An Investigation of the Longitudinal Dynamic Stability of a Box-Wing Aircraft

Paul Olugbeji Jemitola; Paul Peter Okonkwo

doi:doi:10.11648/j.ijmea.20210905.12

| Peer-Reviewed

An Investigation of the Longitudinal Dynamic Stability of a Box-Wing Aircraft

Paul Olugbeji Jemitola, Paul Peter Okonkwo

Published in International Journal of Mechanical Engineering and Applications (Volume 9, Issue 5)

Received: 19 October 2021 Accepted: 15 November 2021 Published: 27 November 2021

Views: Downloads:

Download PDF

Share This Article

Twitter
Linked In
Facebook

Abstract

This study was undertaken to identify the longitudinal dynamic characteristics of the Box-Wing Aircraft. Research on the Box Wing aircraft gained traction following increasing demand for an environmental friendly aircraft that would reduce noise and pollutant emissions. The Box-Wing Aircraft is renowned for its potential aerodynamics advantages over conventional aircraft. However, due to its departure from conventional configuration, the stability dynamics of the Box Wing has not been fully explored. This study investigates the longitudinal dynamic stability characteristics of a Box Wing Aircraft at the conceptual design level using the J2 Aircraft Dynamics Software. The study integrates empirical mass estimation methods and aerodynamic data generated from a vortex lattice tool into J2 Aircraft Dynamics Software Suite. This was done to assess the Short Period Oscillation and Phugoid responses of a Box Wing Aircraft and a conventional cantilever wing aircraft. For a 2s step input, the short period oscillation induced on the Box Wing was damped out after 19s resulting in damping ratio of 0.68 and the undamped natural frequency is 1.8 rad/s. In the Phugoid mode, the Box Wing Aircraft gives a damping ratio of 0.006 and undamped natural frequency of 0.07 rad/s. On the other hand, the SPO induced on the reference conventional aircraft settles after 14s producing a damping ratio of 0.76 and undamped natural frequency of 3.12 rad/s. The damping ratio and undamped natural frequency for the Phugoid mode of the reference conventional aircraft were however 0.001 and 0.07 rad/s respectively. These results indicate that the reference conventional cantilever wing aircraft possesses acceptable longitudinal dynamic stability characteristics while the Box Wing Aircraft would require stability augmentation systems to improve its flying and handling qualities.

Published in	International Journal of Mechanical Engineering and Applications (Volume 9, Issue 5)
DOI	10.11648/j.ijmea.20210905.12
Page(s)	79-84
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), 2021. Published by Science Publishing Group

Keywords

Longitudinal, Dynamics, Stability, Box-Wing

References

[1]	J. Jeffery: “J2 Universal Aircraft Dynamics Software Suite.” J2 Aircraft Dynamics Ltd, (2010).
[2]	P. O Jemitola: Conceptual Design and Optimisation Methodology for Box Wing Aircraft, School of Aerospace Engineering, Department of Aerospace Engineering, Cranfield University, Cranfield, (2012).
[3]	L. Jenkinson, D. Rhodes and P. Simpkin: Civil Jet Aircraft Design. Arnold Publishers, UK, (1999).
[4]	P. O. Jemitola, J. Fielding and G. Monterzino: ‘Wing Mass Estimation Algorithm for Medium Range Box Wing Aircraft’, Aeronautical Journal, (2013).
[5]	L. Jenkinson and J. F. Marchman: Aircraft Design Projects for Engineering Students, Oxford, UK: Elsevier Butterworth-Heinemann and AIAA, (2003).
[6]	C. Matthews: Aeronautical Engineers Data Book, Oxford, UK: Elsevier Butterworth Heinemann, (2002).
[7]	E. Bruhn: Analysis and Design of Flight Vehicle Structures. Indianapolis, USA: SR Jacobs and Associates, (1973).
[8]	J. Roskam: Airplane Design: Part VI - Preliminary Calculation of Aerodynamic, Thrust and Power Characteristics. Roskam Aviation and Engineering Corporation, Kansas, USA, (1990).
[9]	ESDU: “Rate of change of lift coefficient with control deflection for full-span plain controls,” Tech. Rep. 74011, The Royal Aeronautical Society, March (1974).
[10]	ESDU: “Installed tailplane lift-curve slope at subsonic speeds,” Tech. Rep. 89029, The Royal Aeronautical Society, October (1989).
[11]	M. Hepperle: “Javafoil version 2.20 - 01.” http://www.mhaerotools.de/airfoils/javafoil.htm, December 2011. Accessed March (2010).
[12]	T. R. Yechout, T. D. Bossert and S. Morris: Introduction to aircraft flight mechanics: perfor- mance, static stability, dynamic stability and classical feedback control, American Institute of Aeronautics and Astronautics, Virginia, USA, (2003).
[13]	M. Cook: Flight Dynamics Principles, Elsevier Ltd, Oxford, UK, second edition ed., (2007).
[14]	Scholz, R and Caja, D. Box Wing Flight Dynamics in the Stage of Conceptual Aircraft Design. Hamburg University of Applied Sciences Aero – Aircraft Design and Systems Group, Deutscher Luftund Raumfahrtkongress 2012.
[15]	Urso, D and Martinez-val, R. Flight Dynamics of Flying Wings. 26^th International Congress of the Aeronautical Science, ICAS 2008.

Cite This Article

Plain Text BibTeX RIS

APA Style

Paul Olugbeji Jemitola, Paul Peter Okonkwo. (2021). An Investigation of the Longitudinal Dynamic Stability of a Box-Wing Aircraft. International Journal of Mechanical Engineering and Applications, 9(5), 79-84. https://doi.org/10.11648/j.ijmea.20210905.12

Copy | Download

ACS Style

Paul Olugbeji Jemitola; Paul Peter Okonkwo. An Investigation of the Longitudinal Dynamic Stability of a Box-Wing Aircraft. Int. J. Mech. Eng. Appl. 2021, 9(5), 79-84. doi: 10.11648/j.ijmea.20210905.12

Copy | Download

AMA Style

Paul Olugbeji Jemitola, Paul Peter Okonkwo. An Investigation of the Longitudinal Dynamic Stability of a Box-Wing Aircraft. Int J Mech Eng Appl. 2021;9(5):79-84. doi: 10.11648/j.ijmea.20210905.12

Copy | Download

@article{10.11648/j.ijmea.20210905.12,
  author = {Paul Olugbeji Jemitola and Paul Peter Okonkwo},
  title = {An Investigation of the Longitudinal Dynamic Stability of a Box-Wing Aircraft},
  journal = {International Journal of Mechanical Engineering and Applications},
  volume = {9},
  number = {5},
  pages = {79-84},
  doi = {10.11648/j.ijmea.20210905.12},
  url = {https://doi.org/10.11648/j.ijmea.20210905.12},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijmea.20210905.12},
  abstract = {This study was undertaken to identify the longitudinal dynamic characteristics of the Box-Wing Aircraft. Research on the Box Wing aircraft gained traction following increasing demand for an environmental friendly aircraft that would reduce noise and pollutant emissions. The Box-Wing Aircraft is renowned for its potential aerodynamics advantages over conventional aircraft. However, due to its departure from conventional configuration, the stability dynamics of the Box Wing has not been fully explored. This study investigates the longitudinal dynamic stability characteristics of a Box Wing Aircraft at the conceptual design level using the J2 Aircraft Dynamics Software. The study integrates empirical mass estimation methods and aerodynamic data generated from a vortex lattice tool into J2 Aircraft Dynamics Software Suite. This was done to assess the Short Period Oscillation and Phugoid responses of a Box Wing Aircraft and a conventional cantilever wing aircraft. For a 2s step input, the short period oscillation induced on the Box Wing was damped out after 19s resulting in damping ratio of 0.68 and the undamped natural frequency is 1.8 rad/s. In the Phugoid mode, the Box Wing Aircraft gives a damping ratio of 0.006 and undamped natural frequency of 0.07 rad/s. On the other hand, the SPO induced on the reference conventional aircraft settles after 14s producing a damping ratio of 0.76 and undamped natural frequency of 3.12 rad/s. The damping ratio and undamped natural frequency for the Phugoid mode of the reference conventional aircraft were however 0.001 and 0.07 rad/s respectively. These results indicate that the reference conventional cantilever wing aircraft possesses acceptable longitudinal dynamic stability characteristics while the Box Wing Aircraft would require stability augmentation systems to improve its flying and handling qualities.},
 year = {2021}
}

Copy | Download

TY  - JOUR
T1  - An Investigation of the Longitudinal Dynamic Stability of a Box-Wing Aircraft
AU  - Paul Olugbeji Jemitola
AU  - Paul Peter Okonkwo
Y1  - 2021/11/27
PY  - 2021
N1  - https://doi.org/10.11648/j.ijmea.20210905.12
DO  - 10.11648/j.ijmea.20210905.12
T2  - International Journal of Mechanical Engineering and Applications
JF  - International Journal of Mechanical Engineering and Applications
JO  - International Journal of Mechanical Engineering and Applications
SP  - 79
EP  - 84
PB  - Science Publishing Group
SN  - 2330-0248
UR  - https://doi.org/10.11648/j.ijmea.20210905.12
AB  - This study was undertaken to identify the longitudinal dynamic characteristics of the Box-Wing Aircraft. Research on the Box Wing aircraft gained traction following increasing demand for an environmental friendly aircraft that would reduce noise and pollutant emissions. The Box-Wing Aircraft is renowned for its potential aerodynamics advantages over conventional aircraft. However, due to its departure from conventional configuration, the stability dynamics of the Box Wing has not been fully explored. This study investigates the longitudinal dynamic stability characteristics of a Box Wing Aircraft at the conceptual design level using the J2 Aircraft Dynamics Software. The study integrates empirical mass estimation methods and aerodynamic data generated from a vortex lattice tool into J2 Aircraft Dynamics Software Suite. This was done to assess the Short Period Oscillation and Phugoid responses of a Box Wing Aircraft and a conventional cantilever wing aircraft. For a 2s step input, the short period oscillation induced on the Box Wing was damped out after 19s resulting in damping ratio of 0.68 and the undamped natural frequency is 1.8 rad/s. In the Phugoid mode, the Box Wing Aircraft gives a damping ratio of 0.006 and undamped natural frequency of 0.07 rad/s. On the other hand, the SPO induced on the reference conventional aircraft settles after 14s producing a damping ratio of 0.76 and undamped natural frequency of 3.12 rad/s. The damping ratio and undamped natural frequency for the Phugoid mode of the reference conventional aircraft were however 0.001 and 0.07 rad/s respectively. These results indicate that the reference conventional cantilever wing aircraft possesses acceptable longitudinal dynamic stability characteristics while the Box Wing Aircraft would require stability augmentation systems to improve its flying and handling qualities.
VL  - 9
IS  - 5
ER  -

Copy | Download

Author Information

Paul Olugbeji Jemitola

Department of Aerospace Engineering, Faculty of Air Engineering, Air Force Institute of Technology, Kaduna, Nigeria
Paul Peter Okonkwo

Department of Aerospace Engineering, Faculty of Air Engineering, Air Force Institute of Technology, Kaduna, Nigeria

Download PDF

Sections

Plain Text BibTeX RIS

APA Style

Paul Olugbeji Jemitola, Paul Peter Okonkwo. (2021). An Investigation of the Longitudinal Dynamic Stability of a Box-Wing Aircraft. International Journal of Mechanical Engineering and Applications, 9(5), 79-84. https://doi.org/10.11648/j.ijmea.20210905.12

Copy | Download

ACS Style

Paul Olugbeji Jemitola; Paul Peter Okonkwo. An Investigation of the Longitudinal Dynamic Stability of a Box-Wing Aircraft. Int. J. Mech. Eng. Appl. 2021, 9(5), 79-84. doi: 10.11648/j.ijmea.20210905.12

Copy | Download

AMA Style

Paul Olugbeji Jemitola, Paul Peter Okonkwo. An Investigation of the Longitudinal Dynamic Stability of a Box-Wing Aircraft. Int J Mech Eng Appl. 2021;9(5):79-84. doi: 10.11648/j.ijmea.20210905.12

Copy | Download

@article{10.11648/j.ijmea.20210905.12,
  author = {Paul Olugbeji Jemitola and Paul Peter Okonkwo},
  title = {An Investigation of the Longitudinal Dynamic Stability of a Box-Wing Aircraft},
  journal = {International Journal of Mechanical Engineering and Applications},
  volume = {9},
  number = {5},
  pages = {79-84},
  doi = {10.11648/j.ijmea.20210905.12},
  url = {https://doi.org/10.11648/j.ijmea.20210905.12},
  eprint = {https://article.sciencepublishinggroup.com/pdf/10.11648.j.ijmea.20210905.12},
  abstract = {This study was undertaken to identify the longitudinal dynamic characteristics of the Box-Wing Aircraft. Research on the Box Wing aircraft gained traction following increasing demand for an environmental friendly aircraft that would reduce noise and pollutant emissions. The Box-Wing Aircraft is renowned for its potential aerodynamics advantages over conventional aircraft. However, due to its departure from conventional configuration, the stability dynamics of the Box Wing has not been fully explored. This study investigates the longitudinal dynamic stability characteristics of a Box Wing Aircraft at the conceptual design level using the J2 Aircraft Dynamics Software. The study integrates empirical mass estimation methods and aerodynamic data generated from a vortex lattice tool into J2 Aircraft Dynamics Software Suite. This was done to assess the Short Period Oscillation and Phugoid responses of a Box Wing Aircraft and a conventional cantilever wing aircraft. For a 2s step input, the short period oscillation induced on the Box Wing was damped out after 19s resulting in damping ratio of 0.68 and the undamped natural frequency is 1.8 rad/s. In the Phugoid mode, the Box Wing Aircraft gives a damping ratio of 0.006 and undamped natural frequency of 0.07 rad/s. On the other hand, the SPO induced on the reference conventional aircraft settles after 14s producing a damping ratio of 0.76 and undamped natural frequency of 3.12 rad/s. The damping ratio and undamped natural frequency for the Phugoid mode of the reference conventional aircraft were however 0.001 and 0.07 rad/s respectively. These results indicate that the reference conventional cantilever wing aircraft possesses acceptable longitudinal dynamic stability characteristics while the Box Wing Aircraft would require stability augmentation systems to improve its flying and handling qualities.},
 year = {2021}
}

Copy | Download

TY  - JOUR
T1  - An Investigation of the Longitudinal Dynamic Stability of a Box-Wing Aircraft
AU  - Paul Olugbeji Jemitola
AU  - Paul Peter Okonkwo
Y1  - 2021/11/27
PY  - 2021
N1  - https://doi.org/10.11648/j.ijmea.20210905.12
DO  - 10.11648/j.ijmea.20210905.12
T2  - International Journal of Mechanical Engineering and Applications
JF  - International Journal of Mechanical Engineering and Applications
JO  - International Journal of Mechanical Engineering and Applications
SP  - 79
EP  - 84
PB  - Science Publishing Group
SN  - 2330-0248
UR  - https://doi.org/10.11648/j.ijmea.20210905.12
AB  - This study was undertaken to identify the longitudinal dynamic characteristics of the Box-Wing Aircraft. Research on the Box Wing aircraft gained traction following increasing demand for an environmental friendly aircraft that would reduce noise and pollutant emissions. The Box-Wing Aircraft is renowned for its potential aerodynamics advantages over conventional aircraft. However, due to its departure from conventional configuration, the stability dynamics of the Box Wing has not been fully explored. This study investigates the longitudinal dynamic stability characteristics of a Box Wing Aircraft at the conceptual design level using the J2 Aircraft Dynamics Software. The study integrates empirical mass estimation methods and aerodynamic data generated from a vortex lattice tool into J2 Aircraft Dynamics Software Suite. This was done to assess the Short Period Oscillation and Phugoid responses of a Box Wing Aircraft and a conventional cantilever wing aircraft. For a 2s step input, the short period oscillation induced on the Box Wing was damped out after 19s resulting in damping ratio of 0.68 and the undamped natural frequency is 1.8 rad/s. In the Phugoid mode, the Box Wing Aircraft gives a damping ratio of 0.006 and undamped natural frequency of 0.07 rad/s. On the other hand, the SPO induced on the reference conventional aircraft settles after 14s producing a damping ratio of 0.76 and undamped natural frequency of 3.12 rad/s. The damping ratio and undamped natural frequency for the Phugoid mode of the reference conventional aircraft were however 0.001 and 0.07 rad/s respectively. These results indicate that the reference conventional cantilever wing aircraft possesses acceptable longitudinal dynamic stability characteristics while the Box Wing Aircraft would require stability augmentation systems to improve its flying and handling qualities.
VL  - 9
IS  - 5
ER  -

Copy | Download