Field installable and removable helicopter rotor blade vibration and blade tracking device
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-005/02
출원번호
US-0181822
(2008-07-29)
등록번호
US-8192162
(2012-06-05)
발명자
/ 주소
Loftus, Robert T.
McNulty, Michael J.
출원인 / 주소
Loftus, Robert T.
대리인 / 주소
The von Hellens Law Firm, Ltd.
인용정보
피인용 횟수 :
1인용 특허 :
11
초록▼
This invention provides convenient airframe vibration and tracking improvements of a helicopter rotor blade by use of an elastomer profile system that is attached through an adhesive system that allows convenient removal and relocation for use by the helicopter manufacturer or by the helicopter oper
This invention provides convenient airframe vibration and tracking improvements of a helicopter rotor blade by use of an elastomer profile system that is attached through an adhesive system that allows convenient removal and relocation for use by the helicopter manufacturer or by the helicopter operator in a field environment.
대표청구항▼
1. An elastomer profile useful for reducing airframe vibration and improving blade tracking of a helicopter rotor blade comprising: a) an elastomer material,b) wherein said elastomer profile substantially comprises said elastomer material,c) wherein said elastomer profile is adhered to said helicopt
1. An elastomer profile useful for reducing airframe vibration and improving blade tracking of a helicopter rotor blade comprising: a) an elastomer material,b) wherein said elastomer profile substantially comprises said elastomer material,c) wherein said elastomer profile is adhered to said helicopter rotor blade by use of a pressure sensitive adhesive,d) wherein said helicopter rotor blade is a main lifting rotor blade or a tail rotor blade,e) wherein the adherence of said pressure sensitive adhesive to said helicopter rotor blade is peelable by hand,f) wherein said elastomer profile is substantially the shape of an elongated wedge,g) wherein said elongated wedge has a ramp angle of less than 20 degrees inclusive,h) wherein said elongated wedge chord length is less than 20 percent inclusive of the length of the rotor chord dimension,i) wherein said elastomer profile is attached to the trailing edge of said helicopter rotor blade with respect to the motion of said helicopter rotor blade, andj) wherein said elastomer profile is adjustable by segment length, location, said cord length, said ramp angle, or number as required to correct said airframe vibration and said blade tracking simultaneously to a satisfactory condition according to a predetermined criterion, wherein said predetermined criterion is based on airframe vibration and blade tracking measurements. 2. The elastomer profile according to claim 1 wherein said peelable by hand is an adhesive strength between 2.8 to 6.6 lb per inch inclusive. 3. The elastomer profile according to claim 1 wherein said elastomer profile is oriented so that the trailing edge of said elongated wedge is substantially aligned with the trailing edge of said helicopter rotor blade. 4. The elastomer profile according to claim 1 wherein said elastomer material has a durometer between 10 to 100 inclusive as measured on the Shore A scale. 5. The elastomer profile according to claim 4 wherein said elastomer material has a durometer between 50 to 70 inclusive as measured on the Shore A scale. 6. The elastomer profile according to claim 4 wherein said elastomer material is EPDM. 7. The elastomer profile according to claim 1 wherein said elastomer profile has a) a leading edge thickness between 0.005 to 0.010 inches inclusive,b) said ramp angle is between 3 to 12 degrees inclusive, andc) said elongated wedge chord length is between 2 to 10 percent inclusive of the length of the rotor chord dimension. 8. The elastomer profile according to claim 1 wherein said elastomer profile is part of an assembly, wherein said assembly comprises in order: said elastomer material, said pressure sensitive adhesive which is adhered to a major surface of said elastomer profile, and a removable protective barrier membrane. 9. The elastomer profile according to claim 1 wherein at least one end of said elastomer profile is adapted to reduce noise while said helicopter rotor blade is rotating. 10. The elastomer profile according to claim 9 wherein said adapted end is: i) at a non perpendicular angle to the span dimension of said elastomer profile, wherein said non perpendicular angle is based on rotation relative to a first reference axis, wherein said first reference axis is perpendicular to the exterior surface of said elastomer profile,ii) at a slant angle relative to the exterior surface of said elastomer profile, wherein said slant angle is based on rotation relative to a second reference axis, wherein said second reference axis is parallel to the exterior surface of said elastomer profile and perpendicular to the span direction of said elastomer profile,iii) a radial curve with respect to the exterior surface of said elastomer profile, wherein said radial curve is based on a radius relative to a third reference axis that is parallel to said second reference axis, oriv) a combination of at least two of i, ii, and iii above. 11. A wedge detachably attachable to a rotor blade of a helicopter for reducing blade pitching moment dynamic unbalance and aircraft vibrations, said wedge comprising: a) said wedge having a length selectable to effectively reduce blade pitching moment dynamic unbalance and aircraft vibrations;b) said wedge having a triangular shape in cross-section; andc) a peelable pressure sensitive adhesive for detachably attaching said wedge to the rotor blade. 12. The wedge as set forth in claim 11 including a removable protective membrane adjacent said pressure sensitive adhesive. 13. The wedge as set forth in claim 11 wherein said pressure sensitive adhesive is adapted to accommodate detachment by hand of said wedge from the rotor blade. 14. The wedge as set forth in claim 11 wherein said wedge is a truncated triangle in cross section. 15. The wedge as set forth in claim 14 wherein said wedge has a ramp angle of less than 20 degrees. 16. The wedge as set forth in claim 15 wherein the ramp angle is in the range of 3 to 12 degrees. 17. The wedge as set forth in claim 11 wherein the chord of said wedge is less than 20 percent of the chord of the rotor blade to which it is to be attached. 18. The wedge as set forth in claim 11 wherein said wedge is selectively detachably attachable to the main rotor blade or the tail rotor blade of the helicopter. 19. The wedge as set forth in claim 11 wherein said wedge is of elastomer material. 20. A method for reducing airframe vibration and improving blade tracking of a helicopter rotor blade, said method comprising the steps of: a) selecting a wedge having a ramp angle of up to 20 degrees from the leading edge to the trailing edge and a bottom surface;b) removing a protective membrane from a peelable adhesive disposed at the bottom surface of the wedge;c) placing the trailing edge of the wedge at the trailing edge of the rotor blade to extend forwardly therefrom along either the upper or lower surface of the rotor blade; andd) manually pressing the wedge on the rotor blade to detachably adhere the wedge to the rotor blade. 21. The method as set forth in claim 20 including the step of manually peeling the wedge from the rotor blade.
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이 특허에 인용된 특허 (11)
Sewersky Richard A. (Cheshire CT) Molnar George A. (Orange CT) Pratt Joseph L. (Shelton CT), Automated helicopter maintenance monitoring.
Charles Bruce D. ; Hassan Ahmed A. ; Tadghighi Hormoz ; JanakiRam Ram D. ; Sankar Lakshmi N., Blade vortex interaction noise reduction techniques for a rotorcraft.
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