An aircraft system/method for propeller balancing. The system includes an inboard driver with a first and second inboard electromagnetic coil, the inboard driver and the first counterweight balancing rotor and the second counterweight balancing rotor centered around the aircraft propeller shaft rota
An aircraft system/method for propeller balancing. The system includes an inboard driver with a first and second inboard electromagnetic coil, the inboard driver and the first counterweight balancing rotor and the second counterweight balancing rotor centered around the aircraft propeller shaft rotating machine member with the first inboard electromagnetic coil proximate the first inboard magnets of the first counterweight balancing rotor, with the inboard electromagnetic coil driver proximate the rotation axis of the aircraft propeller shaft rotating machine member and the first counterweight balancing rotor outboard of the inboard electromagnetic coil driver with the first inboard electromagnetic coil generating a electromagnetic field to electromagnetically step the first inboard magnets of the at least first counterweight balancing rotor to electromagnetically actuate rotational movement of the first counterweight balancing rotor around the rotating machine member and relative to the inboard electromagnetic coil driver to a first rotor held balancing position.
대표청구항▼
1. A method of balancing an aircraft propeller system comprising: providing an aircraft propeller system with a rotating machine propeller shaft member which rotates around a rotation axis;providing a first counterweight balancing rotor, said first counterweight balancing rotor including a plurality
1. A method of balancing an aircraft propeller system comprising: providing an aircraft propeller system with a rotating machine propeller shaft member which rotates around a rotation axis;providing a first counterweight balancing rotor, said first counterweight balancing rotor including a plurality of first inboard magnets and a first outboard mass concentration;providing a second counterweight balancing rotor, said second counterweight balancing rotor including a plurality of second inboard magnets and a second outboard mass concentration;providing an inboard electromagnetic coil driver, said inboard electromagnetic coil driver including a first inboard electromagnetic coil, and a second inboard electromagnetic coil;rotationally supporting said inboard electromagnetic coil driver upon said rotating machine propeller shaft member, wherein said rotationally supporting includes a plurality of inboard bearing members, said inboard bearing members included within said inboard electromagnetic coil driver:disposing said inboard electromagnetic coil driver and said first counterweight balancing rotor and said second counterweight balancing rotor around said rotating machine propeller shaft member with said first inboard electromagnetic coil proximate said first inboard magnets of said first counterweight balancing rotor, said inboard electromagnetic coil driver proximate said rotation axis and said first counterweight balancing rotor outboard of said inboard electromagnetic coil driver;generating an electromagnetic field with said first inboard electromagnetic coil to electromagnetically step said first inboard magnets of said first counterweight balancing rotor to electromagnetically actuate rotational movement of said first counterweight balancing rotor around said rotating machine member and relative to said inboard electromagnetic coil driver;positioning said second inboard electromagnetic coil proximate said second counterweight balancing rotor, with said second inboard electromagnetic coil proximate said second inboard magnets of said second counterweight balancing rotor; andgenerating an electromagnetic field with said second inboard electromagnetic coil to electromagnetically step said second inboard magnets of said second counterweight balancing rotor to electromagnetically actuate rotational movement of said second counterweight balancing rotor around said rotation axis and relative to said inboard electromagnetic coil driver. 2. The method of claim 1, further comprising the step of restraining said inboard electromagnetic coil driver from rotating around said rotation axis. 3. The method of claim 2, wherein the step of restraining said inboard electromagnetic coil driver from rotating around said rotation axis includes providing a rotation restraint, and disposing said rotation restraint proximate said inboard electromagnetic coil driver, wherein said rotation restraint physically grounds said inboard electromagnetic coil driver to a nonrotating machine member. 4. The method of claim 3, further comprising the step of transmitting electricity through said rotation restraint using at least one electrical conductor to said inboard electromagnetic coil driver, said at least one electrical conductor positioned within said rotation restraint. 5. The method of claim 1, wherein said aircraft propeller system includes a propeller and an engine/gearbox, wherein the method further comprises the step of coupling said propeller and said engine/gearbox with said rotating machine propeller shaft member. 6. The method of claim 1, further comprising the steps of: rotationally supporting said first counterweight balancing rotor with a first rotor bearing support assembly;rotationally supporting said second counterweight balancing rotor with a second rotor bearing support assembly containing said first and second counterweight balancing rotors positioned within a rotating outer casing, said rotating outer casing housing said first and second counterweight balancing rotors, wherein said rotating outer casing is mechanically grounded to said rotating machine propeller shaft member with said first rotor bearing support assembly positioned between said first counterweight balancing rotor and an outboard circumference of said rotating outer casing, and with said second rotor bearing support assembly positioned between said second counterweight balancing rotor and said outboard circumference of said rotating outer casing. 7. The method as claimed in claim 6, including maintaining a liquid lubricant sealed inside said rotating outer casing. 8. The method as claimed in claim 6, wherein said rotating outer casing is comprised of a plurality of sealed welded casing members. 9. The method as claimed in claim 1, including monitoring a plurality of balancing rotor positions relative to said inboard electromagnetic coil driver to provide a monitored health characteristic of said aircraft propeller system. 10. The method as claimed in claim 9, including performing an aircraft maintenance repair procedure in relationship to said monitored health characteristic of said aircraft propeller system. 11. The method as claimed in claim 1, including monitoring a plurality of balancer sensor outputs to provide a monitored aircraft performance health characteristic. 12. An aircraft system, said aircraft system including a rotating machine member having a rotation axis about which said rotating machine member rotates around;a first counterweight balancing rotor, said first counterweight balancing rotor including a plurality of first inboard magnets and a first outboard mass concentration;a second counterweight balancing rotor, said second counterweight balancing rotor including a plurality of second inboard magnets and a second outboard mass concentration;an inboard electromagnetic coil driver, said inboard electromagnetic coil driver including a first inboard electromagnetic coil and a second inboard electromagnetic coil, wherein said inboard electromagnetic coil driver, said first counterweight balancing rotor, and said second counterweight balancing rotor are centered around said rotating machine member with said first inboard electromagnetic coil proximate said first inboard magnets of said first counterweight balancing rotor, wherein said inboard electromagnetic coil driver includes a plurality of inboard bearing members configured to rotationally support said inboard electromagnetic coil driver upon said rotating machine member;said inboard electromagnetic coil driver proximate said rotation axis and said first counterweight balancing rotor outboard of said inboard electromagnetic coil driver, wherein said first inboard electromagnetic coil is configured to generate an electromagnetic field capable of electromagnetically stepping said first inboard magnets of said first counterweight balancing rotor to electromagnetically actuate rotational movement of said first counterweight balancing rotor around said rotating machine member, wherein the rotational movement of said first counterweight balancing rotor is relative to said inboard electromagnetic coil driver to a first rotor held balancing position;said second inboard electromagnetic coil proximate said second counterweight balancing rotor;said second inboard electromagnetic coil proximate said second inboard magnets of said second counterweight balancing rotor, wherein said second inboard electromagnetic coil is configured to generate an electromagnetic field capable of electromagnetically stepping said second inboard magnets of said second counterweight balancing rotor to electromagnetically actuate rotational movement of said second counterweight balancing rotor around said rotation axis, wherein the rotational movement of said second counterweight balancing rotor is relative to said inboard electromagnetic coil driver to a second rotor held position. 13. The aircraft system as claimed in claim 12, including a rotation restraint, said rotation restraint disposed proximate said inboard electromagnetic coil driver wherein said rotation restraint is configured to physically ground said inboard electromagnetic coil driver to a nonrotating machine member. 14. The aircraft system as claimed in claim 13, wherein said rotation restraint includes an electrical circuit, said electrical circuit capable of transmitting electricity through said rotation restraint. 15. The aircraft system as claimed in claim 12, wherein said first counterweight balancing rotor is rotationally supported by a first rotor bearing support assembly, and said second counterweight balancing rotor is rotationally supported by a second rotor bearing support assembly, wherein said first and second counterweight balancing rotors are contained in a rotating outer casing, said rotating outer casing housing said first and second counterweight balancing rotors, wherein said rotating outer casing being mechanically grounded to said rotating machine member with said first rotor bearing support assembly positioned between said first counterweight balancing rotor and an outboard circumference of said rotating outer casing, and with said second rotor bearing support assembly positioned between said second counterweight balancing rotor and said outboard circumference of said rotating outer casing. 16. The aircraft system as claimed in claim 15, including a liquid lubricant sealed inside said rotating outer casing. 17. The aircraft system as claimed in claim 16, wherein said rotating outer casing is comprised of a plurality of sealed welded casing members. 18. A method of electromagnetically balancing a rotating machine member which rotates about a rotation axis, said method including: providing a first balancing rotor, said first balancing rotor including a plurality of first inboard magnets and a first outboard mass concentration;providing an inboard electromagnetic coil driver, said inboard electromagnetic coil driver being nonrotating and including at least a first inboard electromagnetic coil;disposing said inboard electromagnetic coil driver and said first balancing rotor around said rotating machine member with said first inboard electromagnetic coil proximate said first inboard magnets of said first balancing rotor, said inboard electromagnetic coil driver proximate said rotation axis and said first balancing rotor outboard of said inboard electromagnetic coil driver;generating an electromagnetic field with said first inboard electromagnetic coil; andelectromagnetically stepping said first inboard magnets of said first balancing rotor to electromagnetically actuate rotational movement of said first balancing rotor around said rotating machine member, wherein the rotation of said first balancing rotor is relative to said inboard electromagnetic coil driver. 19. The method as claimed in claim 18, further comprising a plurality of inboard bearing members, said plurality of inboard bearing members being included with said inboard electromagnetic coil driver, and rotationally supporting said inboard electromagnetic coil driver upon said rotating machine member with said inboard bearing members. 20. The method as claimed in claim 19, further comprising positioning a plurality of inboard roller bearings between said first inboard electromagnetic coil and said rotation axis in said inboard bearing members, said inboard bearing members including said plurality of inboard roller bearings between said first inboard electromagnetic coil and said rotation axis. 21. The method as claimed in claim 18, further comprising: providing a rotation restraint; anddisposing said rotation restraint proximate said inboard electromagnetic coil driver, wherein said rotation restraint physically grounds said inboard electromagnetic coil driver to a nonrotating machine member. 22. The method as claimed in claim 21, further comprising mechanically restraining said inboard electromagnetic coil driver with a circuit board within said rotation restraint and conducting electricity therewith. 23. The method as claimed in claim 22, further comprising coupling and decoupling a mating electrical connector on said nonrotating machine member with a rotation restraint electrical connector included with said rotation restraint. 24. The method as claimed in claim 18, further comprising: providing a second balancing rotor, said second balancing rotor including a plurality of second inboard magnets and a second outboard mass concentration;providing a second inboard electromagnetic coil, disposing said second inboard electromagnetic coil and second balancing rotor proximate said first inboard electromagnetic coil and said first balancing rotor, with said second inboard electromagnetic coil proximate said second inboard magnets of said second balancing rotor;generating an electromagnetic field with said second inboard electromagnetic coil; andelectromagnetically stepping said second inboard magnets of said second balancing rotor to electromagnetically actuate rotational movement of said second balancing rotor around said rotation axis, wherein the rotation of said second balancing rotor is relative to said inboard electromagnetic coil driver. 25. The method as claimed in claim 24, further comprising: providing a rotating center pole plate;disposing said rotating center pole plate between said first balancing rotor and said second balancing rotor, said rotating center pole plate physically grounded to said rotating machine member;rotating said rotating center pole plate along with said rotating machine member around said rotation axis, said rotating center pole plate providing a grounded rotating reference point for said first balancing rotor and said second balancing rotor to rotate, said first and second balancing rotors rotating relative to said rotation axis. 26. The method as claimed in claim 24, further comprising: providing a first rotor bearing support assembly and rotationally supporting said first balancing rotor with said first rotor bearing support assembly; andproviding a second rotor bearing support assembly and rotationally supporting said second balancing rotor with said second rotor bearing support assembly. 27. The method as claimed in claim 24, wherein said first balancing rotor has an outside diameter FCWROD and said first inboard electromagnetic coil has an outside diameter FEMCOD with FEMCODFEMCOD. 29. The method as claimed in claim 24, wherein said second balancing rotor has an outside diameter SCWROD and an inside diameter SCWRID and said second inboard electromagnetic coil has an outside diameter SEMCOD with SEMCODFEMCOD. 50. The method as claimed in claim 45, wherein said second balancing rotor has an outside diameter SCWROD and an inside diameter SCWRID and said second inboard electromagnetic coil has an outside diameter SEMCOD with SEMCODFEMCOD. 64. The electromagnetically actuated balancer as claimed in claim 59, wherein said second balancing rotor has an outside diameter SCWROD and an inside diameter SCWRID and said second inboard electromagnetic coil has an outside diameter SEMCOD with SEMCOD
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (17)
Zimmerman Ward H. (11044 Auburn Ave. South Seattle WA 98178), Aircraft propulsion control system.
Jolly, Mark; Hildebrand, Stephen; Altieri, Russell; Ferguson, Matthew; Ivers, Douglas, Helicopter vibration control system and rotary force generator for canceling vibrations.
Jolly,Mark; Hildebrand,Stephen; Altieri,Russell; Ferguson,Matthew; Ivers,Douglas, Helicopter vibration control system and rotary force generator for canceling vibrations.
Hildebrand, Stephen; Miller, Lane, Rotating machine active balancer and method of dynamically balancing a rotating machine shaft with torsional vibrations.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.