Hostname: page-component-78c5997874-mlc7c Total loading time: 0 Render date: 2024-11-02T21:04:41.408Z Has data issue: false hasContentIssue false
  • English
  • Français

Derivation of structural weight estimation for Unmanned Combat Aerial Vehicle (UCAV)

Published online by Cambridge University Press:  11 November 2021

A. Panahi ,
M. A. Vaziri Zanjani Open the ORCID record for M. A. Vaziri Zanjani [Opens in a new window] ,
Sh. Yousefi ,
N. Fazli  and
J. Aarabi
A. Panahi
Affiliation:
Department of Mechanical & Aerospace Engineering, Malek-e-Ashtar University, Shahin Shahr, Isfahan, Islamic Republic of Iran
M. A. Vaziri Zanjani*
Affiliation:
Department of Mechanical & Aerospace Engineering, Malek-e-Ashtar University, Shahin Shahr, Isfahan, Islamic Republic of Iran
Sh. Yousefi
Affiliation:
Department of Mechanical & Aerospace Engineering, Malek-e-Ashtar University, Shahin Shahr, Isfahan, Islamic Republic of Iran
N. Fazli
Affiliation:
Department of Mechanical & Aerospace Engineering, Malek-e-Ashtar University, Shahin Shahr, Isfahan, Islamic Republic of Iran
J. Aarabi
Affiliation:
Department of Mechanical & Aerospace Engineering, Malek-e-Ashtar University, Shahin Shahr, Isfahan, Islamic Republic of Iran
*
E-mail: [email protected]
Get access Rights & Permissions [Opens in a new window]

Abstract

Estimation of the structural weight of an Unmanned Combat Aerial Vehicle (UCAV) during conceptual design has proven to be a significant challenge mainly due to its unconventional configuration. We investigate development of a customised approach for structural weight estimation of UCAV based on statistical weight of the manned fighter’s components by applying minor modifications on weight formulations of fuselage, wing, empennage, power plant and landing gear. The modifications are applied by considering the corresponding differences between manned fighters and UCAVs such as manned requirements and mission variances. Some new empirical formulas for estimating the weight of UCAV’s components are proposed. Results for the empty weight estimation are validated against actual values of some well-known UCAVs. Moreover, the structural weight is validated against the benchmark UCAV case studies. The results show that the ratio of structural to takeoff weight for UCAVs is approximately between 20% to 10%. Finally, a generalised equation is developed for estimating the structural weight of UCAVs in conceptual design phase.

Keywords

Conceptual designLambda wing aircraftStructural weightUCAVWeight estimation
Type
Research Article
Information
The Aeronautical Journal , Volume 126 , Issue 1299 , May 2022 , pp. 813 - 829
Check for updates
Copyright
© The Author(s), 2021. Published by Cambridge University Press on behalf of Royal Aeronautical Society

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

Essari, A. “Estimation of Component Design Weights in Conceptual Design Phase for Tactical Uavs”, PhD thesis, university of Belgrade, 2015.Google Scholar
Wang, G. “Key Parameters and Conceptual Configuration of Unmanned Combat Aerial Vehicle Concept”, Chinese Journal of Aeronautics, 2009, 22, pp 393–400.Google Scholar
Roskam, J. “Airplane Design Part V: Component Weight Estimation”, Roskam Aviation and Engineering Corporation, Ottawa (1985).Google Scholar
Nicolai, L.M. and Carichner, G.E. “Fundamentals of aircraft and airship design, Appendix I, aircraft weights data”, 2010.Google Scholar
Sadraey, M.H. “Aircraft Design, A Systems Engineering Approach”, A. John Wiley & Sons, Ltd., Publication, 2013.Google Scholar
Howe, D. “The prediction of aircraft wing mass,” Proceedings of the Institution of Mechanical Engineers, 1996, 210, pp 135–145.CrossRefGoogle Scholar
Essari, A.M. “Estimation Of Empennage Design Weight In Conceptual Design Phase For Tactical Uavs”, Proceedings of First Conference for Engineering Sciences and Technology (CEST-2018), vol. 2Google Scholar
Carsten, M., Cummings, R.M., Schüttea, A., Vormwega, J., Mayec, R.G. and Jeansc, T.L. “Multi-disciplinary design and performance assessment of effective, agile NATO air vehicles”, Aerospace Science and Technology, Available at: DOI 10.1016/j.ast.2020.105764, 2020.Google Scholar
Liersch, C.M. and Bishop, G. “Conceptual Design of a 53deg Swept Flying Wing UCAV Configuration”, AIAA AVIATION Forum, June 25-29, 2018, Atlanta, Georgia.Google Scholar
Voss, A. and Klimmek, T. “Design and Sizing on a Parametric Structural Model for a UCAV Configuration for Loads and Aeroelastic Analysis”, CEAS Aeronautical Journal, 2016, DOI 10.1007/s13272-016-0223-2.Google Scholar
Levy, A., Katz, M., Katzuni, O., Konevsky, A., Frumkin, J., Buium, T. et al. “Final Report, Project 7–8: Team Cerberus – UCAV”, 2009, Haifa, Israel.Google Scholar
Beltramo, M.N.T. “Parametric study of transport aircraft systems cost and weight”, 1977.Google Scholar
Valencia, E.A. “Weight assessment for a blended wing Body-Unmanned aerial vehicle implementing boundary layer ingestion”, CMSME 2018.Google Scholar
Ferguson, M., Magnuson, M., Fridley, C. and Taha, H. “X-47 A/B”, [online], URL: http://www.dept.aoe.vt.edu/~mason/Mason_f/X47Spr11.pdf, [Cited 01 September 2021].Google Scholar
“X-45A Configuration” [online], URL: https://www.secretprojects.co.uk/attachments/x-45a-1-jpg.18703/, [Cited 01 September 2021].Google Scholar
Dassault nEUROn UCAV [online], URL: https://aermech.com/dassault-neuron-ucavunmanned-combat-air- vehicledemonstrator-wiki/, [Cited 01 September 2021].Google Scholar
“X-45B Configuration” [online], URL: https://www.secretprojects.co.uk/attachments/x-45b-2-jpg.18709/ [Cited 01 September 2021].Google Scholar
“X-45C Configuration” [online], URL: https://www.secretprojects.co.uk/attachments/x45c-1-jpg.18693/, [Cited 01 September 2021].Google Scholar
Nilsuwan, S., “Uninhabited Aircraft Design Optimized for Close Formation Air-Refuelling Flight”, Imperial College London, PhD thesis, 2010.Google Scholar
Roskam, J. “Aircraft Design. Part 1. Preliminary sizing of aircraft”, 1989.Google Scholar
Çakin, U. “Conceptual Design of A Stealth Unmanned Combat Aerial Vehicle with Multidisciplinary Design Optimization”, Middle East Technical University, 2018.Google Scholar
“F404 turbofan engines datasheet”, GE Aviation, Cincinnati, Ohio 45215 U.S.A, [online] URL:https://www.geaviation.com/ sites/default/files/datasheet-F404-Family.pdf, [Cited 15 March 2020].Google Scholar
“Pratt & Whitney F100-PW-220 Engine Characteristics”, [online] URL: http://usfighter.tripod.com/F100-PW-220, [Cited 15 March 2020].Google Scholar
“Engine Specifications: Rolls-Royce Turbomeca Adour”, [online], URL: http://www.fi-powerweb.com/Engine/Rolls-Royce- F405-Adour, [Cited 15 March 2020].Google Scholar
“Pratt & Whitney Canada JT15D data sheet”, Forecast International, September 2012, [online], URL: https://www.forecastinternational.com/archive/Pratt& Whitney Canada JT15D, [Cited 15 March 2020].Google Scholar
Daly, M. and Gunston, B. HIS, “Jane’s Aero-Engines 2012-2013”, Ihs Global Incorporated, London.Google Scholar
European Aviation Safety Agency (ed.): Certification specifications for normal, utility, aerobatic, and commuter category aeroplanes CS-23. Amendment 3 (2012)Google Scholar
Liebeck, R.H. “Design of the Blended Wing Body Subsonic Transport”, J. Aircr., 2004, 41, pp 10–25.CrossRefGoogle Scholar
Gundlach, J. “Designing Unmanned Aircraft Systems: A Comprehensive Approach”, Published by the American Institute of Aeronautics and Astronautics, Inc. 2012.Google Scholar