IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0280127
(2005-11-16)
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등록번호 |
US-7490792
(2009-02-17)
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발명자
/ 주소 |
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출원인 / 주소 |
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
5 인용 특허 :
11 |
초록
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A rotor aircraft has a fuselage with a rotor mounted above by a rotor shaft. An arm is pivotally engaged with a lower portion of the rotor shaft and pivotally engaged with the fuselage, enabling the rotor to move with little restriction vertically and horizontal in all directions relative to the fus
A rotor aircraft has a fuselage with a rotor mounted above by a rotor shaft. An arm is pivotally engaged with a lower portion of the rotor shaft and pivotally engaged with the fuselage, enabling the rotor to move with little restriction vertically and horizontal in all directions relative to the fuselage as the rotor rotates in order to isolate rotor oscillations. An infinitely variable air spring is used to counter vertical and fore and aft loads. Damping in the form of elastomeric materials, piston seal friction, and fluid flow through an orifice may be added as required.
대표청구항
▼
The invention claimed is: 1. A rotor aircraft, comprising: a fuselage; a rotor shaft extending upward from the fuselage; a rotor mounted to the rotor shaft; a drive mechanism in the fuselage for rotating the rotor shaft; and an isolation assembly mounted between the fuselage and the drive mechanism
The invention claimed is: 1. A rotor aircraft, comprising: a fuselage; a rotor shaft extending upward from the fuselage; a rotor mounted to the rotor shaft; a drive mechanism in the fuselage for rotating the rotor shaft; and an isolation assembly mounted between the fuselage and the drive mechanism for allowing translational oscillations of the rotor shaft due to rotation of the rotor, and for isolating at least part of the translational movement of the rotor shaft from the fuselage, the isolation assembly comprising: a pneumatic piston and cylinder operatively coupled between the rotor shaft and the fuselage, the piston and cylinder having an air volume that provides a natural frequency less than the rotational speed of the rotor during flight; a detector for detecting a position of the piston within the cylinder; and an air pressure source for urging the piston to a central position between ends of a stroke of the piston. 2. The aircraft according to claim 1, wherein the isolation assembly restricts the translational oscillations to a curvilinear path. 3. The aircraft according to claim 1, further comprising: a tilt assembly between the rotor shaft and the fuselage for selectively tilting the rotor shaft relative to the fuselage. 4. The aircraft according to claim 1, further comprising: a pneumatic tilt cylinder between the rotor shaft and the fuselage for inclining the rotor shaft relative to the fuselage to a selected angle, the tilt cylinder having a volume sized for allowing fore and aft oscillations of the rotor shaft due to rotation of the rotor. 5. The aircraft according to claim 1, wherein the drive mechanism comprises: a power source; a driven shaft coupled to the power source; and a gearbox having an input coupled to the driven shaft and an output to the rotor shaft; and wherein the isolation assembly further comprises: a support arm connected by a first pivot member to the fuselage and by a second pivot member to the gearbox, enabling arcuate movement of the gearbox about the first pivot member. 6. The aircraft according to claim 1, wherein the pneumatic cylinder is operatively coupled between the rotor shaft and the fuselage parallel to the rotor shaft, the pneumatic cylinder having a volume selected to keep its natural frequency below the rotational speed of the rotor. 7. The aircraft according to claim 1, wherein the drive mechanism comprises: a power source; a driven shaft coupled to the power source; and a gearbox having an input coupled to the driven shaft and an output to the rotor shaft; and wherein the isolation assembly further comprises: a support arm connected by a first pivot member to the fuselage and by a second pivot member to the gearbox, enabling arcuate movement of the gearbox about the first pivot member; and the pneumatic cylinder is coupled between the rotor shaft and the support arm. 8. The aircraft according to claim 1, further comprising: a gearbox mounted to the lower portion of the rotor shaft for oscillations with the rotor shaft; a pair of wings extending from the fuselage; a pair of propellers, each mounted to one of the wings; and a pair of propeller drive shafts, each extending from one of the propellers to the gearbox, the propeller drive shafts deflecting as the gearbox oscillates. 9. A rotor aircraft, comprising: a fuselage; a rotor shaft extending upward from the fuselage; a rotor mounted to the rotor shaft; a rotor assembly mounted to the lower portion of the rotor shaft; an arm pivotally engaged with a lower portion of the rotor assembly and pivotally engaged with the fuselage, the arm being pivotal relative to the fuselage between upper and lower positions, enabling the shaft, the rotor assembly and the arm to oscillate relative to the fuselage as the rotor rotates; and a bias member mounted between the arm and the fuselage for urging the arm to a central position between the upper and lower positions, the bias member comprising: a pneumatic cylinder having a piston that strokes therein in response to the oscillations of the shaft and the arm; a detector for detecting a position of the piston within the cylinder; and an air pressure source that varies air pressure to the pneumatic cylinder to urge the piston toward a substantially central position in the cylinder. 10. The aircraft according to claim 9, wherein the point where the arm pivotally engages the fuselage is aft of the point where the arm pivotally engages the lower portion of the rotor assembly. 11. The aircraft according to claim 9, further comprising: a pneumatic tilt cylinder having one end in cooperative engagement with the rotor shaft and another end pivotally carried by the fuselage for selectively tilting the rotor shaft about its lower portion relative to the fuselage, the tilt cylinder having a spring force allowing fore and aft oscillations of the rotor shaft relative to the fuselage regardless of the angle of tilt. 12. The aircraft according to claim 9, further comprising: a gearbox mounted to the lower portion of the rotor shaft, the gearbox being pivotally connected to the arm for oscillations with the rotor shaft; a pair of wings extending from the fuselage; a pair of propellers, each mounted to one of the wings; and a pair of propeller drive shafts, each extending from one of the propellers to the gearbox, the propeller drive shafts deflecting as the gearbox oscillates. 13. The aircraft according to claim 9, further comprising: a power source; a driven shaft coupled to the power source; a gearbox having an input coupled to the driven shaft and an output to the rotor shaft; and wherein: the arm is connected by a first pivot member to the fuselage and by a second pivot member to the gearbox, enabling arcuate movement of the gearbox about the first pivot member in unison with oscillations of the rotor shaft. 14. A gyroplane, comprising: a fuselage; a thrust means to propel the gyroplane forward; a rotor shaft extending upward from the fuselage; a rotor mounted to the rotor shaft, the rotor rotating at reduced speed during cruising conditions; a drive mechanism in the fuselage for rotating the rotor shaft; and an isolation assembly mounted between the fuselage and the drive mechanism for allowing translational oscillations of the rotor shaft due to rotation of the rotor, and for isolating at least part of the translational movement of the rotor shaft from the fuselage, the isolation assembly comprising: a pneumatic piston and cylinder operatively coupled between the rotor shaft and the fuselage, the piston and cylinder having an air volume that provides a natural frequency less than the rotational speed of the rotor during flight; a detector for detecting a position of the piston within the cylinder; and an air pressure source for urging the piston to a central position between ends of a stroke of the piston. 15. The aircraft according to claim 14, wherein the isolation assembly restricts the translational oscillations to a curvilinear path. 16. The aircraft according to claim 14, further comprising: a tilt assembly between the rotor shaft and the fuselage for selectively tilting the rotor shaft relative to the fuselage. 17. The aircraft according to claim 14, further comprising: a pneumatic tilt cylinder between the rotor shaft and the fuselage for inclining the rotor shaft relative to the fuselage to a selected angle, the tilt cylinder having a volume sized for allowing fore and aft oscillations of the rotor shaft due to rotation of the rotor. 18. The aircraft according to claim 14, wherein the drive mechanism comprises: a power source; a driven shaft coupled to the power source; and a gearbox having an input coupled to the driven shaft and an output to the rotor shaft; and wherein the isolation assembly further comprises: a support arm connected by a first pivot member to the fuselage and by a second pivot member to the gearbox, enabling arcuate movement of the gearbox about the first pivot member. 19. The aircraft according to claim 14, wherein the pneumatic cylinder is operatively coupled between the rotor shaft and the fuselage parallel to the rotor shaft, the pneumatic cylinder having a volume selected to keep its natural frequency below the rotational speed of the rotor. 20. The aircraft according to claim 14, wherein the drive mechanism comprises: a power source; a driven shaft coupled to the power source; and a gearbox having an input coupled to the driven shaft and an output to the rotor shaft; and wherein the isolation assembly further comprises: a support arm connected by a first pivot member to the fuselage and by a second pivot member to the gearbox, enabling arcuate movement of the gearbox about the first pivot member; and the pneumatic cylinder is coupled between the rotor shaft and the support arm. 21. The aircraft according to claim 14, further comprising: a gearbox mounted to the lower portion of the rotor shaft for oscillations with the rotor shaft; and a pair of wings extending from the fuselage; and wherein the thrust means comprises: a pair of propellers, each mounted to one of the wings; and a pair of propeller drive shafts, each extending from one of the propellers to the gearbox, the propeller drive shafts deflecting as the gearbox oscillates.
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