The present application belongs to the technical field of tilt-rotor aircraft flight control, and relates to a transition boundary protection method for tilt-rotor aircraft. According to the upper boundary of the transition corridor and the lower boundary of the transition corridor of the tilt-rotor aircraft, the maximum tilt rate upper boundary of the transition corridor and the maximum tilt rate lower boundary of the transition corridor are calculated. According to the current
flight speed, the upper boundary of the transition corridor, the lower boundary of the transition corridor, the maximum tilt rate upper boundary and the maximum tilt rate lower boundary, the proportional coefficient of the current flight state approaching the upper boundary of the transition corridor and the proportional coefficient of the current flight state approaching the lower boundary of the transition corridor are calculated. According to the current given
nacelle tilt rate instruction and the current
nacelle angle, the upper limit proportional coefficient of the amplitude limiting and the
lower limit proportional coefficient of the amplitude limiting are calculated. According to the maximum
nacelle tilt rate, the minimum nacelle tilt rate, the proportional coefficient, the proportional coefficient, the upper limit proportional coefficient of the amplitude limiting and the
lower limit proportional coefficient of the amplitude limiting, the upper limit of the nacelle tilt rate amplitude limiting and the
lower limit of the nacelle tilt rate amplitude limiting are calculated. According to the current given nacelle tilt rate instruction, the maximum nacelle tilt rate, the minimum nacelle tilt rate, the proportional coefficient, the proportional coefficient, the upper limit and the lower limit of the amplitude limiting, the nacelle tilt rate instruction with the boundary protection function is calculated.