Investigation of the Dynamic Stability for a Light Aircraft

Samuel David Iyaghigba; Aminu Hamza; Andrew Ebiega Ogaga

doi:doi:10.11648/j.ajece.20180202.15

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Investigation of the Dynamic Stability for a Light Aircraft

Samuel David Iyaghigba, Aminu Hamza, Andrew Ebiega Ogaga

Published in American Journal of Electrical and Computer Engineering (Volume 2, Issue 2)

Received: 22 November 2018 Accepted: 11 December 2018 Published: 15 January 2019

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Abstract

The dynamic stability of a light aircraft is very crucial at all phases of flight. This may include takeoff, climb, cruise, loiter, descend and landing where the aircraft is subjected to intense pressure from aerodynamic forces and moments. Control surfaces and flight control systems are therefore, used to control and pilot the aircraft to safe flight. The dynamic behavior of the aircraft can be simulated if an appropriate model of the aircraft is generated with a view to predicting the amount of force required to control the actuators that would actuate the control surfaces and make the aircraft stable from a disturbance. In this research paper, the dynamic stability of a light aircraft called the Air Beetle (ABT- 18) was investigated where the geometry of the aircraft was inputted in Athena Vortex Lattice (AVL) Software using X downstream, Y outright wing and Z up coordinates. The objective was to investigate how stable the aircraft will be on the longitudinal and lateral directions respectively. A model of the aircraft was created with dimensionless aerodynamic coefficients based on trim flight condition of cruise speed 51.4m/s at 12,000ft altitude. The aircraft airframe configuration and specification was inputted in AVL and aerodynamic stability coefficients were produced. The simulation was carried out in the graphic environment of Matlab Simulink, where block models of the aircraft were formed. Thereafter, transfer functions were obtained from the solutions of the light aircraft equations of motions. Pole placement method was used to test the dynamic stability of the aircraft and it was found to be laterally stable on the longitudinal axis and longitudinally stable on the lateral axis. Thus, the dynamic stability controls of the aircraft were achieved in autopilot design by implementing PID controllers’ successive loops and it was found that the ABT-18 aircraft had satisfied the conditions necessary for longitudinal and lateral stabilities.

Published in	American Journal of Electrical and Computer Engineering (Volume 2, Issue 2)
DOI	10.11648/j.ajece.20180202.15
Page(s)	37-55
Creative Commons	This is an Open Access article, distributed under the terms of the Creative Commons Attribution 4.0 International License (http://creativecommons.org/licenses/by/4.0/), which permits unrestricted use, distribution and reproduction in any medium or format, provided the original work is properly cited.
Copyright	Copyright © The Author(s), 2019. Published by Science Publishing Group

Keywords

Air Beetle (ABT-18), Athena Vortex Lattice (AVL), Proportional, Integrator, Derivative, (PID) Controllers, Lateral, Longitudinal, Directional, Dynamic Stabilities

References

[1]	Ugozo, SO et al (2016) Revised Project specification modifications of ABT 18 Aircraft to ABT 18 UAV. Unpublished.
[2]	Konstantinos D., Valavanis K. P. & Piegl L. A. (2012), On Integrating Unmanned Aircraft Systems into the National Airspace System: Issues, Challenges, Operational Restrictions, Certification and Recommendations. Springer Dordrecht Heidelberg, London; New York.
[3]	Valavanis K. P. (2007) Advances in Unmanned Aerial Vehicles: State of the Art and the Road to Autonomy. Springer Dordrecht Heidelberg, London; New York.
[4]	Collinson R. P. G. (2003) Introduction to Avionics Systems. Springer Science and Business Media, New York.
[5]	Searle L. (1989) The Bombsight Ware: Nordern versus Sperry. IEEE.
[6]	Ian M. & Allan G S. (2003) Civil Avionics Systems. Professional Engineering Publishing Limited, London and Bury St Edmunds, UK
[7]	Robert Nelson, Flight Stability and Automatic Control, WCB/McGraw-Hill, Ohio, 1998.
[8]	Paul Dorman (2006) Study of the Aerodynamics of a Small UAV using AVL Software. http://www.viscerallogic.com/paul/works/AVL%20Report.pdf
[9]	M. V. Cook (2007). Flight Dynamics Principles. Elsevier Linacre House, Jordan Hill, Oxford.
[10]	“What is Matlab” http://cimss.ssec.wisc.edu/wxwise/class/aos340/spr00/whatismatlab.htm Accessed April 5, 2018.
[11]	“Control Tutorials for MATLAB and Simulink - Introduction: PID Controller Design“ http://ctms.engin.umich.edu/CTMS/index.php?example=Introduction&section=ControlPID Accessed April 5, 2018.
[12]	Jia H., “Guideline for AVD Avionics System Design,” Department of Aerospace Engineering, Cranfield University, 2014. Unpublished.
[13]	Alan C. Tribble, Steven P. Miller, and David L. Lempia (2007), Software Safety Analysis of a Flight Guidance System. Rockwell Collins, Inc., 400 Collins Rd, NE.

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APA Style

Samuel David Iyaghigba, Aminu Hamza, Andrew Ebiega Ogaga. (2019). Investigation of the Dynamic Stability for a Light Aircraft. American Journal of Electrical and Computer Engineering, 2(2), 37-55. https://doi.org/10.11648/j.ajece.20180202.15

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ACS Style

Samuel David Iyaghigba; Aminu Hamza; Andrew Ebiega Ogaga. Investigation of the Dynamic Stability for a Light Aircraft. Am. J. Electr. Comput. Eng. 2019, 2(2), 37-55. doi: 10.11648/j.ajece.20180202.15

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AMA Style

Samuel David Iyaghigba, Aminu Hamza, Andrew Ebiega Ogaga. Investigation of the Dynamic Stability for a Light Aircraft. Am J Electr Comput Eng. 2019;2(2):37-55. doi: 10.11648/j.ajece.20180202.15

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@article{10.11648/j.ajece.20180202.15,
  author = {Samuel David Iyaghigba and Aminu Hamza and Andrew Ebiega Ogaga},
  title = {Investigation of the Dynamic Stability for a Light Aircraft},
  journal = {American Journal of Electrical and Computer Engineering},
  volume = {2},
  number = {2},
  pages = {37-55},
  doi = {10.11648/j.ajece.20180202.15},
  url = {https://doi.org/10.11648/j.ajece.20180202.15},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ajece.20180202.15},
  abstract = {The dynamic stability of a light aircraft is very crucial at all phases of flight. This may include takeoff, climb, cruise, loiter, descend and landing where the aircraft is subjected to intense pressure from aerodynamic forces and moments. Control surfaces and flight control systems are therefore, used to control and pilot the aircraft to safe flight. The dynamic behavior of the aircraft can be simulated if an appropriate model of the aircraft is generated with a view to predicting the amount of force required to control the actuators that would actuate the control surfaces and make the aircraft stable from a disturbance. In this research paper, the dynamic stability of a light aircraft called the Air Beetle (ABT- 18) was investigated where the geometry of the aircraft was inputted in Athena Vortex Lattice (AVL) Software using X downstream, Y outright wing and Z up coordinates. The objective was to investigate how stable the aircraft will be on the longitudinal and lateral directions respectively. A model of the aircraft was created with dimensionless aerodynamic coefficients based on trim flight condition of cruise speed 51.4m/s at 12,000ft altitude. The aircraft airframe configuration and specification was inputted in AVL and aerodynamic stability coefficients were produced. The simulation was carried out in the graphic environment of Matlab Simulink, where block models of the aircraft were formed. Thereafter, transfer functions were obtained from the solutions of the light aircraft equations of motions. Pole placement method was used to test the dynamic stability of the aircraft and it was found to be laterally stable on the longitudinal axis and longitudinally stable on the lateral axis. Thus, the dynamic stability controls of the aircraft were achieved in autopilot design by implementing PID controllers’ successive loops and it was found that the ABT-18 aircraft had satisfied the conditions necessary for longitudinal and lateral stabilities.},
 year = {2019}
}

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TY  - JOUR
T1  - Investigation of the Dynamic Stability for a Light Aircraft
AU  - Samuel David Iyaghigba
AU  - Aminu Hamza
AU  - Andrew Ebiega Ogaga
Y1  - 2019/01/15
PY  - 2019
N1  - https://doi.org/10.11648/j.ajece.20180202.15
DO  - 10.11648/j.ajece.20180202.15
T2  - American Journal of Electrical and Computer Engineering
JF  - American Journal of Electrical and Computer Engineering
JO  - American Journal of Electrical and Computer Engineering
SP  - 37
EP  - 55
PB  - Science Publishing Group
SN  - 2640-0502
UR  - https://doi.org/10.11648/j.ajece.20180202.15
AB  - The dynamic stability of a light aircraft is very crucial at all phases of flight. This may include takeoff, climb, cruise, loiter, descend and landing where the aircraft is subjected to intense pressure from aerodynamic forces and moments. Control surfaces and flight control systems are therefore, used to control and pilot the aircraft to safe flight. The dynamic behavior of the aircraft can be simulated if an appropriate model of the aircraft is generated with a view to predicting the amount of force required to control the actuators that would actuate the control surfaces and make the aircraft stable from a disturbance. In this research paper, the dynamic stability of a light aircraft called the Air Beetle (ABT- 18) was investigated where the geometry of the aircraft was inputted in Athena Vortex Lattice (AVL) Software using X downstream, Y outright wing and Z up coordinates. The objective was to investigate how stable the aircraft will be on the longitudinal and lateral directions respectively. A model of the aircraft was created with dimensionless aerodynamic coefficients based on trim flight condition of cruise speed 51.4m/s at 12,000ft altitude. The aircraft airframe configuration and specification was inputted in AVL and aerodynamic stability coefficients were produced. The simulation was carried out in the graphic environment of Matlab Simulink, where block models of the aircraft were formed. Thereafter, transfer functions were obtained from the solutions of the light aircraft equations of motions. Pole placement method was used to test the dynamic stability of the aircraft and it was found to be laterally stable on the longitudinal axis and longitudinally stable on the lateral axis. Thus, the dynamic stability controls of the aircraft were achieved in autopilot design by implementing PID controllers’ successive loops and it was found that the ABT-18 aircraft had satisfied the conditions necessary for longitudinal and lateral stabilities.
VL  - 2
IS  - 2
ER  -

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Author Information

Samuel David Iyaghigba

Aircraft Engineering Department, Air Force Institute of Technology, Kaduna, Nigeria
Aminu Hamza

Aircraft Engineering Department, Air Force Institute of Technology, Kaduna, Nigeria
Andrew Ebiega Ogaga

Aircraft Engineering Department, Air Force Institute of Technology, Kaduna, Nigeria

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APA Style

Samuel David Iyaghigba, Aminu Hamza, Andrew Ebiega Ogaga. (2019). Investigation of the Dynamic Stability for a Light Aircraft. American Journal of Electrical and Computer Engineering, 2(2), 37-55. https://doi.org/10.11648/j.ajece.20180202.15

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ACS Style

Samuel David Iyaghigba; Aminu Hamza; Andrew Ebiega Ogaga. Investigation of the Dynamic Stability for a Light Aircraft. Am. J. Electr. Comput. Eng. 2019, 2(2), 37-55. doi: 10.11648/j.ajece.20180202.15

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AMA Style

Samuel David Iyaghigba, Aminu Hamza, Andrew Ebiega Ogaga. Investigation of the Dynamic Stability for a Light Aircraft. Am J Electr Comput Eng. 2019;2(2):37-55. doi: 10.11648/j.ajece.20180202.15

Copy | Download

@article{10.11648/j.ajece.20180202.15,
  author = {Samuel David Iyaghigba and Aminu Hamza and Andrew Ebiega Ogaga},
  title = {Investigation of the Dynamic Stability for a Light Aircraft},
  journal = {American Journal of Electrical and Computer Engineering},
  volume = {2},
  number = {2},
  pages = {37-55},
  doi = {10.11648/j.ajece.20180202.15},
  url = {https://doi.org/10.11648/j.ajece.20180202.15},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ajece.20180202.15},
  abstract = {The dynamic stability of a light aircraft is very crucial at all phases of flight. This may include takeoff, climb, cruise, loiter, descend and landing where the aircraft is subjected to intense pressure from aerodynamic forces and moments. Control surfaces and flight control systems are therefore, used to control and pilot the aircraft to safe flight. The dynamic behavior of the aircraft can be simulated if an appropriate model of the aircraft is generated with a view to predicting the amount of force required to control the actuators that would actuate the control surfaces and make the aircraft stable from a disturbance. In this research paper, the dynamic stability of a light aircraft called the Air Beetle (ABT- 18) was investigated where the geometry of the aircraft was inputted in Athena Vortex Lattice (AVL) Software using X downstream, Y outright wing and Z up coordinates. The objective was to investigate how stable the aircraft will be on the longitudinal and lateral directions respectively. A model of the aircraft was created with dimensionless aerodynamic coefficients based on trim flight condition of cruise speed 51.4m/s at 12,000ft altitude. The aircraft airframe configuration and specification was inputted in AVL and aerodynamic stability coefficients were produced. The simulation was carried out in the graphic environment of Matlab Simulink, where block models of the aircraft were formed. Thereafter, transfer functions were obtained from the solutions of the light aircraft equations of motions. Pole placement method was used to test the dynamic stability of the aircraft and it was found to be laterally stable on the longitudinal axis and longitudinally stable on the lateral axis. Thus, the dynamic stability controls of the aircraft were achieved in autopilot design by implementing PID controllers’ successive loops and it was found that the ABT-18 aircraft had satisfied the conditions necessary for longitudinal and lateral stabilities.},
 year = {2019}
}

Copy | Download

TY  - JOUR
T1  - Investigation of the Dynamic Stability for a Light Aircraft
AU  - Samuel David Iyaghigba
AU  - Aminu Hamza
AU  - Andrew Ebiega Ogaga
Y1  - 2019/01/15
PY  - 2019
N1  - https://doi.org/10.11648/j.ajece.20180202.15
DO  - 10.11648/j.ajece.20180202.15
T2  - American Journal of Electrical and Computer Engineering
JF  - American Journal of Electrical and Computer Engineering
JO  - American Journal of Electrical and Computer Engineering
SP  - 37
EP  - 55
PB  - Science Publishing Group
SN  - 2640-0502
UR  - https://doi.org/10.11648/j.ajece.20180202.15
AB  - The dynamic stability of a light aircraft is very crucial at all phases of flight. This may include takeoff, climb, cruise, loiter, descend and landing where the aircraft is subjected to intense pressure from aerodynamic forces and moments. Control surfaces and flight control systems are therefore, used to control and pilot the aircraft to safe flight. The dynamic behavior of the aircraft can be simulated if an appropriate model of the aircraft is generated with a view to predicting the amount of force required to control the actuators that would actuate the control surfaces and make the aircraft stable from a disturbance. In this research paper, the dynamic stability of a light aircraft called the Air Beetle (ABT- 18) was investigated where the geometry of the aircraft was inputted in Athena Vortex Lattice (AVL) Software using X downstream, Y outright wing and Z up coordinates. The objective was to investigate how stable the aircraft will be on the longitudinal and lateral directions respectively. A model of the aircraft was created with dimensionless aerodynamic coefficients based on trim flight condition of cruise speed 51.4m/s at 12,000ft altitude. The aircraft airframe configuration and specification was inputted in AVL and aerodynamic stability coefficients were produced. The simulation was carried out in the graphic environment of Matlab Simulink, where block models of the aircraft were formed. Thereafter, transfer functions were obtained from the solutions of the light aircraft equations of motions. Pole placement method was used to test the dynamic stability of the aircraft and it was found to be laterally stable on the longitudinal axis and longitudinally stable on the lateral axis. Thus, the dynamic stability controls of the aircraft were achieved in autopilot design by implementing PID controllers’ successive loops and it was found that the ABT-18 aircraft had satisfied the conditions necessary for longitudinal and lateral stabilities.
VL  - 2
IS  - 2
ER  -

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