IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0752791
(2007-05-23)
|
등록번호 |
US-7757992
(2010-08-09)
|
발명자
/ 주소 |
- Bussom, Richard
- McVeigh, Michael A.
- Narducci, Robert P.
- Zientek, Thomas A.
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
3 인용 특허 :
16 |
초록
▼
Embodiments of systems and methods for enhancing the performance of rotary wing aircraft through reduced torque, noise and vibration are disclosed. In one embodiment, a method includes configuring the rotorcraft in a selected flight condition, communicating input signals to a control system operable
Embodiments of systems and methods for enhancing the performance of rotary wing aircraft through reduced torque, noise and vibration are disclosed. In one 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. Alternately, input signals may be communicated to a control system operable to position a plurality of sails, each sail having an aerodynamic shape and positioned proximate to a tip portion of the rotor blade. The input signals may be configured to rotate each sail about a longitudinal axis into a corresponding pitch angle independently of the other sails.
대표청구항
▼
What is claimed is: 1. A method for configuring a rotor blade in a rotary wing aircraft, comprising: selecting a flight condition; configuring the rotor blade to the selected flight condition; receiving a control input generated from a sensing device installed in the rotary wing aircraft; determini
What is claimed is: 1. A method for configuring a rotor blade in a rotary wing aircraft, comprising: selecting a flight condition; configuring the rotor blade to the selected flight condition; receiving a control input generated from a sensing device installed in the rotary wing aircraft; determining, based on the control input, an orientation of a sail coupled to a tip of the rotor blade, at least a portion of the sail extending beyond an axis that extends along a trailing edge of the rotor blade to an outboard edge of the sail; and moving the sail to the determined orientation. 2. The method of claim 1, wherein the selecting the flight condition comprises selecting at least one of a rotor blade pitch angle and a rotor blade rotational velocity associated with the flight condition. 3. The method of claim 1, wherein the moving the sail to the determined orientation comprises rotating the sail about a span-wise axis of the sail. 4. The method of claim 1, wherein the moving the sail to the determined orientation comprises applying a selected field to a smart material that is coupled to the sail and moving the sail in response to the selected field. 5. The method of claim 4, wherein the applying the selected field to the smart material further comprises applying an electric field to at least one of a piezoelectric material, an electrostrictive material, and an electroactive polymer material to move the sail to the determined orientation. 6. The method of claim 4, wherein the applying the selected field to the smart material further comprises applying a magnetic field to a magnetostrictive material to move the sail to the determined orientation. 7. The method of claim 4, wherein the applying the selected field to the smart material further comprises applying a thermal field to a thermoresponsive material to move the sail to the determined orientation. 8. The method of claim 1, wherein the sensing device is one of a structural vibration detection system, a torque measurement device, or a pitot-static system. 9. The method of claim 1, wherein the determining the orientation of the sail includes determining at least one of a sail pitch angle and a sail dihedral angle and further wherein the moving the sail to the determined orientation includes moving the sail to at least one of the sail pitch angle and the sail dihedral angle. 10. The method of claim 1, wherein the determining the orientation of the sail includes determining a sail pitch angle and a sail dihedral angle and further wherein the moving the sail to the determined orientation includes moving the sail to the sail pitch angle and the sail dihedral angle. 11. A method for configuring a rotor blade in a rotary wing aircraft, comprising: selecting a flight condition; configuring the rotor blade to the selected flight condition; receiving a control input generated from a sensing device installed in the rotary wing aircraft; determining, based on the control input, an orientation of a sail coupled to a tip of the rotor blade, at least a portion of the sail extending beyond an axis that extends along a trailing edge of the rotor blade to an outboard edge of the sail; and applying a selected field to a smart material that is coupled to the sail to move the sail to the determined orientation. 12. The method of claim 11, wherein the applying the selected field to the smart material further comprises applying an electric field to at least one of a piezoelectric material, an electrostrictive material, and an electroactive polymer material to move the sail to the determined orientation. 13. The method of claim 11, wherein the applying the selected field to the smart material further comprises applying a magnetic field to a magnetostrictive material to move the sail to the determined orientation. 14. The method of claim 11, wherein the applying the selected field to the smart material further comprises applying a thermal field to a thermoresponsive material to move the sail to the determined orientation. 15. The method of claim 11, wherein the sensing device is one of a structural vibration detection system, a torque measurement device, or a pitot-static system.
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