System and method for controlling a roll rate of a torsionally-disconnected freewing aircraft

A system for controlling a roll rate, comprising:

• an aircraft;
• a roll rate sensor configured to measure a roll rate of a fuselage of the aircraft and to output a first roll rate signal,
• wherein the aircraft includes first and second main freewings, 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 a 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;
• a control processor in communication with the roll rate sensor,
• wherein the control processor is configured to receive a second roll rate signal from a pilot of the aircraft, and
• wherein the control processor is configured to compare the first and second roll rate signals to generate first and second control signals;
• and
• a control actuator in communication with the control processor,
• wherein the control actuator is configured to actuate a first control member of the first main freewing and a second control member of the second main freewing in response to the first and second control signals, respectively, to control the roll rate of the aircraft.

A method of controlling a roll rate of an aircraft, comprising the steps of:

• a.) measuring a roll rate of a fuselage of the aircraft to generate a first roll rate signal,
• wherein the aircraft includes first and second main freewings, 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 includes 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 a 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;
• b.) receiving a second roll rate signal from a pilot of the aircraft;
• c.) comparing the first and second roll rate signals to generate first and second control signals;
• and
• d.) actuating 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 signals, respectively, to control the roll rate of the aircraft.