IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0534657
(2006-09-24)
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등록번호 |
US-7731123
(2010-06-29)
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발명자
/ 주소 |
- Young, Kendall G.
- Simon, Joseph A.
- Cascella, Robert S.
- Edge, Kevin D.
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출원인 / 주소 |
- Lockheed Martin Corporation
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
0 인용 특허 :
6 |
초록
▼
A contra-bevel driven control mechanism repositions a control surface in a fluid environment such as an aerodynamic or hydrodynamic environment. This involves mechanically coupling an airfoil and a control surface. The control surface may pivot about a spanwise axis between upwardly deflected and do
A contra-bevel driven control mechanism repositions a control surface in a fluid environment such as an aerodynamic or hydrodynamic environment. This involves mechanically coupling an airfoil and a control surface. The control surface may pivot about a spanwise axis between upwardly deflected and downwardly deflected positions. A forward beveled rotor mounted to the airfoil and an aft beveled rotor mounted to the control surface counter rotate. The forward beveled rotor rotates about a forward chordwise axis within the airfoil while the aft beveled rotor rotates about an aft chordwise axis within the control surface. The angular rotation between the forward beveled rotor and the aft beveled rotor deflects the aft beveled rotor and the aft chordwise axis within the control surface. Additionally, this method allows the control surface to be deflected with maximum mechanical advantage when the control surface is fully deflected.
대표청구항
▼
What is claimed is: 1. A flight control system, comprising: a forward beveled member having an axis, a first end coupled on an airfoil, a second end terminating in a beveled surface, and the forward beveled member selectively rotatable about its axis with respect to the airfoil; an aft beveled memb
What is claimed is: 1. A flight control system, comprising: a forward beveled member having an axis, a first end coupled on an airfoil, a second end terminating in a beveled surface, and the forward beveled member selectively rotatable about its axis with respect to the airfoil; an aft beveled member having an axis, a first end coupled on a control surface, a second end terminating in a beveled surface that mates with the forward beveled member second end along an interface oblique to the axes of both members, and the aft beveled member selectively rotatable about its axis with respect to the control surface, so that when one of the forward or aft beveled members rotates with respect to the other, their contact along the oblique interface repositions the members with respect to one another to pivot the control surface with respect to the airfoil. 2. The flight control system of claim 1, wherein the forward bevel member and aft beveled member counter rotate at an about equal angular rate. 3. The flight control system of claim 1, wherein the control surface is hingedly coupled to the airfoil. 4. The flight control system of claim 1, wherein the operator mechanism further comprises a bearing at the interface of the forward beveled member and the aft beveled member. 5. The flight control system of claim 1, further comprising: a forward drive motor coupled to the forward beveled member; and an aft drive motor coupled to the aft beveled member. 6. The flight control system of claim 5, wherein: a universal drive shaft couples the aft drive motor to the aft beveled member; and the forward drive motor and aft drive motor are mounted on a forward chordwise axis within the airfoil. 7. The flight control system of claim 1, wherein the operator mechanism further comprises: a mid beveled member mounted between the forward beveled member and the aft beveled member, the mid beveled member to rotate to reposition the control surface. 8. The flight control system of claim 1, wherein the forward beveled member and the aft beveled members are contra beveled. 9. The flight control system of claim 1, wherein the forward chordwise axis and the aft chordwise axis are coaxial when the control surface is in a neutral position. 10. The flight control system of claim 1, wherein a mechanical advantage offered by the operator mechanism is maximized when the load on the control surface is also at a maximum. 11. The flight control system of claim 1, further comprising an elastomeric transition section joining the airfoil and the control surface. 12. An operator mechanism coupled between a control surface and an airfoil, comprising: a forward beveled member having an axis, an end coupled to the airfoil, another end having a bevel configuration, and selectively rotatable about its axis with respect to the airfoil; an aft beveled member having an axis, an end coupled to the control surface, another end having a beveled configuration, and the aft beveled member selectively rotatable about its axis with respect to the control surface; and a mid beveled member having an axis, an end with a bevel shaped configuration that mates with the end of the forward beveled member having the bevel and along a plane oriented oblique to the axes of the mid beveled and forward beveled members, and the mid beveled member having another end with a bevel shaped configuration that mates with the end of the aft beveled member having the bevel and along a plane oriented oblique to the axes of the mid beveled and aft beveled member, so that when at least one of the forward, aft, or mid beveled members is rotated, the control surface deflects with respect to the airfoil. 13. The flight control system of claim 12, further comprising a mid drive motor, an aft drive motor, a forward drive motor, at least one universal mid drive shaft that couples the at least one mid drive motor to the mid beveled member; and a universal drive shaft that couples the aft drive motor to the aft beveled member. 14. The flight control system of claim 13, further comprising: a drive motor a forward gearing mechanism coupled to the forward beveled member and the drive motor; at least one mid gearing mechanism coupled to the at least one mid beveled member and the drive motor; and an aft gearing mechanism coupled to the aft beveled member and the drive motor. 15. The flight control system of claim 12, wherein the axis of the forward beveled member, the axis of the mid beveled member, and the axis of the aft beveled member are coaxial when the operator mechanism is in a neutral position. 16. A method to reposition a control surface with respect to an airfoil, the method comprising: providing a control mechanism comprising: a first member having an axis, an end terminating along a plane oblique to the member axis and an opposite end coupled to the control surface and rotatable with respect to the control surface, a second member having an axis, an end that terminates along a plane oblique to the member axis and that is coupled to the beveled end of the first member, and an opposite end coupled to the airfoil and rotatable with respect to the airfoil; and changing the position of the first member with respect to the second member by rotating at least one of the first or second members about at least one of their respective axes to thereby deflect the control surface with respect to the airfoil. 17. The method of claim 16, wherein the control surface deflects at a substantially constant angular rate. 18. The method of claim 16 wherein the first member comprises a forward beveled member having the end coupled to the control surface and a mid beveled member, wherein the forward and mid beveled members are rotatable with respect to one another and are coupled along an interface lying in a plane oblique to the first member axis. 19. The method of claim 18, wherein the control surface deflects at a substantially constant angular rate. 20. The method of claim 18, wherein a single drive motor is coupled by individual gear mechanisms to each beveled member drive each beveled member.
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