Load Analysis Of The Landing Gear Structure On The Grob G120TP-A

Benedictus Mardwianta; Muhammad Bimo Santoso; Abdul Haris Subarjo; Nurfi Ahmadi; Okto Dinaryanto; Dedet Hermawan

doi:10.2991/978-94-6463-358-0_20

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Load Analysis Of The Landing Gear Structure On The Grob G120TP-A

Authors

Benedictus Mardwianta¹^{, *}, Muhammad Bimo Santoso¹, Abdul Haris Subarjo¹, Nurfi Ahmadi¹, Okto Dinaryanto¹, Dedet Hermawan¹

¹Mechanical Engineering Department, Adisutjipto Institute of Aerospace Technology, Yogyakarta, Indonesia

^*Corresponding author. Email: benedictusmardwianta@gmail.com

Corresponding Author

Benedictus Mardwianta

Available Online 12 January 2024.

DOI: 10.2991/978-94-6463-358-0_20 How to use a DOI?
Keywords: landing gear; Grob G120TP-A aircraft; Mean Aerodynamic Chord; static load; dynamic load
Abstract: The landing gear plays a role in supporting the weight of the aircraft while on the ground, and the characteristics of the landing gear vary according to the characteristics of the aircraft itself. The Grob G120TP-A aircraft utilizes Retractable Tricycle Landing Gear. With a three-wheeled structure, as a result, the aircraft is more stable when on the ground, and the landing gear must be capable of absorbing landing loads and navigating uneven terrain. To understand the limitations of the landing gear structure’s capabilities for the Grob G120TP-A aircraft, a structural analysis is necessary. During the landing gear analysis phase, specific provisions have been formalized to analyze the weight of the landing gear structure for the Grob G120TP-A aircraft. The Grob G120TP-A aircraft has a center of gravity position in terms of percent MAC (X̅TO) of 36.38% and (Y̅TO) of 62.31%, with a center of gravity height of 1,420 m. The maximum static load for the main landing gear (MLG) is 45,686.79 N, and for the nose landing gear (NLG) is 54,631.66 N. The minimum static load for the MLG is 53,556.01 N. The dynamic load for the NLG is 91,340.38 N, and for the MLG is 82,395.51 N.
Copyright: © 2023 The Author(s)
Open Access: Open Access This chapter is licensed under the terms of the Creative Commons Attribution-NonCommercial 4.0 International License (http://creativecommons.org/licenses/by-nc/4.0/), which permits any noncommercial use, sharing, adaptation, distribution and reproduction in any medium or format, as long as you give appropriate credit to the original author(s) and the source, provide a link to the Creative Commons license and indicate if changes were made.

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Volume Title: Proceedings of the 2023 Annual Technology, Applied Science and Engineering Conference (ATASEC 2023)
Series: Advances in Engineering Research
Publication Date: 12 January 2024
ISBN: 10.2991/978-94-6463-358-0_20
ISSN: 2352-5401
DOI: 10.2991/978-94-6463-358-0_20 How to use a DOI?
Open Access: Open Access This chapter is licensed under the terms of the Creative Commons Attribution-NonCommercial 4.0 International License (http://creativecommons.org/licenses/by-nc/4.0/), which permits any noncommercial use, sharing, adaptation, distribution and reproduction in any medium or format, as long as you give appropriate credit to the original author(s) and the source, provide a link to the Creative Commons license and indicate if changes were made.

Cite this article

ris enw bib

TY  - CONF
AU  - Benedictus Mardwianta
AU  - Muhammad Bimo Santoso
AU  - Abdul Haris Subarjo
AU  - Nurfi Ahmadi
AU  - Okto Dinaryanto
AU  - Dedet Hermawan
PY  - 2024
DA  - 2024/01/12
TI  - Load Analysis Of The Landing Gear Structure On The Grob G120TP-A
BT  - Proceedings of the 2023 Annual Technology, Applied Science and Engineering Conference (ATASEC 2023)
PB  - Atlantis Press
SP  - 195
EP  - 209
SN  - 2352-5401
UR  - https://doi.org/10.2991/978-94-6463-358-0_20
DO  - 10.2991/978-94-6463-358-0_20
ID  - Mardwianta2024
ER  -

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