Configuration Design and Optimization Study on Compound Gyroplane

Abstract

A conceptual design and optimization study has been performed to obtain the configuration and weight of a compound gyroplane. A study of research trends and characteristics was performed to develop the compound gyroplane sizing program. Based on these results, the sizing program has been developed and its suitability has been validated using existing aircraft data. The target for validation was a Challis Heliplane UAV, Carter Copter, FB-1 Gyrodyne, and Jet Gyrodyne. The program was suitable to size a compound gyroplane at the conceptual design phase, because the greatest error rate was less than 10%. Through this sizing program, the performance analysis program has been developed, and then optimization was performed using those programs. The objective was to reduce the total gross weight (TOGW), the design variables were the rotor lift sharing factor (N) and the ratio of the wing span and rotor diameter (Bw/DMR), and the design constraints were the loft to drag ratio, cruise minimum speed, and fuel weight. According to the result of optimization, the TOGW of all four kinds of compound gyroplanes was reduced.