The research object of this paper is a novel morphing aircraft. The V‐tail is a tiltable heading stabilizer that can be deflected in the range of 0°~75° continuously. According to the mission requirements, the aircraft can be transformed into stealth flying wings and high mobility layout configuration; the “scorpion tail” at the rear of the fuselage is a pitching fluid thrust vectoring control surface based on the Coandă effect, which can effectively reduce the infrared characteristics of the engine jet and realize the short takeoff and landing of the aircraft. To be appropriate for the morphing, a new control method of “butterfly rudder” is proposed, which solves the problem of coordinated control of pitch, roll, and yaw in the flying wing configuration. Theoretical analyses and flight tests reveal that the stability and control characteristics of this morphing aircraft differ significantly from those of conventional fixed‐geometry aircraft. It exhibits multi‐axis static instability, along with multivariate, strongly coupled, and highly nonlinear dynamics. Guided by the Control‐Configured Vehicle (CCV) concept, the design prioritizes optimized aerodynamic performance. A multidisciplinary design analysis integrating aerodynamics, stealth, control systems, and materials science was conducted to achieve balanced performance across multiple metrics. The flight control algorithm designed with it achieves stable flight, with good command tracking characteristics and controllable variation process, which effectively proves the correctness of the design scheme.
Jin et al. (Thu,) studied this question.