Overall parameter design method and sensitivity analysis for solar aircraft

This paper establishes the overall parameter model for solar aircraft based on energy balance constraints and mass balance constraints. On this basis, a method for the overall parameter design considering the feasible design domain is proposed, with the aircraft’s total mass and wing area as optimization objectives. Sensitivity analysis and scenario study of the optimal configuration of solar-powered aircraft under various general parameters during the design process is conducted. Finally, a design scheme is introduced and compared with prototype data. The results verify the practical applicability of the scheme. The method proposed in this article can provide a reference for the conceptual design stage of solar aircraft.