A design and numerical optimization of a landing gear for 1400 kg (AT-6) take-off mass aircraft

• Autorzy: Tywoniuk A. , Jakubowski R.

Identyfikatory

DOI

10.5604/12314005.1216489

• Języki publikacji: EN

Abstrakty

EN

One of the most important systems responsible for safe take-off and landing of aircraft is a landing gear system. Regardless of the configuration and the type of landing gear, its main function is to absorb energy from landing. The aim of this paper is to describe design and numerical optimization of modern tricycle-type, retractable landing gear system equipped with oleo-pneumatic amortization and mechanical emergency release. The landing gear was designed for a new prototype of 4 seats 1400 kg (AT-6) take-off mass aircraft in accordance with Certification Specifications for Normal, Utility, Aerobatic and Commuter Category Aeroplanes – CS-23. A complete design process from concept to final version was performed in Warsaw Institute of Aviation’s Landing Gear Laboratory. Proposed retractable landing gear concept substantially reduces aerodynamic drag of aircraft. Although application of one retraction system for the left and right gear make the system more complicated, this solution significantly reduces weight. The authors, because of the project complexity, focused on most important aspects of the main landing gear design and described numerical optimization of chosen components like composite leg with main and upper aluminium fittings. Engineers involved in the project used SolidEdge software for 3D modelling, kinematics optimization and 2D documentation preparation. Strength and stiffness analysis was carried out using hand and numerical calculation methods – FEMAP with NX Nastran and Hyperworks software.

Słowa kluczowe

EN

landing gear; aircraft; design; finite element method; undercarriage

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2016
• Tom: Vol. 23, No. 3
• Strony: 541--547
• Opis fizyczny: Bibliogr. 6 poz., rys.

Twórcy

autor

Tywoniuk A.

• Warsaw Institute of Aviation, Department of Transport and Energy Conversion Krakowska Avenue 110/114, 02-256 Warsaw, Poland tel.:[phone]

autor

Jakubowski R.

• Warsaw Institute of Aviation, Department of Transport and Energy Conversion Krakowska Avenue 110/114, 02-256 Warsaw, Poland tel.:[phone]

Bibliografia

• [1] Currey, N., Aircraft Landing Gear Design: Principles and Practices, AIAA (American Institute of Aeronautics & Ast, 1988.
• [2] Aviation Maintenance Technician Handbook – Airframe, Vol. 2 (FAA-H-8083-31), U.S. Department of Transportation, Federal Aviation Administration, 2012.
• [3] Certification Specifications for Normal, Utility, Aerobatic, and Commuter Category Aeroplanes CS23, European Aviation Safety Agency, 2009.
• [4] EM-11C Orka – specification document.
• [5] Femap with NX Nastran Help.
• [6] HyperMesh 11.0 User Guide, Altair.

Uwagi

PL

Opracowanie ze środków MNiSW w ramach umowy 812/P-DUN/2016 na działalność upowszechniającą naukę.