This work aims at establishing a design procedure applicable to hybrid-electric, full-electric, or conventional aircraft. Firstly, the author introduces a mathematical model to describe the dynamics of the propulsive system. Then, the effects associated with the new propulsive system introduced are measured. Methods already proposed in the literature are coupled with new methods proposed by the author in a unique workflow. In this way, the aeropropulsive effects, the weights, the fault-tolerance analysis, and the aircraft performance are estimated. The conceptual design chain proposed is divided into two different steps. The first one defines the constraints of the aircraft design space by estimating the point performance, while the second step is aimed at identifying aircraft performance through a simulation-based approach.