Numerical Continuation Applied to Landing Gear Mechanism Analysis 2.pdf (4.38 MB)
Numerical continuation applied to landing gear mechanism analysis
journal contribution
posted on 2015-09-10, 10:11 authored by James KnowlesJames Knowles, Bernd Krauskopf, Mark H. LowenbergA method of investigating quasi-static mechanisms is presented and applied to an overcenter mechanism and to a nose landing gear mechanism. The method uses static equilibrium equations along with equations describing the geometric constraints in the mechanism. In the spirit of bifurcation analysis, solutions to these steady-state equations are then continued numerically in parameters of interest. Results obtained from the bifurcation method agree with the equivalent results obtained from two overcenter mechanism dynamic models (one state-space and one multibody dynamic model), while a considerable computation time reduction is demonstrated with the overcenter mechanism. The analysis performed with the nose landing gear model demonstrates the flexibility of the continuation approach, allowing conventional model states to be used as continuation parameters without a need to reformulate the equations within the model. This flexibility, coupled with the computation time reductions, suggests that the bifurcation approach has potential for analyzing complex landing gear mechanisms.
Funding
This research was supported by an Engineering and Physical Sciences Research Council (EPSRC) Case Award grant in collaboration with Airbus in the UK.
History
School
- Aeronautical, Automotive, Chemical and Materials Engineering
Department
- Aeronautical and Automotive Engineering
Published in
Journal of AircraftVolume
48Issue
4Pages
1254 - 1262 (8)Citation
KNOWLES, J.A.C., KRAUSKOPF, B. and LOWENBERG, M.H., 2011. Numerical continuation applied to landing gear mechanism analysis. Journal of Aircraft, 48(4), pp.1254-1262.Publisher
© American Institute of Aeronautics and AstronauticsVersion
- AM (Accepted Manuscript)
Publisher statement
This work is made available according to the conditions of the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International (CC BY-NC-ND 4.0) licence. Full details of this licence are available at: https://creativecommons.org/licenses/by-nc-nd/4.0/Publication date
2011Notes
This paper was accepted for publication in the journal Journal of Aircraft and the definitive published version is available at http://dx.doi.org/10.2514/1.C031247ISSN
0021-8669;1533-3868Publisher version
Language
- en