Design Exploration of Aerodynamic Wing Shape for Reusable Launch Vehicle Flyback Booster

摘要

The wing for a TSTO RLV flyback booster powered by a liquid-propellant rocket engine for VTHL was optimized by considering four aerodynamic objective functions using ARMOGA. Consequently, the tradeoff information among the four objective functions has been revealed. No tradeoff exists between the shift of aerodynamic center and transonic pitching moment. However, a severe tradeoff was found between transonic drag and subsonic lift. Moreover, data mining for the design space was performed using SOM. For example, wing position should not be too far to the rear of the fuselage, to decrease the shift in the aerodynamic center between supersonic and transonic flow conditions, transonic pitching moment, and transonic drag. Rearward camber height at the tip has an influence on transonic drag. Rearward camber height at the kink increases subsonic lift. Strake has less effect on the increase in subsonic lift and primary leading-edge separation from the outboard wing is more important for vortex lift. Data mining provides knowledge regarding the design space, which is considered an important facet of solving optimization problems.