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Airplanes have been expected as a new platform for Mars exploration. This paper presents conceptual design results of a Mars airplane for various entry capsule diameters, payload mass, and flight range. The conceptual design method includes considerations of the deployment mechanism using hinges and aerodynamic characteristics at low Reynolds number. The results reveal a relation among total mass of the airplane, entry capsule size, payload mass, and flight range. When the total mass and entry capsule diameter are fixed, the flight range is expressed as a linear function of the payload mass with negative slope. When the entry capsule diameter and the payload mass are fixed, optimal total mass from the viewpoint of the flight range is found for each entry capsule diameter. Finally a specification of the airplane at the optimal total mass is shown. An airplane weighing 34.0 kg shows a maximum range of 370 km under the conditions of an aeroshell diameter of 3 m and a payload mass of 3 kg.

A Parametric Study of Mars Airplane Concept for Science Mission on Mars