System and method for improved rotor tip performance
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-027/72
B64C-027/00
출원번호
US-0898698
(2004-07-23)
등록번호
US-7264200
(2007-09-04)
발명자
/ 주소
Bussom,Richard
McVeigh,Michael A.
Narducci,Robert P.
Zientek,Thomas A.
출원인 / 주소
The Boeing Company
대리인 / 주소
Lee & Hayes, PLLC
인용정보
피인용 횟수 :
10인용 특허 :
15
초록▼
The present invention discloses systems and methods for the performance enhancement of rotary wing aircraft through reduced torque, noise and vibration. In one embodiment, a system includes a sail having an aerodynamic shape positioned proximate to a tip of the rotor blade. An actuator may be config
The present invention discloses systems and methods for the performance enhancement of rotary wing aircraft through reduced torque, noise and vibration. In one embodiment, a system includes a sail having an aerodynamic shape positioned proximate to a tip of the rotor blade. An actuator may be configured to rotate the sail relative to the blade tip. a A control system receives information from a rotorcraft system and commands the actuator to rotate the sail to a predetermined favorable rotor blade operating condition. In another embodiment, a method includes configuring the rotorcraft in a selected flight condition, communicating input signals to a control system operable to position sails coupled to tips of blades of a rotor assembly, processing the input signals according to a constraint condition to generate sail positional information, and transferring the sail positional information to the sail.
대표청구항▼
What is claimed is: 1. A system for improved rotor blade performance in a rotorcraft, comprising: a plurality of sails, each sail having an aerodynamic shape and positioned proximate to a tip of the rotor blade; an actuator coupled to each sail of the plurality of sails, the actuator being configur
What is claimed is: 1. A system for improved rotor blade performance in a rotorcraft, comprising: a plurality of sails, each sail having an aerodynamic shape and positioned proximate to a tip of the rotor blade; an actuator coupled to each sail of the plurality of sails, the actuator being configured to rotate each sail about a longitudinal axis into a corresponding pitch angle independently of the other sails, such that one or more of the pitch angles has a different pitch value than the other pitch angles; and a control system operable to receive information from a selected rotorcraft system and to command the actuator to actuate each sail to a position that corresponds to a predetermined favorable rotor blade operating condition. 2. The system of claim 1, wherein the longitudinal axis of the at least one sail forms a dihedral angle with a longitudinal axis of the blade. 3. The system of claim 2, wherein the dihedral angle is a positive dihedral angle or a negative dihedral angle. 4. The system of claim 1, wherein the actuator is further configured to adjust a corresponding dihedral angle of each sail independently of the other sails, such that one or more of the dihedral angles has a different dihedral value than the other dihedral angles. 5. The system of claim 1, wherein the actuator further comprises a piezoelectric material operable to effect the rotation of the at least one sail upon application of an electric field to the material. 6. The system of claim 1, wherein the actuator comprises a magnetostrictive material operable to effect the rotation of the at least one sail upon application of a magnetic field to the material. 7. The system of claim 1, wherein the at least one sail comprises a plurality of sails. 8. The system of claim 1, wherein the actuator comprises at least one of an electrostrictive material, a thermoresponsive material, and an electroactive polymer operable to effect the rotation of the at least one sail upon application of a thermal field to the material. 9. The system of claim 8, wherein the actuator comprises a thermoresponsive material that includes a shape memory alloy. 10. The system of claim 1, wherein the at least one sail projects at least partially aft of a trailing edge of the tip of the rotor blade. 11. The system of claim 1, wherein the control system is configured to receive information from a pitot-static system installed in the rotorcraft. 12. The system of claim 11, further comprising an air data computer coupled to the pitot-static system, and wherein the control system is configured to receive information from the air data computer. 13. A system for improved rotor blade performance in a rotorcraft, comprising: at least one sail having an aerodynamic shape and positioned proximate to a tip of the rotor blade; an actuator coupled to the at least one sail, the actuator being configured to rotate the sail about a longitudinal axis of the sail and to adjust a dihedral angle of the sail; and a control system operable to receive information from a selected rotorcraft system and to command the actuator to actuate the sail to a position that corresponds to a predetermined favorable rotor blade operating condition, wherein the control system is configured to receive information from a structural vibration detection system operable to detect a vibration level on a selected portion of the rotorcraft structure. 14. A system for improved rotor blade performance in a rotorcraft, comprising: at least one sail having an aerodynamic shape and positioned proximate to a tip of the rotor blade; an actuator coupled to the at least one sail, the actuator being configured to rotate the sail about a longitudinal axis of the sail and to adjust a dihedral angle of the sail; and a control system operable to receive information from a selected rotorcraft system and to command the actuator to actuate the sail to a position that corresponds to a predetermined favorable rotor blade operating condition, wherein the control system is configured to receive information from a torque sensor coupled to a rotor portion of the rotorcraft. 15. A rotary wing aircraft, comprising: a rotor assembly having a plurality of blades attached thereto; a propulsion system operatively coupled to the rotor assembly; and a system for improved rotor blade performance in a rotorcraft, further comprising: a plurality of sails, each sail coupled to tips of the blades and rotatable about a longitudinal axis that extends in a span-wise direction along the sail; an actuator coupled to each sail of the plurality of sails and coupled to the blade tips and operable to rotate each sail about the longitudinal axis into a corresponding pitch angle independently of the other sails such that one or more of the pitch angles has a different pitch value than the other pitch angles; and a control system coupled to a selected rotorcraft system and operable to receive information from the rotorcraft system and to controllably adjust the actuator to rotate each sail to a position that corresponds to a predetermined favorable rotor blade operating condition. 16. The system of claim 15, wherein the actuator being comprised of a smart material that is responsive to an applied field, the smart material including at least one of a piezoelectric material, and a magnetostrictive material, and wherein the applied field is at least one of an electric field and a magnetic field. 17. The system of claim 15, wherein the actuator is further configured to adjust a corresponding dihedral angle of each sail independently of the other sails, such that one or more of the dihedral angles has a different dihedral value than the other dihedral angles. 18. The system of claim 15, wherein the smart material comprises an electrostrictive material and the applied field is an electric field operable to effect the rotation of the at least one sail upon application of the electric field to the material. 19. The system of claim 15, wherein the smart material comprises a thermoresponsive material and the applied field is a thermal field operable to effect the rotation of the at least one sail upon application of the thermal field to the material. 20. The system of claim 19, wherein the thermoresponsive material comprises a memory shape alloy. 21. The system of claim 15, wherein the smart material comprises an electroactive polymer and the applied field is an electric field operable to effect the rotation of the at least one sail upon application of the electric field to the material. 22. The system of claim 15, wherein the control system is configured to receive information from a pitot-static system installed in the rotorcraft. 23. The system of claim 22, further comprising an air data computer coupled to the pitot-static system, and wherein the control system is configured to receive information from the air data computer. 24. A rotary wing aircraft, comprising: a rotor assembly having a plurality of blades attached thereto; a propulsion system operatively coupled to the rotor assembly; and a system for improved rotor blade performance in a rotorcraft, further comprising: at least one sail coupled to tips of the blades and rotatable about a longitudinal axis that extends in a span-wise direction alone the sail; an actuator coupled to the at least one sail and coupled to the blade tips and operable to rotate the sail about the longitudinal axis and adjust a dihedral angle of the at least one sail, the actuator being comprised of a smart material that is responsive to an applied field; and a control system coupled to a selected rotorcraft system and operable to receive information from the rotorcraft system and to apply the field to the actuator to rotate the sail to a position that corresponds to a predetermined favorable rotor blade operating condition, wherein the control system is configured to receive information from a structural vibration detection system operable to detect a vibration level on a selected portion of the rotorcraft structure. 25. A rotary wing aircraft, comprising: a rotor assembly having a plurality of blades attached thereto; a propulsion system operatively coupled to the rotor assembly; and a system for improved rotor blade performance in a rotorcraft, further comprising: at least one sail coupled to tips of the blades and rotatable about a longitudinal axis that extends in a span-wise direction along the sail; an actuator coupled to the at least one sail and coupled to the blade tips and operable to rotate the sail about the longitudinal axis and adjust a dihedral angle of the at least one sail, the actuator being comprised of a smart material that is responsive to an applied field; and a control system coupled to a selected rotorcraft system and operable to receive information from the rotorcraft system and to apply the field to the actuator to rotate the sail to a position that corresponds to a predetermined favorable rotor blade operating condition, wherein the control system is configured to receive information from a torque sensor coupled to a rotor portion of the rotorcraft.
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