Active system and method for vibration and noise reduction
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-027/51
출원번호
US-0952412
(2001-09-14)
발명자
/ 주소
Terpay, Gregory Weston
Zipfel, George G.
Welsh, William
출원인 / 주소
General Dynamics Advanced Information Systems, Inc.
대리인 / 주소
Moore & Van Allen PLLC
인용정보
피인용 횟수 :
29인용 특허 :
46
초록▼
An active mount is provided for use in a rotary wing aircraft between each of the gearbox and airframe mounting locations for mechanically suspending the airframe from the gearbox. The active mount comprises first and second linear hydraulic actuators each having a principal axis. The length of the
An active mount is provided for use in a rotary wing aircraft between each of the gearbox and airframe mounting locations for mechanically suspending the airframe from the gearbox. The active mount comprises first and second linear hydraulic actuators each having a principal axis. The length of the actuators is variable along the principal axis for providing relative movement between the airframe and the gearbox. The principal axes of the actuators are adapted to lie in the directional planes of the primary forces necessary for supporting the airframe and acting on the transmission gearbox mounting locations for providing movement of the gearbox relative to the airframe in the planes at a frequency for reducing the transfer of vibration through the active mount to the airframe. A system for reducing vibration in the rotary wing aircraft further comprises a hydraulic system for supplying a controlled flow of pressurized hydraulic fluid to the actuators.
대표청구항▼
An active mount is provided for use in a rotary wing aircraft between each of the gearbox and airframe mounting locations for mechanically suspending the airframe from the gearbox. The active mount comprises first and second linear hydraulic actuators each having a principal axis. The length of the
An active mount is provided for use in a rotary wing aircraft between each of the gearbox and airframe mounting locations for mechanically suspending the airframe from the gearbox. The active mount comprises first and second linear hydraulic actuators each having a principal axis. The length of the actuators is variable along the principal axis for providing relative movement between the airframe and the gearbox. The principal axes of the actuators are adapted to lie in the directional planes of the primary forces necessary for supporting the airframe and acting on the transmission gearbox mounting locations for providing movement of the gearbox relative to the airframe in the planes at a frequency for reducing the transfer of vibration through the active mount to the airframe. A system for reducing vibration in the rotary wing aircraft further comprises a hydraulic system for supplying a controlled flow of pressurized hydraulic fluid to the actuators. ched, if the missile was not affected by the said missile attachment, which said direction of travel is a forward direction of travel. 3. The missile of claim 2 wherein an electric motor is attached to the missile, which said electric motor is attached to the missile such that the electric motor can rotate the said tube such that the tube can be rotated in a controlled manner relative to the encircled part of the missile. 4. The missile of claim 2 wherein a lever is attached to the missile such that a part of the lever can be pushed towards the said tube so as to induce frictional force between the said lever and the tube. 5. The missile of claim 4 wherein an electric motor is used to move the said lever such that a part of the lever can be pushed towards the said tube such that frictional force between the said lever and the tube can be induced. 6. The missile of claim 1 wherein with the missile and the tube in a horizontal position such that the longitudinal axis of rotation of the tube is in a horizontal position and the protruding section protruding from the tube is in an upper most position on the tube, the said concave forward facing surface area faces a direction, which direction is a direction of travel that the missile would travel in when the missile is launched, if the missile was not affected by the said missile attachment, which said direction of travel is a forward direction of travel. 7. The missile of claim 6 wherein an electric motor is attached to the missile, which said electric motor is attached to the missile such that the electric motor can rotate the said tube such that the tube can be rotated in a controlled manner relative to the encircled part of the missile. 8. The missile of claim 6 wherein a lever is attached to the missile such that a part of the lever can be pushed towards the said tube so as to induce frictional force between the said lever and the tube. 9. The missile of claim 8 wherein an electric motor is used to move the said lever such that a part of the lever can be pushed towards the said tube such that frictional force between the said lever and the tube can be induced. 10. The missile of claim 1 wherein an electric motor is attached to the missile, which said electric motor is attached to the missile such that the electric motor can rotate the said tube such that the tube can be rotated in a controlled manner relative to the encircled part of the missile. 11. The missile of claim 1 wherein a lever is attached to the missile such that a part of the lever can be pushed towards the said tube so as to induce frictional force between the said lever and the tube. 12. The missile of claim 11 wherein an electric motor is used to move the said lever such that a part of the lever can be pushed towards the said tube such that frictional force between the said lever and the tube can be induced. 13. The missile of claim 1 wherein the said tube is in the form of a cylindrical tube. 14. A missile with a missile attachment which said missile attachment consists of a tube with a protruding section, which said protruding section protrudes outward from the tube, and which said protruding section has a forward facing surface area, with the said tube attached to the missile such that a part of the missile is encircled by the said tube and such that the said tube can be rotated continuously in one direction relative to the part of the missile that is encircled by the tube, with the protruding section able to complete numerous revolutions relative to the missile while revolving around the missile during continuous rotation of the tube around the encircled part of the missile, with the tube having a longitudinal axis of rotation and which said forward facing surface area is slanted forward such that the said forward facing surface area extends laterally away from the tube and such that as the forward facing surface area extends laterally away from the tube the forward facing surface area leans in a forward dir ection, and which said forward facing surface area is thus slanted forward relative to the longitudinal axis of rotation of the cylindrical tube, and such that if a plurality of lines are drawn radially away from the longitudinal axis of the tube, with each line drawn from a different point on the longitudinal axis to that of another line, and with the lines drawn from points on the longitudinal axis such that the lines could reach the forward facing surface area while drawn through an area in front of the forward facing surface area and while the lines are drawn parallel to one another, with the lines being of such respective lengths that the lines could make contact with the forward facing surface area while remaining parallel, but not be extended beyond the point of contact with the forward facing surface area, then one of the said lines would be shorter in length with respect to another of the said lines. 15. The missile of claim 14 wherein with the missile and the tube in a horizontal position such that the longitudinal axis of rotation of the tube is in a horizontal position and the protruding section protruding from the tube is in an upper most position on the tube, the said forward facing surface area faces a direction, which direction has as a component a direction of travel that the missile would travel in when the missile is launched, if the missile was not affected by the said missile attachment, which said direction of travel is a forward direction of travel. 16. The missile of claim 15 wherein an electric motor is attached to the missile, which said electric motor is attached to the missile such that the electric motor can rotate the said tube such that the tube can be rotated in a controlled manner relative to the encircled part of the missile. 17. The missile of claim 15 wherein a lever is attached to the missile such that a part of the lever can be pushed towards the said tube so as to induce frictional force between the said lever and the tube. 18. The missile of claim 17 wherein an electric motor is used to move the said lever such that a part of the lever can be pushed towards the said tube such that frictional force between the said lever and the tube can be induced. 19. The missile of claim 14 wherein with the missile and the tube in a horizontal position such that the longitudinal axis of rotation of the tube is in a horizontal position and the protruding section protruding from the tube is in an upper most position on the tube, the said forward facing surface area faces a direction, which direction is a direction of travel that the missile would travel in when the missile is launched, if the missile was not affected by the said missile attachment, which said direction of travel is a forward direction of travel. 20. The missile of claim 19 wherein an electric motor is attached to the missile, which said electric motor is attached to the missile such that the electric motor can rotate the said tube such that the tube can be rotated in a controlled manner relative to the encircled part of the missile. 21. The missile of claim 19 wherein a lever is attached to the missile such that a part of the lever can be pushed towards the said tube so as to induce frictional force between the said lever and the tube. 22. The missile of claim 21 wherein an electric motor is used to move the said lever such that a part of the lever can be pushed towards the said tube such that frictional force between the said lever and the tube can be induced. 23. The missile of claim 14 wherein an electric motor is attached to the missile, which said electric motor is attached to the missile such that the electric motor can rotate the said tube such that the tube can be rotated in a controlled manner relative to the encircled part of the missile. 24. The missile of claim 14 wherein a lever is attached to the missile such that a part of the lever can be pushed towards the said tube so as to induce frictional force between the said lever and the tube. 25. The missile of claim 24 wherein an electric motor is used to move the said lever such that a part of the lever can be pushed towards the said tube such that frictional force between the said lever and the tube can be induced. 26. The missile of claim 14 wherein the said tube is in the form of a cylindrical tube. 27. A missile with a missile attachment which said missile attachment consists of a tube with a protruding section, which said protruding section protrudes outward from the tube, and which said protruding section has a concave forward facing surface area, with the said tube attached to the missile such that a part of the missile is encircled by the said tube and such that the said tube is able to rotate relative to the part of the missile that is encircled by the tube, such that the said tube can be rotated continuously relative to the part of the missile that is encircled by the tube, with the protruding section able to complete numerous revolutions around the missile during flight through the continuous rotation of the tube around the encircled part of the missile, with the tube having a longitudinal axis of rotation, and which concave forward facing surface area is curved such that if the tube was placed in a horizontal position such that the longitudinal axis of rotation of the tube was placed in a horizontal position, and a side of the tube could be viewed while the tube was in the said horizontal position, and the protruding section was positioned on an upper most position on the tube such that the protruding section protruded above the tube, an outline of the concave forward facing surface area that protruded above the tube would appear concave with respect to the protruding section while a side of the tube is viewed from a position that is level in height to the longitudinal axis of rotation of the tube.
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