Abstract: Rotated wing aircraft is a unique new type of aircraft structure, whose rotor is non-torqued blade rotor and rotating with all or part of the wing. To meet the control demand of transition section from a helicopter model to the fixed wing of the rotated wing aircraft, the longitudinal nonlinear mathematical model has been established based on the analysis of longitudinal channel. Balancing the transition section model and designing the conversion channel according to the requirement of altitude. The model is linearized and analyzed, and the results show that the rotated wing aircraft transition section is stable.