The Application of the Root Locus Method for the Design of Pitch Controller of an F-104A Aircraft

606 Ogledov
835 Prenosov
Izvoz citacije: ABNT
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. 
Strojniški vestnik - Journal of Mechanical Engineering, [S.l.], v. 55, n.9, p. 555-560, august 2017. 
ISSN 0039-2480.
Available at: <https://www.sv-jme.eu/sl/article/the-application-of-the-root-locus-method-for-the-design-of-pitch-controller-of-an-f-104a-aircraft/>. Date accessed: 11 nov. 2019. 
doi:http://dx.doi.org/.
Stojiljković, B., Vasov, L., Mitrović, ., & Cvetković, D.
(2009).
The Application of the Root Locus Method for the Design of Pitch Controller of an F-104A Aircraft.
Strojniški vestnik - Journal of Mechanical Engineering, 55(9), 555-560.
doi:http://dx.doi.org/
@article{.,
	author = {Branimir  Stojiljković and Ljubiša  Vasov and Časlav  Mitrović and Dragan  Cvetković},
	title = {The Application of the Root Locus Method for the Design of Pitch Controller of an F-104A Aircraft},
	journal = {Strojniški vestnik - Journal of Mechanical Engineering},
	volume = {55},
	number = {9},
	year = {2009},
	keywords = {controller synthesis; root locus; stability derivatives; longitudinal dynamic stability; },
	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 Single 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.},
	issn = {0039-2480},	pages = {555-560},	doi = {},
	url = {https://www.sv-jme.eu/sl/article/the-application-of-the-root-locus-method-for-the-design-of-pitch-controller-of-an-f-104a-aircraft/}
}
Stojiljković, B.,Vasov, L.,Mitrović, .,Cvetković, D.
2009 August 55. The Application of the Root Locus Method for the Design of Pitch Controller of an F-104A Aircraft. Strojniški vestnik - Journal of Mechanical Engineering. [Online] 55:9
%A Stojiljković, Branimir 
%A Vasov, Ljubiša 
%A Mitrović, Časlav 
%A Cvetković, Dragan 
%D 2009
%T The Application of the Root Locus Method for the Design of Pitch Controller of an F-104A Aircraft
%B 2009
%9 controller synthesis; root locus; stability derivatives; longitudinal dynamic stability; 
%! The Application of the Root Locus Method for the Design of Pitch Controller of an F-104A Aircraft
%K controller synthesis; root locus; stability derivatives; longitudinal dynamic stability; 
%X 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 Single 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.
%U https://www.sv-jme.eu/sl/article/the-application-of-the-root-locus-method-for-the-design-of-pitch-controller-of-an-f-104a-aircraft/
%0 Journal Article
%R 
%& 555
%P 6
%J Strojniški vestnik - Journal of Mechanical Engineering
%V 55
%N 9
%@ 0039-2480
%8 2017-08-21
%7 2017-08-21
Stojiljković, Branimir, Ljubiša  Vasov, Časlav  Mitrović, & Dragan  Cvetković.
"The Application of the Root Locus Method for the Design of Pitch Controller of an F-104A Aircraft." Strojniški vestnik - Journal of Mechanical Engineering [Online], 55.9 (2009): 555-560. Web.  11 Nov. 2019
TY  - JOUR
AU  - Stojiljković, Branimir 
AU  - Vasov, Ljubiša 
AU  - Mitrović, Časlav 
AU  - Cvetković, Dragan 
PY  - 2009
TI  - The Application of the Root Locus Method for the Design of Pitch Controller of an F-104A Aircraft
JF  - Strojniški vestnik - Journal of Mechanical Engineering
DO  - 
KW  - controller synthesis; root locus; stability derivatives; longitudinal dynamic stability; 
N2  - 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 Single 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.
UR  - https://www.sv-jme.eu/sl/article/the-application-of-the-root-locus-method-for-the-design-of-pitch-controller-of-an-f-104a-aircraft/
@article{{}{.},
	author = {Stojiljković, B., Vasov, L., Mitrović, ., Cvetković, D.},
	title = {The Application of the Root Locus Method for the Design of Pitch Controller of an F-104A Aircraft},
	journal = {Strojniški vestnik - Journal of Mechanical Engineering},
	volume = {55},
	number = {9},
	year = {2009},
	doi = {},
	url = {https://www.sv-jme.eu/sl/article/the-application-of-the-root-locus-method-for-the-design-of-pitch-controller-of-an-f-104a-aircraft/}
}
TY  - JOUR
AU  - Stojiljković, Branimir 
AU  - Vasov, Ljubiša 
AU  - Mitrović, Časlav 
AU  - Cvetković, Dragan 
PY  - 2017/08/21
TI  - The Application of the Root Locus Method for the Design of Pitch Controller of an F-104A Aircraft
JF  - Strojniški vestnik - Journal of Mechanical Engineering; Vol 55, No 9 (2009): Strojniški vestnik - Journal of Mechanical Engineering
DO  - 
KW  - controller synthesis, root locus, stability derivatives, longitudinal dynamic stability, 
N2  - 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 Single 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.
UR  - https://www.sv-jme.eu/sl/article/the-application-of-the-root-locus-method-for-the-design-of-pitch-controller-of-an-f-104a-aircraft/
Stojiljković, Branimir, Vasov, Ljubiša, Mitrović, Časlav, AND Cvetković, Dragan.
"The Application of the Root Locus Method for the Design of Pitch Controller of an F-104A Aircraft" Strojniški vestnik - Journal of Mechanical Engineering [Online], Volume 55 Number 9 (21 August 2017)

Avtorji

Inštitucije

  • University of Belgrade, Faculty of Transport and Traffic Engineering, Serbia
  • University of Belgrade, Faculty of Transport and Traffic Engineering, Serbia
  • University of Belgrade, Faculty of Mechanical Engineering, Serbia
  • University ''Singidunum'' Belgrade, Faculty of Informatics and Management, Serbia

Informacije o papirju

Strojniški vestnik - Journal of Mechanical Engineering 55(2009)9, 555-560

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 Single 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.

controller synthesis; root locus; stability derivatives; longitudinal dynamic stability;