A method for controlling rotor blades of a co-axial rotor assembly of an aircraft including a first rotor co-axial with a second rotor includes identifying a first zone of rotor rotation angles of the co-axial rotor assembly. The first zone defines a range of rotor rotation angles corresponding to a
A method for controlling rotor blades of a co-axial rotor assembly of an aircraft including a first rotor co-axial with a second rotor includes identifying a first zone of rotor rotation angles of the co-axial rotor assembly. The first zone defines a range of rotor rotation angles corresponding to an up-flow of air to the coaxial rotor assembly, and the remainder of the rotor rotation angles other than the first zone of rotation angles is defined as a second zone. The method includes receiving a yaw command to adjust a yaw moment of the aircraft and applying a different rotor blade angle change to rotor blades in the first zone than a rotor blade angle change applied to rotor blades in the second zone to adjust the yaw moment of the aircraft according to the yaw command.
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1. A method for controlling rotor blades of a co-axial counter-rotating rotor assembly of an aircraft including a first rotor co-axial with a second rotor, comprising: identifying a first zone of rotor rotation angles of the co-axial counter-rotating rotor assembly, the first zone defining a range o
1. A method for controlling rotor blades of a co-axial counter-rotating rotor assembly of an aircraft including a first rotor co-axial with a second rotor, comprising: identifying a first zone of rotor rotation angles of the co-axial counter-rotating rotor assembly, the first zone defining a range of rotor rotation angles corresponding to an up-flow of air to the coaxial rotor assembly, and the remainder of the rotor rotation angles other than the first zone of rotation angles being defined as a second zone;receiving a yaw command to adjust a yaw moment of the aircraft; andapplying a different rotor blade angle change to rotor blades in the first zone than a rotor blade angle change applied to rotor blades in the second zone to adjust the yaw moment of the aircraft according to the yaw command. 2. The method of claim 1, wherein the change in rotor blade angle applied to rotor blades in the second zone of the first rotor is opposite the change in rotor blade angle applied to rotor blades in the second zone of the second rotor. 3. The method of claim 1, wherein the range of angles corresponding to the first zone corresponds to an up-flow of air to the first rotor, the method further comprising: identifying a third zone of rotation angles of the second rotor, the third zone defining a range of rotor rotation angles corresponding to an up-flow of air to the second rotor, and the third zone having a size different from the first zone, and the remainder of the rotor rotation angles of the second rotor other than the third zone of rotation angles being defined as a fourth zone;applying a different rotor blade angle change to rotor blades in the third zone than a rotor blade angle change applied to rotor blades in the fourth zone to adjust the yaw moment of the aircraft according to the yaw command. 4. The method of claim 1, further comprising: individually and separately controlling the blade pitch angle of each rotor blade of the co-axial rotor assembly. 5. The method of claim 1, further comprising: adjusting the rotor blade angle of each rotor blade within the first zone and the second zone according to an azimuthal position of the each rotor blade within the first zone and the second zone, respectively. 6. The method of claim 1, wherein the first zone includes a range of rotation angles within a range between, and including, ninety (90) degrees and two-hundred seventy (270) degrees, and passing through one-hundred eighty (180) degrees, where one hundred eighty (180) degrees is defined by a front end of a fuselage of the aircraft. 7. The method of claim 1, wherein the change in rotor blade angle of the rotor blades in the first zone is around zero (0) degrees. 8. The method of claim 1, wherein the first zone includes a range of rotation angles within a range between, and including, ninety (90) degrees and two-hundred seventy (270) degrees, and passing through one-hundred eighty (180) degrees, where one hundred eighty (180) degrees is defined by a front end of a fuselage of the aircraft, and the change in rotor blade angle of the rotor blades in the first zone is around zero (0) degrees. 9. A method for controlling rotor blades of a co-axial rotor assembly of an aircraft, comprising: receiving a target yaw value to adjust a yaw moment of the aircraft;controlling a change in pitch angle of the rotor blades of the co-axial rotor assembly within a predetermined range of rotation angles defining a first zone to have a substantially constant value based on receiving the target yaw value; andcontrolling a change in pitch angle of the rotor blades of the co-axial rotor assembly in the remainder of rotation angles other than the predetermined range of rotation angles, defining a second zone, to be adjusted based on receiving the target yaw value. 10. The method of claim 9, wherein the predetermined range of rotation angles defining the first zone corresponds to a flow of air onto the rotor blades of the rotor assembly that is an up-flow of air, and the rotation angles of the second zone correspond to a flow of air onto the rotor blades of the rotor assembly that is a down-flow of air onto the rotor blades. 11. The method of claim 9, wherein the predetermined range of rotation angles is within the range of two-hundred seventy (270) degrees and ninety (90) degrees, and passing through one hundred eighty (180) degrees, where one hundred eighty (180) degrees is defined by a front end of a fuselage of the aircraft. 12. The method of claim 9, wherein the substantially constant value is around zero (0). 13. The method of claim 9, wherein the co-axial rotor assembly includes a first rotor and a second rotor co-axial with the first rotor, and controlling a change in pitch angle of the rotor blades of the co-axial rotor assembly in the second zone includes changing a pitch angle of the rotor blades of the first rotor in a first rotation direction, and changing a pitch angle of the rotor blades of the second rotor in an opposite rotation direction to the first rotation direction. 14. A co-axial rotor assembly of an aircraft, comprising: a first rotor including a plurality of rotor blades to rotate around a shaft;a second rotor being co-axial with the first rotor and rotating in a direction opposite the first rotor; anda rotor-blade controller to identify a first zone of rotor rotation angles of the co-axial rotor assembly, the first zone defining a range of rotor rotation angles corresponding to an up-flow of air to the coaxial rotor assembly, and the remainder of the rotor rotation angles other than the first zone of rotation angles being defined as a second zone, the rotor-blade controller to receive a yaw command to adjust a yaw moment of the aircraft, and the rotor-blade controller to apply a different rotor blade angle change to rotor blades in the first zone than a rotor blade angle change applied to rotor blades in the second zone to adjust the yaw moment of the aircraft according to the yaw command. 15. The co-axial rotor assembly of claim 14, wherein the change in rotor blade angle applied to rotor blades in the second zone of the first rotor is opposite the change in rotor blade angle applied to rotor blades in the second zone of the second rotor. 16. The co-axial rotor assembly of claim 14, wherein the range of angles corresponding to the first zone corresponds to an up-flow of air to the first rotor, the rotor-blade controller is to identify a third zone of rotation angles of the second rotor, the third zone defining a range of rotor rotation angles corresponding to an up-flow of air to the second rotor, the third zone having a size different from the first zone, and the remainder of the rotor rotation angles of the second rotor other than the third zone of rotation angles being defined as a fourth zone, andthe rotor-blade controller is to apply a different rotor blade angle change to rotor blades in the third zone than a rotor blade angle change applied to rotor blades in the fourth zone to adjust the yaw moment of the aircraft according to the yaw command. 17. The co-axial rotor assembly of claim 14, wherein the rotor-blade controller is to individually and separately control the blade pitch angle of each rotor blade of the co-axial rotor assembly. 18. The co-axial rotor assembly of claim 14, wherein the first zone includes a range of rotation angles within a range between, and including, ninety (90) degrees and two-hundred seventy (270) degrees, and passing through one-hundred eighty (180) degrees, where one hundred eighty (180) degrees is defined by a front end of a fuselage of the aircraft. 19. The co-axial rotor assembly of claim 14, wherein the change in rotor blade angle of the rotor blades in the first zone is around zero (0) degrees. 20. The co-axial rotor assembly of claim 14, wherein the first zone includes a range of rotation angles within a range between, and including, ninety (90) degrees and two-hundred seventy (270) degrees, and passing through one-hundred eighty (180) degrees, where one hundred eighty (180) degrees is defined by a front end of a fuselage of the aircraft, and the change in rotor blade angle of the rotor blades in the first zone is around zero (0) degrees.
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