Yaw control of maneuvering tailless aircraft using induced drag – a control allocation method based on aerodynamic mode shapes

This paper proposes a novel method to achieve three-axis control of a tailless aircraft using conventional conformal trailing edge controls only. The method is based on the synthesis of control allocation modes which produce laterally asymmetric profile drag and induced drag at constant lift, pitching moment and rolling moment. Results are presented for a generic low aspect ratio swept wing planform at a range of trimmed sideslip angles up to 10 degrees, with control allocations optimized for either minimum drag or minimum aggregate control deflection. Obtained solutions have equivalent authority to conventional mid-chord spoilers with reduced overall drag and, at angles of trimmed sideslip less than 4 degrees, reduced aggregate control deflection. This presents designers with an option for directional control which reduces the need for non-conformal controls outside of the low speed flight regime.