lasinta Ari Nendra. (2019a). Desain dan Analisis Kekuatan Rangka Tricycle Landing Gear UAV Menggunakan Metode Elemen Hingga. Mechanical,9(2), 33. https://doi.org/10.23960/mech. v9.i2.201806
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- FAA, 2018, “Aviation Maintenance Technician Handbook–Airframe (FAA-H- 8083-31A), Volume 2”, United States Department of Transportation, Oklahoma City.
- Joel. P. Praveen, R. Vijayan. 2014. “Design and Stress Analysis of Nose Landing gear Barrel (NLGB) of A Typical Naval Trainer Aircraft”. IOSR- JMCE Vol. 11 Ver. III.
- Xue, Z., Li, M., Li, Y., & Jia, H. (2014). A Simplified Flexible Multibody Dynamics for a Main Landing Gear with Flexible Leaf Spring. 2014.
- Herlina Sari, N., Dyah, E. S., & Wirya Dirjan, M. (2014). Analisis Sifat Kekuatan Impact Komposit Sandwich Plastik Bekas Diperkuat Serat Sisal Dengan Core Bonggol Jagung.
- Dinamika Teknik Mesin, 4(1), 2088–88.
- Parmar, J., & Acharya, V. (2015). Selection And Analysis Of The Landing Gear For Unmanned Aerial Vehicle For Sae Aero Design Series Iaeme Publication Selection And Analysis Of The Landing Gear For Unmanned Aerial Vehicle For Sae Aero Design Series 48 International Mechanical International Mechanical Engineering and Technology, 6(2), 10–18. www.jifactor.com
- Wibawa, L. A.N. (2021). Effect of Fillet Radius of UAV Main Landing Gear on Static Stress and Fatigue Life using Finite Element Method. Journal of Physics: Conference Series. https://doi.org/10.1088/1742- 6596/1811/1/012082
- Ardiansyah, R., Hidayat, Nugroho, Afid, 2014, “Design and Analysis of Main Landing Gear Frame of LSU-05 By Finite Element Methode”, Jurnal Teknologi Pesawat Terbang, LAPAN, Rumpin.
References
Wibawa, Lasinta Ari Nendra. (2019a). Desain dan Analisis Kekuatan Rangka Tricycle Landing Gear UAV Menggunakan Metode Elemen Hingga. Mechanical,9(2), 33. https://doi.org/10.23960/mech. v9.i2.201806
Liang, Y . C., Chin, P . C., Sun, Y. P., & Wang, M. R. (2021). Design and manufacture of composite landing gear for a light unmanned aerial vehicle. Applied Sciences (Switzerland), 11(2), 1–12. https://doi.org/10.3390/app110 20509
Nababan. Arie. Dwi, 2021, “Optimisasi Arah Serat Komposit Main Landing Gear Pesawat Nirawak Lsu- 05 Menggunakan Metode Elemen Hingga”, Skripsi, Universitas Dirgantara Marsekal Suryadarma.
FAA, 2018, “Aviation Maintenance Technician Handbook–Airframe (FAA-H- 8083-31A), Volume 2”, United States Department of Transportation, Oklahoma City.
Joel. P. Praveen, R. Vijayan. 2014. “Design and Stress Analysis of Nose Landing gear Barrel (NLGB) of A Typical Naval Trainer Aircraft”. IOSR- JMCE Vol. 11 Ver. III.
Xue, Z., Li, M., Li, Y., & Jia, H. (2014). A Simplified Flexible Multibody Dynamics for a Main Landing Gear with Flexible Leaf Spring. 2014.
Herlina Sari, N., Dyah, E. S., & Wirya Dirjan, M. (2014). Analisis Sifat Kekuatan Impact Komposit Sandwich Plastik Bekas Diperkuat Serat Sisal Dengan Core Bonggol Jagung.
Dinamika Teknik Mesin, 4(1), 2088–88.
Parmar, J., & Acharya, V. (2015). Selection And Analysis Of The Landing Gear For Unmanned Aerial Vehicle For Sae Aero Design Series Iaeme Publication Selection And Analysis Of The Landing Gear For Unmanned Aerial Vehicle For Sae Aero Design Series 48 International Mechanical International Mechanical Engineering and Technology, 6(2), 10–18. www.jifactor.com
Wibawa, L. A.N. (2021). Effect of Fillet Radius of UAV Main Landing Gear on Static Stress and Fatigue Life using Finite Element Method. Journal of Physics: Conference Series. https://doi.org/10.1088/1742- 6596/1811/1/012082
Ardiansyah, R., Hidayat, Nugroho, Afid, 2014, “Design and Analysis of Main Landing Gear Frame of LSU-05 By Finite Element Methode”, Jurnal Teknologi Pesawat Terbang, LAPAN, Rumpin.