Electric Multirotor Propulsion System Optimization for Mission Objectives

This paper describes a proposed method for the design of a propulsion system of generic single and multirotor vehicles. With this methodology, a designer is able to generate a vehicle that will be capable of completing a specific mission. The method allows for optimization of drive components in terms of physical parameters such as total weight, minimum wing chord, propeller pitch, etc. The considered propulsion system components are motors, propellers, batteries, and electronic speed controllers (ESCs) and associated drive wiring. The study considers battery powered vehicles, although, with simple modifications, the method remains valid for other electrical energy sources. The method is generic enough to apply to both standard and non-standard vehicle configurations. The method’s output is a set of propulsion system parameters, and chassis parameters when applicable, that will accomplish a specific mission. A vehicle may be sized for lightest gross takeoff weight (GTOW), smallest wing, highest efficiency or climb rates, and/or other performance goals, depending on the desired objective(s).