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Abstract
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). This paper identifies the parameters of electric multirotor propulsion systems which are important to a design with respect to completing a mission. The broader study also provides physical and electrical characterizations of propulsion system components. The results of the study indicate that using this proposed methodology has several benefits. A methodical attempt can be made to guarantee that a vehicle can accomplish a particular mission. The method provides at least a theoretically valid starting point for the design. Should a less rigorous method be replaced by the proposed, a reduction in wasted resources is possible due to less required redesigns. The proposed propulsion design methodology has been employed on several vehicles, including the winner of the 2015 AHS Micro Air Vehicle Challenge in VA Beach, VA. Other vehicles include the Georgia Institute of Technology’s entry to the International Aerial Robotics Competition for 2016 as well as general lab aircraft. The optimization of a propulsion system, with attention paid to the battery configuration, is also presented for a ”long” endurance vehicle. Momentum theory is used to analyze the battery weight fraction chosen for these two and other vehicles.

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  Electric Multirotor Propulsion System Optimization for Mission Objectives

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