A control circuitry comprising: a propulsor trim prediction circuitry configured to generate a predicted propulsor trim value for a target state of an aircraft based on an aircraft velocity and a pitch attitude deviation from a reference , 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 configured to output a propulsor command based on the predicted propulsor trim value , the propulsor command configured to cause: an adjustment in a collective blade pitch angle of a propulsor 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 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 for a target state of an aircraft based on an aircraft velocity and a pitch attitude deviation from a reference , 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 configured to output a propulsor command based on the predicted propulsor trim value , the propulsor command configured to cause: an adjustment in a collective blade pitch angle of a propulsor 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 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 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 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 . <EOS>