Generalized Sizing Methodology for Hybrid Aircraft Using Integrated Performance Constraints

What is it about?

The paper presents a formal methodology with all necessary mathematical formulations to calculate the adequate sizing parameters of hybrid (fixed wing and VTOL) aircraft by analyzing the point-performance constraints in the 3 flying modes (i.e., rotorcraft, transition, and fixed-wing). The methodology is verified by estimating the sizing parameters of the Bell XV-15 tiltrotor aircraft with errors less than 3% when compared to the actual parameters.

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Why is it important?

This problem has received scant attention in the literature and the majority of the available studies have used a somewhat feasible, but not optimal approach to obtain the sizing parameters using traditional fixed-wing design methods and/or historical data. To resolve such limitation and provide a formal methodology to assist aircraft designers, the paper presents an efficient sizing design methodology for hybrid aircraft.