This research paper presents a methodology for optimizing the performance of an electrically powered general aviation aircraft through nonlinear dynamic flight simulations. In comparison to conventionally powered airborne systems, the electric aircraft domain offers a substantially expanded set of design variables and architectural options, resulting in a high-dimensional configuration space. The proposed optimization framework systematically evaluates flight performance over a broad range of configurations and parameter variations to identify the most suitable combination while considering optimization goals such as the maximization of mission range. The process incorporates an integrated requirements management and traceability toolchain to ensure that all considered configuration variants remain compliant with relevant airworthiness and certification standards. Multiple certification-relevant requirements are validated through dedicated test and analysis activities embedded within the workflow. The study demonstrates the practical application of the proposed optimization and requirements-validation toolchain using an electric motor glider as a representative testbed vehicle.     «

This research paper presents a methodology for optimizing the performance of an electrically powered general aviation aircraft through nonlinear dynamic flight simulations. In comparison to conventionally powered airborne systems, the electric aircraft domain offers a substantially expanded set of design variables and architectural options, resulting in a high-dimensional configuration space. The proposed optimization framework systematically evaluates flight performance over a broad range of co...     »