IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0655299
(2000-09-05)
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발명자
/ 주소 |
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인용정보 |
피인용 횟수 :
1 인용 특허 :
1 |
초록
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This light aircraft crash avoidance system performs what previous such systems perform, but with much less system weight, much less cost and much less expenditure of electrical energy. In this system, air enters openings or windows in front of concentric tubing and leaves through openings facing ver
This light aircraft crash avoidance system performs what previous such systems perform, but with much less system weight, much less cost and much less expenditure of electrical energy. In this system, air enters openings or windows in front of concentric tubing and leaves through openings facing vertically downward, thus giving lift to an aircraft's wing, where needed. Unlike other designs, this one requires no high-pressure air tanks to provide high pressure, high-velocity air to air valves. The valves depend upon the forward motion of the aircraft to provide high velocity air and lift. Two different prime movers are suggested for rotating the outer tubing for opening or closing the air valve, one being a d.c. motor and the other a rotary solenoid, as the simpler one to implement. The proposed design is for making any needed corrections to the aircraft's roll angle and for providing buoyancy to the entire aircraft when making a landing. A side benefit for this design is the ability for the aircraft's engine to save fuel on take-off and in flight, because of the added lift provided by the tubular air valves in their open positions. Openings or air outlets facing downward may be fitted with circular collars to assist in directing the high velocity out-flow air downward.
대표청구항
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This light aircraft crash avoidance system performs what previous such systems perform, but with much less system weight, much less cost and much less expenditure of electrical energy. In this system, air enters openings or windows in front of concentric tubing and leaves through openings facing ver
This light aircraft crash avoidance system performs what previous such systems perform, but with much less system weight, much less cost and much less expenditure of electrical energy. In this system, air enters openings or windows in front of concentric tubing and leaves through openings facing vertically downward, thus giving lift to an aircraft's wing, where needed. Unlike other designs, this one requires no high-pressure air tanks to provide high pressure, high-velocity air to air valves. The valves depend upon the forward motion of the aircraft to provide high velocity air and lift. Two different prime movers are suggested for rotating the outer tubing for opening or closing the air valve, one being a d.c. motor and the other a rotary solenoid, as the simpler one to implement. The proposed design is for making any needed corrections to the aircraft's roll angle and for providing buoyancy to the entire aircraft when making a landing. A side benefit for this design is the ability for the aircraft's engine to save fuel on take-off and in flight, because of the added lift provided by the tubular air valves in their open positions. Openings or air outlets facing downward may be fitted with circular collars to assist in directing the high velocity out-flow air downward. the elongated member and being disposed between the belts; wherein flapping forces generated by the rotor blades are accommodated by the flexure regions; and wherein the mid-plane delamination durability of the composite flexure is increased. 8. The helicopter according to claim 7, wherein the laminated composite belts and the laminated composite off-axis layers are all formed from fiberglass fibers in an epoxy resin. 9. The helicopter according to claim 7, wherein the laminated composite belts and the laminated composite off-axis layers are all formed from fiberglass fibers in an epoxy resin having a designation S2/E773. 10. The helicopter according to claim 7, wherein the off-axis layers are oriented at ±45° relative to the longitudinal axis. 11. The helicopter according to claim 7, wherein each flexure region has a reduced thickness in a direction perpendicular to the plane of the belts, the reduction in thickness being from a reduction in the number of off-axis layers only. 12. The helicopter according to claim 7, further comprising: protective edge members disposed along exposed lateral edges of the elongated member. 13. A method of accommodating flapping forces in a helicopter rotor system, the method comprising the steps of: providing a helicopter having a fuselage and a drive means carried by the fuselage for actuating a drive mast; forming an elongated rotor yoke having an upper surface, a lower surface, a flexure region at each end, and a longitudinal axis, the formation of the rotor yoke comprising the steps of: forming the upper and lower surfaces from a plurality of laminated composite belts having composite fibers that are oriented along the longitudinal axis; and disposing a plurality of laminated composite off-axis layers having composite fibers that are oriented at selected angles to the longitudinal axis between the belts; and forming the flexure regions by selectively reducing the thickness of the rotor yoke in a direction perpendicular to the plane of the belts, the reduction in thickness being from a reduction in the number of off-axis layers only; coupling the rotor yoke to the drive mast; coupling a plurality of rotor blades to the rotor yoke; and accommodating flapping forces generated by the rotor blades with the flexure regions such that the mid-Diane delamination durability of the rotor yoke is increased. 14. The method according to claim 13, wherein the laminated composite belts and the laminated composite off-axis layers are all formed from fiberglass fibers in an epoxy resin. 15. The method according to claim 13, wherein the laminated composite belts and the laminated composite off-axis layers are all formed from fiberglass fibers in an epoxy resin having a designation S2/E773. 16. The method according to claim 13, wherein the off-axis layers are oriented at ±45° relative to the longitudinal axis. 17. A method to help prevent mid-plane delamination in a composite flapping flexure in a helicopter rotor system, the method comprising the steps of: providing a helicopter having a fuselage and a drive means carried by the fuselage for actuating a drive mast; forming an elongated rotor yoke having an upper surface, a lower surface, a flexure region at each end, and a longitudinal axis, the formation of the rotor yoke comprising the steps of: forming the upper and lower surfaces from a plurality of laminated composite belts having composite fibers that are oriented along the longitudinal axis; and disposing a plurality of laminated composite off-axis layers having composite fibers that are oriented at selected angles to the longitudinal axis between the belts; and forming the flexure regions by selectively reducing the thickness of the rotor yoke in a direction perpendicular to the plane of the belts, the reduction in thickness being from a reduction in the number of off-axis layers only; coupling the rotor yoke to the drive shaft; and coupling a plurality of rotor
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