عنوان :
طراحي تستر براي تشخيص و شناسايي عيب در سيستم كنترلي بالگرد
مقطع تحصيلي :
كارشناسي ارشد
محل تحصيل :
اصفهان: دانشگاه صنعتي اصفهان، دانشكده برق و كامپيوتر
صفحه شمار :
دوازده،74ص.: مصور،جدول،نمودار
يادداشت :
ص.ع.به فارسي و انگليسي
استاد راهنما :
جواد عسگري، سعيد حسين نيا
توصيفگر ها :
كنترل گام به عقب , تشخيص و جداسازي عيب , عيب يابي بالگرد , عيب هاي محرك
تاريخ نمايه سازي :
18/3/93
استاد داور :
ايمان ايزدي، مرضيه كمالي
دانشكده :
مهندسي برق و كامپيوتر
چكيده انگليسي :
Tester Design for Fault Detection and Diagnosis in Helicopter Control System Ata Nazari Ata nazari@ec iut ac ir Date of Submission 01 22 2014 Department of Electrical and Computer Engineering Isfahan University of Technology Isfahan 84156 83111 Iran Degree M Sc Language FarsiSupervisors Javad Askari j askari@cc iut ac ir Saeed Hosseinnia hoseinia@cc iut ac ir Abstract Helicopter is a complicated system which is made of various elements that are closelycommunicating with each other Any kind of fault in this system could create multipledeficiencies such as human and economic damages Therefore it is necessary to design amechanism to detect the faults in order to accomplish the required proceedings Differenttechniques in creating fault diagnosis units have been suggested In this thesis we focus oncreating the aforementioned unit based on the idea of state observer methods The idea of using observer in fault diagnosis units is based on dynamic model ofhelicopter Most of the works that has been done in fault diagnosis in helicopter are basedon linear or nonlinear models with limited degrees of freedom As a result acomprehensive model with the highest degree of freedom is employed Helicopter controland stabilization is done using back stepping method ensures bounded tracking of the system statesin the presence of structural uncertainties Existence of structural uncertainties in the structureof a helicopter causes difficulties in fault diagnosis so adaptive threshold is applied toovercome such problems The fault diagnosis unit that is designed in this thesis has beenused in the incidence of fault in flap actuators The resulting fault model is performancedegradation faults or multiplicative faults Also extended observers are used to isolate the occurredfaults Since there are several state variables which can indicate us where the fault happens only some are used to detect and isolate them Keywords Helicopter Back stepping control Fault Diagnosis and Isolation FDI inhelicopter Actuator faults
استاد راهنما :
جواد عسگري، سعيد حسين نيا
استاد داور :
ايمان ايزدي، مرضيه كمالي
