The Application of the Root Locus Method for the Design of Pitch Controller of an F-104A Aircraft
Само за регистроване кориснике
2009
Чланак у часопису (Објављена верзија)
Метаподаци
Приказ свих података о документуАпстракт
This paper presents an application of the root locus technique for the design of a feedback control system of an F-104A aircraft. The analysis of the longitudinal aircraft stability was performed for the jingle Input Single Output (SISO) open-loop system, using linearised equations of aircraft motion and aerodynamic derivatives of an F-104A aircraft taken from the NASA report [1]. The dynamical behavior of the open-loop system was unsatisfactory and led to the introduction of the feedback control system. The closed-loop system was designed using the root locus technique, developed by Evans in 1948. The transfer function parameters of each element of the feedback control system are determined according to previously set design requirements. Although, the analysis of the closed-loop step response showed that all of the design requirements were realised, the controller designed within the proposed control system structure is not the only one, and there are different controller designs tha...t lead to a satisfactory solution.
Кључне речи:
stability derivatives / root locus / longitudinal dynamical stability / controller synthesisИзвор:
Strojniski Vestnik/Journal of Mechanical Engineering, 2009, 55, 9, 555-560Колекције
Институција/група
Mašinski fakultetTY - JOUR AU - Stojiljković, Branimir AU - Vasov, Ljubiša AU - Mitrović, Časlav AU - Cvetković, Dragan PY - 2009 UR - https://machinery.mas.bg.ac.rs/handle/123456789/875 AB - This paper presents an application of the root locus technique for the design of a feedback control system of an F-104A aircraft. The analysis of the longitudinal aircraft stability was performed for the jingle Input Single Output (SISO) open-loop system, using linearised equations of aircraft motion and aerodynamic derivatives of an F-104A aircraft taken from the NASA report [1]. The dynamical behavior of the open-loop system was unsatisfactory and led to the introduction of the feedback control system. The closed-loop system was designed using the root locus technique, developed by Evans in 1948. The transfer function parameters of each element of the feedback control system are determined according to previously set design requirements. Although, the analysis of the closed-loop step response showed that all of the design requirements were realised, the controller designed within the proposed control system structure is not the only one, and there are different controller designs that lead to a satisfactory solution. T2 - Strojniski Vestnik/Journal of Mechanical Engineering T1 - The Application of the Root Locus Method for the Design of Pitch Controller of an F-104A Aircraft EP - 560 IS - 9 SP - 555 VL - 55 UR - https://hdl.handle.net/21.15107/rcub_machinery_875 ER -
@article{ author = "Stojiljković, Branimir and Vasov, Ljubiša and Mitrović, Časlav and Cvetković, Dragan", year = "2009", abstract = "This paper presents an application of the root locus technique for the design of a feedback control system of an F-104A aircraft. The analysis of the longitudinal aircraft stability was performed for the jingle Input Single Output (SISO) open-loop system, using linearised equations of aircraft motion and aerodynamic derivatives of an F-104A aircraft taken from the NASA report [1]. The dynamical behavior of the open-loop system was unsatisfactory and led to the introduction of the feedback control system. The closed-loop system was designed using the root locus technique, developed by Evans in 1948. The transfer function parameters of each element of the feedback control system are determined according to previously set design requirements. Although, the analysis of the closed-loop step response showed that all of the design requirements were realised, the controller designed within the proposed control system structure is not the only one, and there are different controller designs that lead to a satisfactory solution.", journal = "Strojniski Vestnik/Journal of Mechanical Engineering", title = "The Application of the Root Locus Method for the Design of Pitch Controller of an F-104A Aircraft", pages = "560-555", number = "9", volume = "55", url = "https://hdl.handle.net/21.15107/rcub_machinery_875" }
Stojiljković, B., Vasov, L., Mitrović, Č.,& Cvetković, D.. (2009). The Application of the Root Locus Method for the Design of Pitch Controller of an F-104A Aircraft. in Strojniski Vestnik/Journal of Mechanical Engineering, 55(9), 555-560. https://hdl.handle.net/21.15107/rcub_machinery_875
Stojiljković B, Vasov L, Mitrović Č, Cvetković D. The Application of the Root Locus Method for the Design of Pitch Controller of an F-104A Aircraft. in Strojniski Vestnik/Journal of Mechanical Engineering. 2009;55(9):555-560. https://hdl.handle.net/21.15107/rcub_machinery_875 .
Stojiljković, Branimir, Vasov, Ljubiša, Mitrović, Časlav, Cvetković, Dragan, "The Application of the Root Locus Method for the Design of Pitch Controller of an F-104A Aircraft" in Strojniski Vestnik/Journal of Mechanical Engineering, 55, no. 9 (2009):555-560, https://hdl.handle.net/21.15107/rcub_machinery_875 .