Brake-induced vibration often involves strong coupling with the aircraft structure, thereby necessitating a system level understanding. However, testing a full system is both costly and impossible until late in the development cycle. To overcome these issues, it becomes necessary to utilize simulation tools to assess the system behavior at an earlier stage. This paper demonstrates a methodology which implements such simulations to guide appropriate brake component tests that are more tractable for the brake supplier. As a result of this combined simulation and testing, a reduction in actual testing can be achieved. However, the ultimate success of the methodology depends on how well the components and the various parameters are estimated. Consequently, means to improve these estimations are also addressed in this paper.
- Design Engineering Division and Computers and Information in Engineering Division
Coupling of an Aircraft Landing Gear Simulation Strategy to Parameter Identification Techniques for Enhanced Fidelity
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Rook, T. "Coupling of an Aircraft Landing Gear Simulation Strategy to Parameter Identification Techniques for Enhanced Fidelity." Proceedings of the ASME 2003 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. Volume 5: 19th Biennial Conference on Mechanical Vibration and Noise, Parts A, B, and C. Chicago, Illinois, USA. September 2–6, 2003. pp. 1251-1258. ASME. https://doi.org/10.1115/DETC2003/VIB-48450
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