Please use this identifier to cite or link to this item: https://hdl.handle.net/10356/16715
Title: Study of impact and transient vibration of aircraft landing gear
Authors: Hong, Weiling.
Keywords: DRNTU::Engineering::Aeronautical engineering::Aircraft
Issue Date: 2009
Abstract: This report looked into the reduction of vibration impact on landing gear such that passengers do not feel uncomforted during landing even if the pilots are not highly skilled. The actions involved in this project included building a test rig which consist of a landing gear, an accelerometer connected to the landing gear and a newly designed damping circuit that acted together with the oleo strut to further reduced the vibration at touchdown so as to achieve smooth landing. The mounted landing gear system was then dropped to simulate aircraft landing. The data collected by Vibration View software and hardware were compared to the published data of F-106 using dimensional analysis. The experiments and design were considered to be successful since the resultant vibration of the system was reduced. Results showed that height and weight during touchdown affect landing gear performance. Working in accordance to Joint Aviation Requirements (JAR) regulations, the increase in number of throttle valves connected in series circuit would improve the damping effect. The best design would be having the throttle valves connected to both the pressure line and the returning flow line. With such results, improvements to the design of landing gear were made and it will make a difference to the future landing gear performance.
URI: http://hdl.handle.net/10356/16715
Rights: Nanyang Technological University
Fulltext Permission: restricted
Fulltext Availability: With Fulltext
Appears in Collections:MAE Student Reports (FYP/IA/PA/PI)

Files in This Item:
File Description SizeFormat 
M-B108.pdf
  Restricted Access
2.14 MBAdobe PDFView/Open

Google ScholarTM

Check

Items in DR-NTU are protected by copyright, with all rights reserved, unless otherwise indicated.