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

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.

Conceptual Design of a Nonconstant Swept Flying Wing Unmanned Combat Aerial Vehicle

“…The initial estimation for the weight components was obtained using the statistical coefficients excluding the fuel weight. The duration performance level was preliminary computed according to engine performance data [5,58,59].…”

“…The small diameter bombs with a mass of approximately 100 to 500 kg such as GBU-16, EGBU-16, GBU-32, GBU-38 and GBU-39 and GBU-55 are typical for miniaturized air-to-ground missiles and bombs that are adapted to the concealed armament UCAVs. Payloads vary from 400 up to 2000 kg [6,56,59], and thus the payload weight (𝑊 𝑃𝑎𝑦𝑙𝑜𝑎𝑑 ) of UCAV is initially kept as 1050 kg.…”