Patent ID: 8523102

Claim:
A reconfigurable flight control system for reconfiguring flight control of an aircraft in response to a failure, the aircraft having flight control actuators and sensors, the reconfigurable flight control system comprising: a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix; a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator, the reconfiguration management tool comprising: a risk factor tool for calculating a risk factor, the risk factor being used for determining whether reconfiguration is necessary; wherein the risk factor is an empirical representation of a control authority of the aircraft, such that a degradation in the control authority effects the risk factor; and a sensor management tool for providing input to the reconfiguration management tool in order to smooth any transient conditions that may occur during the reconfiguring flight control of the aircraft in response to the failure; wherein the mixing/mapping matrix is configured to mix the usage of the flight control actuators in response to a failing of the failed actuator by employing a first independent actuator system at a first percentage and employing a second independent actuator system at a second percentage, such that the combination of the first independent actuator system and the second independent actuator system produces a desired aircraft flight control response that takes into consideration the failed actuator; wherein the mixing/mapping matrix is configured to continuously change the first percentage and the second percentage to optimize flight control of the aircraft in response to the failed actuator.