Design and aerodynamic analysis of multidimensional combined morphing for supersonic aircraft forebody

Purpose The morphing aircraft adaptively changes its shape to achieve optimal performance according to the mission requirements in each flight phase. The purpose of this study is to design a new morphing scheme for the aircraft forebody that provides greater aerodynamic performance benefits than wing deformation. Design/methodology/approach A new multidimensional combined morphing scheme that considers flexible skin technology constraints and air tightness is proposed based on the mission profile, enabling multi-stage extension and deflection deformation of the aircraft forebody. Numerical simulations of the contraction, extension and deflection states of morphing aircraft are carried out at different Mach numbers and angles of attack. Findings The aerodynamic characteristics of three states are compared and the effects of deformation ratio are further explored. The results show that scheme can not only improve the lift-drag performance but also the pitching maneuverability. Originality/value First, a mission-profile-driven multidimensional combined morphing concept is proposed for the aircraft forebody, integrating contraction, extension and deflection states within a unified framework. Second, a fully rigid segmented forebody configuration is developed to avoid the load-carrying and airtightness limitations associated with flexible skins in supersonic and hypersonic applications. Third, the proposed scheme is evaluated not only in terms of aero-dynamic characteristics but also in terms of trajectory implications, showing that the extension state is beneficial for cruise efficiency, while the deflection state is advantageous for maneuverability.