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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]
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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
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Copyright
© The Author(s), 2021. Published by Cambridge University Press on behalf of Royal Aeronautical Society

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