Abstract
Landing, take off are one of the most maneuvering occurring in aircraft. The landing gear is considered as a non-linear structure due to its complicate behavior during landing period large amount of impact forces transferred into nose gear and main landing gear. Nose landing gear bears approx. 5% of aircraft's weight and is used for operations like landing, takeoff, as well as steering purpose. The cyclic loads acting on the landing gear which cause fatigue failure of landing gear or its parts. The current work includes the design of the nose landing gear which is retractable type of landing gear. During the ground operation of the aircraft, various types of loads will be encountered. Each of these loads will cause axial compression and tension on the wheels and strut of the landing gear. In this work the landing gear part we have chosen is shock strut which is one of the parts in landing gear on which most of the fatigue failures are observed is modeled using CATIA V5 Software. The analysis is carried out in ANSYS 20 R1.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
