Sizing and Optimization of a Subscale VTOL Aircraft with COTS Components Using the PEACE Framework

Extensive subscale flight-testing is necessary for de-risking the development and validation of novel and/or unconventional vertical takeoff and landing concepts, in particular those that transition between vertical and forward flight modes. In this work, a sizing and optimization workflow is demonstrated for rapidly-producible, cost-effective subscale prototypes that utilize commercially off-the-shelf components and additive manufacturing. The Parametric Energy-based Aircraft Configuration Evaluator framework is used, and all-electric and hybrid-electric variants of a tandem tiltwing configuration are considered as examples. Weight estimation relationships developed for carbon fiber and 3-D printed components and available, estimated, or measured performance characteristics of batteries, motors, propellers, and other system components were incorporated into the framework, which was configured to size the vehicle using only available off-the-shelf components. Optimization was performed using the Non-Dominated Sorting Algorithm II genetic algorithm for both all-electric and hybrid-electric designs with four and eight propulsors. The results yielded lighter all-electric designs with shorter flight time and heavier hybrid-electric designs with extended flight time.