Conceptual Design of a Fixed-Wing UAV for Exploration of Titan

Titan, Saturn’s largest moon, offers the unusual pairing of Earth-like nitrogen atmosphere, high 1.5-bar surface density, and low 0.14 g gravity—environments well-suited both to efficient, long-range flight but also to cryogenic, chemically complex operations. Preceding missions, such as Cassini-Huygens, have mapped Titan from orbit and via a single descent probe, yet comprehensive in-situ coverage has not been realized. The majority of aerial mission concepts proposed to date have concentrated on balloons or rotorcraft with comparatively little exploration of fixed-wing performance in Titan conditions. This paper presents a first-cut design of a fixed-wing platform—Titan Atmospheric Navigation and Investigation System (TITANIS)—to bridge this gap. TITANIS is designed for multi-mission, such as low-altitude terrain imaging, stratified atmospheric sampling, and micro-probe deployment along methane-lake shorelines. Using Raymer’s sizing methods adapted to Titan’s 5.4 kg m−3 air density, we define a small 1.14 m-span rectangular wing. Three low-Re airfoils (Eppler 387, Eppler 205, Selig 1223) are evaluated in 2-D CFD for −2° to 10° angles of attack; Eppler 387 has the best lift-to-drag ratio at the zero-incidence cruise point and is selected for the baseline. A 3-D CAD model depicts the high-wing, twin-boom H-tail configuration scaled to a stall speed near 7.8 m s−1 in Titan air. An early 5 × 5 severity–likelihood risk matrix determines stall-margin uncertainty, low-temperature material brittleness, and battery capacity loss to be top design drivers, guiding early mitigation strategies. While it is a conceptual framework, the coupled aerodynamic and risk framework provides a quantitative foundation for guiding future power-plant trades, sub-scale testing, and final mission definition of fixed-wing exploration of Titan.