Dynamic Model Establishment of Deployable Missile Control Fin with Nonlinear Hinge

A deployable missile control fin has some structural nonlinearities because of the worn or loose hinges and the manufacturing tolerance. The structural nonlinearity cannot be eliminated completely, and exerts significant effects on the static and dynamic characteristics of the control fin. Thus, it is important to establish the accurate deployable missile control fin model. In the present study, the nonlinear dynamic model of the deployable missile control fin is established. The deployable missile control fin can be subdivided into two substructures represented by linear dynamic models and a nonlinear hinge with structural nonlinearities. From dynamic tests, the nonlinear hinge parameters are identified and the nonlinear hinge model is established by using system identification method such as Force-State Mapping Technique. The substructure modes are improved using the Frequency Response Method. The substructure models and the nonlinear hinge model are coupled to establish the nonlinear dynamic model of the fin using the expanded substructure synthesis. Finally, the established nonlinear dynamic model of the deployable missile control fin is verified by modal and dynamic tests.
Publisher
American Institute of Aeronautics and Astronautics
Issue Date
2005-01
Citation

Journal of Spacecraft and Rockets, vol.42, no.1, pp.66-77

ISSN
0022-4650
URI
http://hdl.handle.net/10203/5772
Link
http://www.aiaa.org/content.cfm?pageid=322&lupubid=25
Appears in Collection
AE-Journal Papers(저널논문)
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