Initial Weight Estimate of Advanced Transport Aircraft Concepts Considering Aeroelastic Effects

Abstract

This paper presents a semi-empirical method for the weight estimation of advanced transport aircraft concepts in early design stages. The aircraft weight is estimated according to four component groups with different sizing drivers. Emphasis is placed on the wing weight estimation considering aeroelastic effects. A physics-based wing weight estimation tool is used in a Design of Experiments and the results are applied in a least-squares regression obtaining wing Weight Estimating Relationships (WERs). Typical parameters covering a wide design space are considered so the method is applicable to business jets, regional turboprops, short-range and long-range transport aircraft. The WERs equations are presented in typical handbook form for simple application. Static aeroelastic loads, aileron efficiency and aeroelastic divergence effects on the wing weight are considered. Equations are presented for conventional transport aircraft, forward swept wing, strut-braced wing, and forward-swept strut-braced wing concepts. The WERs are applicable to aluminum or carbon-fiber reinforced plastic wings. The equations are verified for accuracy with available designs and the sensitivities are checked against the weights tool used to generate them. Application of the method in a simple design study illustrates its usefulness in quickly assessing different concepts for a set of requirements.