Extension of three loop control laws for system uncertainties, calculation time delay and command quickness

An aircraft, comprising:

• an interface;
• a plurality of actuators;
• and
• a flight control computer operably associated with the interface and at least one of the plurality of the actuators, the flight control computer having a control logic architecture having:
• a dynamic command input shaping model associated with an input command;
• a robust inner loop associated with the dynamic command input shaping model;
• and
• a time delay cancelation model;
• wherein the input command is received by the control system, analyzed with the control logic architecture, and thereafter commands the at least one actuator of the plurality of actuators.

A method, comprising:

• selecting a control law based upon a flight performance of an aircraft;
• decoupling the control law into a first individual component and a second individual component of the aircraft flight motion;
• analyzing each individual component separately;
• regrouping the component of flight motion;
• and
• analyzing the control law with a time delay cancelation model.