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Fault adaptation by reconfiguring flight controls using control allocation

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dc.contributor.advisor Young, Trevor M.
dc.contributor.advisor Omerdić, Edin
dc.contributor.advisor Toal, Daniel Ahmad, Hammad 2016-08-30T11:58:07Z 2016-08-30T11:58:07Z 2009
dc.description peer-reviewed en_US
dc.description.abstract This research work focuses on the design and implementation of control law and control allocation for overactuated, nonlinear model of commercial aircraft (B747-200). The redundancies in this aircraft are exploited to achieve fault tolerance in the system through control allocation. Control allocation in the aircraft is actually the distribution of the settings for various control surfaces to achieve virtual control demands (i.e. pitch, roll and yaw angular accelerations). Control allocation is studied as a convex optimization problem. A constrained strictly convex quadratic problem is used with variation of designed problem parameters to influence the solution explicitly and implicitly. The solution is obtained online at a sampling frequency of 100Hz and then applied to the control surfaces of the aircraft. en_US
dc.language.iso eng en_US
dc.publisher University of Limerick
dc.subject aircraft modelling en_US
dc.subject fault tolerant control en_US
dc.subject control allocation design en_US
dc.subject overactuated systems en_US
dc.title Fault adaptation by reconfiguring flight controls using control allocation en_US
dc.type info:eu-repo/semantics/doctoralThesis en_US
dc.type.supercollection all_ul_research en_US
dc.type.supercollection ul_published_reviewed en_US
dc.type.supercollection ul_theses_dissertations en_US
dc.rights.accessrights info:eu-repo/semantics/openAccess en_US

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