Patent ID: 7441724

Claim:
An aircraft, comprising: a fuselage; a first main freewing and a second main freewing, wherein each of the first and second main freewings is torsionally disconnected from each other, such that each of the first and second main freewings is decoupled from each other and the fuselage wherein each of the first and second main freewings is independently and freely pivotable i) about its respective pivot axis, ii) about the fuselage, and iii) in regard to each other, and wherein each of the first and second main freewings comprises a principal inertial axis, a tip and a base, and wherein the principal inertial axis of each of the first and second main freewings is substantially aligned fore of the respective pivot axis at the tip of each of the first and second main freewings, and substantially aligned aft of the respective pivot axis at the base of each of the first and second main freewings; an angular rate sensor, wherein the angular rate sensor is configured to measure a roll rate of the fuselage and to output a first roll rate signal; a controller in communication with the angular rate sensor, wherein the controller is configured to receive a second roll rate signal from a pilot of the aircraft, and wherein the controller is configured to compare the first and second roll rate signals to generate first and second control surface control signals; and at least one control actuator in communication with the controller, wherein the at least one control actuator is configured to actuate a first control surface of the first main freewing and a second control surface of the second main freewing in response to the first and second control surface control signals, respectively, to control a roll rate of the aircraft.