An aircraft comprising: an airframe; a control input for inputting a desired aircraft attitude; an extending tail; a counter rotating, coaxial main rigid rotor assembly including an upper rigid rotor assembly and a lower rigid rotor assembly; a rotor interface configured to independently control the collective and cyclic pitch of the upper rigid rotor assembly and of the lower rigid rotor assembly by means of independently controlled swashplates or individual blade control in each of the rigid rotor assemblies (28, 32); a translational thrust system positioned at the extending tail with a translational thrust axis oriented substantially horizontal and parallel to the aircraft longitudinal axis, the translational thrust system providing translational thrust to the airframe; and a horizontal stabilizer positioned at the extending tail, the horizontal stabilizer having one or more elevators; a plurality of sensors to detect sensor data of at least one environmental condition and at least one aircraft state data, the plurality of sensors providing the sensor data to the flight control computer; a flight control computer in response to the control input to independently control one or more of the upper rigid rotor assembly, the lower rigid rotor assembly, the elevator, and the translational thrust system through a fly-by-wire control system, wherein the aircraft and the flight control computer in response to the control input are configured to utilize algorithms based on the sensor data and the control input to selectively mix the independently controllable collective pitch of the upper rigid rotor assembly and of the lower rigid rotor assembly, the independently controllable cyclic pitch for the upper rigid rotor assembly and for the lower rigid rotor assembly, the elevator deflection, and the translational thrust system thrust to trim the aircraft attitude. an airframe; a control input for inputting a desired aircraft attitude; an extending tail; a counter rotating, coaxial main rigid rotor assembly including an upper rigid rotor assembly and a lower rigid rotor assembly; a rotor interface configured to independently control the collective and cyclic pitch of the upper rigid rotor assembly and of the lower rigid rotor assembly by means of independently controlled swashplates or individual blade control in each of the rigid rotor assemblies (28, 32); a translational thrust system positioned at the extending tail with a translational thrust axis oriented substantially horizontal and parallel to the aircraft longitudinal axis, the translational thrust system providing translational thrust to the airframe; and a horizontal stabilizer positioned at the extending tail, the horizontal stabilizer having one or more elevators; a plurality of sensors to detect sensor data of at least one environmental condition and at least one aircraft state data, the plurality of sensors providing the sensor data to the flight control computer; a flight control computer in response to the control input to independently control one or more of the upper rigid rotor assembly, the lower rigid rotor assembly, the elevator, and the translational thrust system through a fly-by-wire control system, wherein the aircraft and the flight control computer in response to the control input are configured to utilize algorithms based on the sensor data and the control input to selectively mix the independently controllable collective pitch of the upper rigid rotor assembly and of the lower rigid rotor assembly, the independently controllable cyclic pitch for the upper rigid rotor assembly and for the lower rigid rotor assembly, the elevator deflection, and the translational thrust system thrust to trim the aircraft attitude.