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L₁ adaptive control of fixed-wing unmanned aerial vehicle / Mohamed Hussien Ahmed Mohamed ; Supervised Hossameldin Ahmed Abdelfattah , Ahmed Mohamed Ahmed Kamel , Mahmoud Elnaggar

By: Contributor(s): Material type: TextTextLanguage: English Publication details: Cairo : Mohamed Hussien Ahmed Mohamed , 2021Description: 119 P. : charts , facsimiles ; 30cmOther title:
  • فى الطائرات بدون طيار ذات الجناح الثابت L₁ التحكم المتوائم من نوع [Added title page title]
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Dissertation note: Thesis (M.Sc.) - Cairo University - Faculty of Engineering - Department of Electrical Power and Machines Summary: In this thesis, L₁ adaptive controller is used to fully control fixed-wing unmanned aerial vehicle{u2019}s attitude (UAV), both longitudinal and lateral. Two modeling approaches are used to model the UAV.The classical approach which uses the kinematic and dynamic differential equations that describe the vehicle motion, forces and moments.This approach results in a fully nonlinear model of the vehicle.The model is, then linearized and augmented with the actuator dynamics.The controller is designed using the augmented linear model and tested using the fully nonlinear model. The second approach is the total energy control system (TECS) in which the aircraft is considered as a point of mass. In this technique, the energy-based concept is used in modeling aircraft depending on energy states
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Item type Current library Home library Call number Copy number Status Date due Barcode
Thesis Thesis قاعة الرسائل الجامعية - الدور الاول المكتبة المركزبة الجديدة - جامعة القاهرة Cai01.13.07.M.Sc.2021.Mo.L (Browse shelf(Opens below)) Not for loan 01010110085244000
CD - Rom CD - Rom مخـــزن الرســائل الجـــامعية - البدروم المكتبة المركزبة الجديدة - جامعة القاهرة Cai01.13.07.M.Sc.2021.Mo.L (Browse shelf(Opens below)) 85244.CD Not for loan 01020110085244000

Thesis (M.Sc.) - Cairo University - Faculty of Engineering - Department of Electrical Power and Machines

In this thesis, L₁ adaptive controller is used to fully control fixed-wing unmanned aerial vehicle{u2019}s attitude (UAV), both longitudinal and lateral. Two modeling approaches are used to model the UAV.The classical approach which uses the kinematic and dynamic differential equations that describe the vehicle motion, forces and moments.This approach results in a fully nonlinear model of the vehicle.The model is, then linearized and augmented with the actuator dynamics.The controller is designed using the augmented linear model and tested using the fully nonlinear model. The second approach is the total energy control system (TECS) in which the aircraft is considered as a point of mass. In this technique, the energy-based concept is used in modeling aircraft depending on energy states

Issued also as CD

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