A control circuitry comprising: a propulsor trim prediction circuitry configured to generate a predicted propulsor trim value (444, 562, 662) for a target state of an aircraft based on an aircraft velocity and a pitch attitude deviation from a reference (550, 622), wherein the pitch attitude deviation from the reference corresponds to an aircraft pitch attitude command when the predicted propulsor trim value is a predicted propulsor collective blade pitch trim value, or wherein the pitch attitude deviation from the reference corresponds to a gravity compensated longitudinal acceleration signal when the predicted propulsor trim value is a predicted proprotor nacelle angle trim value; and an output circuitry (406, 516, 518) configured to output a propulsor command based on the predicted propulsor trim value (444, 562, 662), the propulsor command (452, 652) configured to cause: an adjustment in a collective blade pitch angle of a propulsor (112, 114) of the aircraft, when the propulsor command is the propulsor collective blade pitch angle command and the predicted propulsor trim value is the predicted propulsor collective blade pitch trim value, or an adjustment in a nacelle angle of a proprotor (112, 114) of the aircraft, when the propulsor command is a proprotor nacelle command and the predicted propulsor trim value is the predicted proprotor nacelle angle trim value. a propulsor trim prediction circuitry configured to generate a predicted propulsor trim value (444, 562, 662) for a target state of an aircraft based on an aircraft velocity and a pitch attitude deviation from a reference (550, 622), wherein the pitch attitude deviation from the reference corresponds to an aircraft pitch attitude command when the predicted propulsor trim value is a predicted propulsor collective blade pitch trim value, or wherein the pitch attitude deviation from the reference corresponds to a gravity compensated longitudinal acceleration signal when the predicted propulsor trim value is a predicted proprotor nacelle angle trim value; and wherein the pitch attitude deviation from the reference corresponds to an aircraft pitch attitude command when the predicted propulsor trim value is a predicted propulsor collective blade pitch trim value, or wherein the pitch attitude deviation from the reference corresponds to a gravity compensated longitudinal acceleration signal when the predicted propulsor trim value is a predicted proprotor nacelle angle trim value; and an output circuitry (406, 516, 518) configured to output a propulsor command based on the predicted propulsor trim value (444, 562, 662), the propulsor command (452, 652) configured to cause: an adjustment in a collective blade pitch angle of a propulsor (112, 114) of the aircraft, when the propulsor command is the propulsor collective blade pitch angle command and the predicted propulsor trim value is the predicted propulsor collective blade pitch trim value, or an adjustment in a nacelle angle of a proprotor (112, 114) of the aircraft, when the propulsor command is a proprotor nacelle command and the predicted propulsor trim value is the predicted proprotor nacelle angle trim value. an adjustment in a collective blade pitch angle of a propulsor (112, 114) of the aircraft, when the propulsor command is the propulsor collective blade pitch angle command and the predicted propulsor trim value is the predicted propulsor collective blade pitch trim value, or an adjustment in a nacelle angle of a proprotor (112, 114) of the aircraft, when the propulsor command is a proprotor nacelle command and the predicted propulsor trim value is the predicted proprotor nacelle angle trim value.