US Patent 11460865 Method and system for longitudinal control of aircraft

Methods and systems for longitudinal control of aircraft during flight are disclosed. One method comprises receiving a commanded normal acceleration of the aircraft and computing a target pitch rate for the aircraft based on the commanded normal acceleration. The target pitch rate is used in a control technique for controlling one or more flight control surfaces of the aircraft to achieve the target pitch rate for the aircraft. The control technique can include (e.g., incremental) nonlinear dynamics inversion.