Automatic pitch change rotary wing rotor system and method of rotor control
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-011/00
B64C-027/02
B64C-027/54
A63H-027/00
B64C-027/52
출원번호
US-0818105
(2015-08-04)
등록번호
US-9586679
(2017-03-07)
발명자
/ 주소
Cupp, Sr., John Neal
Cupp, Jr., John Neal
출원인 / 주소
Cupp, Sr., John Neal
대리인 / 주소
Klein, O'Neill, Singh, LLP
인용정보
피인용 횟수 :
0인용 특허 :
7
초록▼
A helicopter main rotor control system includes a trunnion head mountable to a rotatable helicopter mast wherein the trunnion head has a control bar pivot supported by the trunnion head and pivotal about an axis substantially at a right angle to the helicopter mast. A control bar extends through the
A helicopter main rotor control system includes a trunnion head mountable to a rotatable helicopter mast wherein the trunnion head has a control bar pivot supported by the trunnion head and pivotal about an axis substantially at a right angle to the helicopter mast. A control bar extends through the control bar pivot at a right angle thereto, and a pair of opposing leaf hinges are pivotal about the control bar and centered about said trunnion head. Each leaf hinge has a hinge plate extending from the control bar and defines a rotor blade mount hole therethrough.
대표청구항▼
1. A rotor system comprising: a trunnion head mounted to a rotatable mast, said rotatable mast having a mast lengthwise axis;a control bar pivot having a pivot lengthwise axis, said control bar pivot supported by said trunnion head and pivotal about said pivot lengthwise axis, said pivot lengthwise
1. A rotor system comprising: a trunnion head mounted to a rotatable mast, said rotatable mast having a mast lengthwise axis;a control bar pivot having a pivot lengthwise axis, said control bar pivot supported by said trunnion head and pivotal about said pivot lengthwise axis, said pivot lengthwise axis being substantially at a right angle to said mast lengthwise axis;a control bar having a bar lengthwise axis, said control bar extending through said control bar pivot, said bar lengthwise axis being generally at a right angle to said pivot lengthwise axis; anda pair of opposing leaf hinges having a gap and pivotal about said bar lengthwise axis and having said trunnion head projecting, at least in part, through said gap, each of said leaf hinges having a hinge plate extending from said control bar and including a rotor blade mount hole extending through said hinge plate;wherein total lift generated by the rotor system is by rotational velocity of said mast without a collective pitch. 2. The rotor system according to claim 1, further including a rotor blade affixed to each of said hinge plates at said rotor blade mount hole and pivotal about a mount hole axis of said rotor blade mount hole. 3. The rotor system according to claim 2, wherein said rotor blades are pivotal through an arc of zero degrees to ninety degrees with respect to said bar lengthwise axis. 4. The rotor system according to claim 2, wherein said rotor blades are pivotal through an arc of fifteen to forty-five degrees with respect to said bar lengthwise axis. 5. The rotor system according to claim 2, wherein said rotor blades are pivotal through an arc of twenty five to thirty degrees with respect to said bar lengthwise axis. 6. The rotor system according to claim 2, wherein each said rotor blade includes a cambered airfoil cross-section. 7. The rotor system according to claim 2, wherein a pitch angle of attack of each said rotor blade is fixed and nonrotatable with respect to a plane of said leaf hinge when said rotor blade is affixed at a ninety degree angle with respect to said bar lengthwise axis. 8. The rotor system according to claim 7, wherein each of said rotor blades is mounted a fixed distance above said hinge plate. 9. The rotor system according to claim 8, wherein each of said rotor blades is mounted with a hydraulic apparatus for adjusting a distance each said rotor blade is above said hinge plate. 10. The rotor system according to claim 8, wherein each of said rotor blades is mounted with a ball screw apparatus for adjusting a distance each said rotor blade is above said hinge plate. 11. The rotor system according to claim 1, wherein said control bar terminates at two distal ends of the control bar and further includes a weight affixed at each said end of said control bar. 12. A helicopter having a helicopter rotor control system comprising: a trunnion head mounted to a rotatable helicopter mast, said rotatable helicopter mast having a mast lengthwise axis;a control bar pivot having a pivot lengthwise axis, said control bar pivot supported by said trunnion head and pivotal about said pivot lengthwise axis, said pivot lengthwise axis being substantially at a right angle to said mast lengthwise axis;a control bar having a bar lengthwise axis, said control bar extending through said control bar pivot, said bar lengthwise axis being generally at a right angle to said pivot lengthwise axis;a pair of opposing leaf hinges pivotal about said bar lengthwise axis, each of said leaf hinges having a hinge plate extending from said control bar;a rotor blade affixed to each of said hinge plates, a pitch angle of the rotor blades changing according to the rotational velocity of the rotor blades; anda rotor tilting mechanism for directional control. 13. The helicopter according to claim 12, wherein said rotor tilting mechanism for directional control comprises a swash plate including control rods running to a yoke encircling said trunnion head and said mast. 14. The helicopter according to claim 12, wherein said rotor tilting mechanism for directional control comprises a mast tilting mechanism. 15. The helicopter according to claim 12, wherein the rotor blade is affixed to each said hinge plate at a rotor blade mount hole extending through said hinge plate and is pivotal about a mount hole axis of said rotor blade mount hole. 16. The helicopter according to claim 15, wherein a pitch angle of attack of each said rotor blade is fixed and non-rotatable with respect to a plane of said leaf hinge when said rotor is affixed at a ninety degree angle with respect to said bar lengthwise axis. 17. The helicopter according to claim 16, wherein each said rotor blade is mounted a fixed distance above said hinge plate. 18. The helicopter according to claim 17, wherein each of said rotor blades is mounted with a hydraulic apparatus for adjusting a distance each said rotor blade is above said hinge plate. 19. The helicopter according to claim 17, wherein each of said rotor blades is mounted with a ball screw apparatus for adjusting a distance each said rotor blade is above said hinge plate. 20. The helicopter according to claim 12, wherein said control bar terminates at two distal ends of the control bar and further includes a weight affixed at each said end of said control bar. 21. A method of using a rotor system without a collective pitch system, the rotor system comprising a trunnion head mounted to a rotatable mast, a control bar, a pair of opposing leaf hinges pivotal about said control bar and centered about said trunnion head, a pair of rotor blades, and a rotor tilting mechanism for directional control, said trunnion head including a control bar pivot supported by said trunnion head and pivotal about an axis substantially at a right angle to said helicopter mast, said control bar extending through said control bar pivot at a right angle to said control bar pivot, each of said leaf hinges having a hinge plate extending from said control bar and defining a rotor blade mount hole extending through said hinge plate, each of said rotor blades affixed to each of said hinge plates at said rotor blade mount hole, the method comprising: rotating the mast; andmaintaining rotational velocity so that an increase in rotational velocity increases lift.
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