Aircraft lateral and lateral flight state solving method based on roll angle rate input

The invention discloses an aircraft transverse and lateral flight state solving method based on roll angle rate input, which is characterized in that a traditional three-degree-of-freedom particle motion model and transverse and lateral input are improved, a roll angle rate is used as input, yaw angle acceleration and roll angle acceleration are obtained through indirect calculation based on the roll angle rate, and the yaw angle acceleration and the roll angle acceleration are calculated to obtain the transverse and lateral flight state of an aircraft. For a given roll angle rate instruction, the angle and position information of the aircraft can be directly calculated while the control capability of the aileron and the rudder is fully considered. Compared with a mass point motion equation based on a heeling angle as input, the state of the aircraft can be better restrained within the control surface control capability by taking the roll angle rate as input. Compared with the prior art, the method for solvin