A flight control system for an aircraft, the flight control system comprising: one or more computer processors; and a memory coupled to the one or more computer processors, the memory storing data comprising a database and program code that, when executed by the one or more computer processors, causes the flight control system to: receive as an input a first plurality of operating parameters that each represent an operating condition of the aircraft; determine a drag coefficient (C D) and a lift coefficient (C L) based on the first plurality of operating parameters; receive as a further input a measured longitudinal acceleration (Ax (mea)) and a measured vertical acceleration (Az (mea)); receive as input a second plurality of operating parameters of the aircraft; determine an estimated net thrust of the aircraft based on the second plurality of operating parameters of the aircraft; determine an estimated longitudinal acceleration (Ax (est)) and an estimated vertical acceleration (Az (est)) based on the drag coefficient (C D), the lift coefficient (C L), and the estimated net thrust; determine an acceleration error value for a first difference between the estimated longitudinal acceleration (Ax (est)) and the measured longitudinal acceleration (Ax (mea)), and a second difference between the estimated vertical acceleration (Az (est)) and the measured vertical acceleration (Az (mea)); and determine a residual Kalman value by multiplying the acceleration error value for the first difference and the second difference with a Kalman gain value; determine an estimated rate of change of the dynamic pressure ( Q̇ bar(e)) based on the estimated longitudinal acceleration (Ax (est)) of the aircraft; combine the residual Kalman value with the estimated rate of change of the dynamic pressure ( Q̇ bar(e)) together into a sum; and integrate the sum of the residual Kalman value and the estimated rate of change of the dynamic pressure ( Q̇ bar(e)) to determine an estimated dynamic pressure (Q bar(e)). one or more computer processors; and a memory coupled to the one or more computer processors, the memory storing data comprising a database and program code that, when executed by the one or more computer processors, causes the flight control system to: receive as an input a first plurality of operating parameters that each represent an operating condition of the aircraft; determine a drag coefficient (C D) and a lift coefficient (C L) based on the first plurality of operating parameters; receive as a further input a measured longitudinal acceleration (Ax (mea)) and a measured vertical acceleration (Az (mea)); receive as input a second plurality of operating parameters of the aircraft; determine an estimated net thrust of the aircraft based on the second plurality of operating parameters of the aircraft; determine an estimated longitudinal acceleration (Ax (est)) and an estimated vertical acceleration (Az (est)) based on the drag coefficient (C D), the lift coefficient (C L), and the estimated net thrust; determine an acceleration error value for a first difference between the estimated longitudinal acceleration (Ax (est)) and the measured longitudinal acceleration (Ax (mea)), and a second difference between the estimated vertical acceleration (Az (est)) and the measured vertical acceleration (Az (mea)); and determine a residual Kalman value by multiplying the acceleration error value for the first difference and the second difference with a Kalman gain value; determine an estimated rate of change of the dynamic pressure ( Q̇ bar(e)) based on the estimated longitudinal acceleration (Ax (est)) of the aircraft; combine the residual Kalman value with the estimated rate of change of the dynamic pressure ( Q̇ bar(e)) together into a sum; and integrate the sum of the residual Kalman value and the estimated rate of change of the dynamic pressure ( Q̇ bar(e)) to determine an estimated dynamic pressure (Q bar(e)). receive as an input a first plurality of operating parameters that each represent an operating condition of the aircraft; determine a drag coefficient (C D) and a lift coefficient (C L) based on the first plurality of operating parameters; receive as a further input a measured longitudinal acceleration (Ax (mea)) and a measured vertical acceleration (Az (mea)); receive as input a second plurality of operating parameters of the aircraft; determine an estimated net thrust of the aircraft based on the second plurality of operating parameters of the aircraft; determine an estimated longitudinal acceleration (Ax (est)) and an estimated vertical acceleration (Az (est)) based on the drag coefficient (C D), the lift coefficient (C L), and the estimated net thrust; determine an acceleration error value for a first difference between the estimated longitudinal acceleration (Ax (est)) and the measured longitudinal acceleration (Ax (mea)), and a second difference between the estimated vertical acceleration (Az (est)) and the measured vertical acceleration (Az (mea)); and determine a residual Kalman value by multiplying the acceleration error value for the first difference and the second difference with a Kalman gain value; determine an estimated rate of change of the dynamic pressure ( Q̇ bar(e)) based on the estimated longitudinal acceleration (Ax (est)) of the aircraft; combine the residual Kalman value with the estimated rate of change of the dynamic pressure ( Q̇ bar(e)) together into a sum; and integrate the sum of the residual Kalman value and the estimated rate of change of the dynamic pressure ( Q̇ bar(e)) to determine an estimated dynamic pressure (Q bar(e)).