초록 ▼

An aircraft system and method with a first counterweight rotating balancing rotor mass concentration, and a second counterweight rotating balancing rotor mass concentration to balance a first aircraft propeller. The system includes an inboard electromagnetic coil driver with a first inboard electrom

An aircraft system and method with a first counterweight rotating balancing rotor mass concentration, and a second counterweight rotating balancing rotor mass concentration to balance a first aircraft propeller. The system includes an inboard electromagnetic coil driver with a first inboard electromagnetic coil, and a second inboard electromagnetic coil, the inboard electromagnetic coil driver and the first counterweight balancing rotor and the second counterweight balancing rotor centered around the aircraft propeller shaft rotating machine member. The system/method utilizes a first control system controller to control the coils and position the mass concentrations to balance the first aircraft propeller. The system/method includes a third counterweight rotating balancing rotor mass concentration, and a fourth counterweight rotating balancing rotor mass concentration to balance a second aircraft propeller which positioned and controlled by a second control system controller.

대표청구항 ▼

1. A method of balancing aircraft propeller systems, said method comprising: providing an aircraft with at least a first propeller system with a first rotation axis and at least a second propeller system with a second rotation axis,providing a first means for actively balancing said first propeller

1. A method of balancing aircraft propeller systems, said method comprising: providing an aircraft with at least a first propeller system with a first rotation axis and at least a second propeller system with a second rotation axis,providing a first means for actively balancing said first propeller system during aircraft flight,providing a first control system controller and disposing said first control system controller proximate said first propeller system wherein said first control system controller controls said first means for actively balancing said first propeller system during aircraft flight,providing a second means for actively balancing said second propeller system during aircraft flight,providing a second control system controller and disposing said second control system controller proximate said second propeller system wherein said second control system controller controls said second means for actively balancing said second propeller system during aircraft flight,wherein providing a first means for actively balancing said first propeller system during aircraft flight, further includes: providing a first counterweight rotating balancing rotor with a first rotor bearing support flange arc oriented with a first mass concentration andproviding a second counterweight rotating balancing rotor with a second rotor bearing support flange arc oriented with a second mass concentration, with said first rotor bearing support flange arc retaining a first rotor outboard rotating bearing support assembly wherein said first counterweight rotating balancing rotor is rotationally supported by said first rotor outboard rotating bearing support assembly, and with said second rotor bearing support flange arc retaining a second rotor outboard rotating bearing support assembly wherein said second counterweight rotating balancing rotor is rotationally supported by said second rotor outboard rotating bearing support assembly. 2. A method as claimed in claim 1 wherein said first means includes: said first control system controller receiving a first counterweight rotating balancing rotor position signal and a second counterweight rotating balancing rotor position signal, andsaid first control system controller receiving a first propeller system vibration signal from a first vibration sensor sensing first propeller system vibrations proximate said first control system controller wherein said first control system controller positions a first and a second counterweight rotating balancing rotor to minimize said first propeller system vibrations. 3. A method as claimed in claim 2 wherein said second means includes: said second control system controller receiving a third counterweight rotating balancing rotor position signal and a fourth counterweight rotating balancing rotor position signal, andsaid second control system controller receiving a second propeller system vibration signal from a second vibration sensor sensing second propeller system vibrations proximate said second control system controller wherein said second control system controller positions a third and a fourth counterweight rotating balancing rotor to minimize said second propeller system vibrations. 4. A method as claimed in claim 3, including: providing a third aircraft propeller system with a third rotation axis,providing a third means for actively balancing said third propeller system during aircraft flight,providing a third control system controller and disposing said third control system controller proximate said third aircraft propeller system wherein said third control system controller controls said third means for actively balancing said third propeller system. 5. A method as claimed in claim 4 wherein said third means includes: said third control system controller receiving a fifth counterweight rotating balancing rotor position signal and a sixth counterweight rotating balancing rotor position signal, andsaid third control system controller receiving a third propeller system vibration signal from a third vibration sensor sensing third propeller system vibrations proximate said third control system controller wherein said third control system controller positions a third and a fourth counterweight rotating balancing rotor to minimize said third propeller system vibrations. 6. A method as claimed in claim 5, including: providing a fourth aircraft propeller system with a fourth rotation axis,providing a fourth means for actively balancing said fourth propeller system during aircraft flight,providing a fourth control system controller and disposing said fourth control system controller proximate said fourth propeller system wherein said fourth control system controller controls said fourth means for actively balancing said fourth propeller system during aircraft flight. 7. A method as claimed in claim 6 wherein said fourth means includes: said fourth control system controller receiving a seventh counterweight rotating balancing rotor position signal and an eighth counterweight rotating balancing rotor position signal, andsaid fourth control system controller receiving a fourth propeller system vibration signal from a fourth vibration sensor sensing fourth propeller system vibrations proximate said fourth control system controller wherein said fourth control system controller positions a seventh and an eighth counterweight rotating balancing rotor to minimize said fourth propeller system vibrations. 8. A method as claimed in claim 1 wherein providing a first means for actively balancing said first propeller system during aircraft flight includes providing a rotating outer casing with a decoupling void. 9. A method as claimed in claim 1 wherein providing a first means for actively balancing said first propeller system during aircraft flight includes providing a rotation restraint, said rotation restraint including a circuit board mechanically restraining an inboard nonrotating electromagnetic coil driver and conducting electricity. 10. A method as claimed in claim 9 wherein said rotation restraint includes a rotation restraint electrical connector for coupling and decoupling with a mating electrical connector on a nonrotating machine member. 11. A method of balancing aircraft propeller systems, said method comprising: providing an aircraft with at least a first propeller system with a first rotation axis and at least a second propeller system with a second rotation axis,providing a first means for actively balancing said first propeller system during aircraft flight,providing a first control system controller and disposing said first control system controller proximate said first propeller system wherein said first control system controller controls said first means for actively balancing said first propeller system during aircraft flight, wherein providing said first means for actively balancing said first propeller system during aircraft flight includes providing a rotation restraint, said rotation restraint including a circuit board mechanically restraining an inboard nonrotating electromagnetic coil driver and conducting electricity,providing a second means for actively balancing said second propeller system during aircraft flight,providing a second control system controller and disposing said second control system controller proximate said second propeller system wherein said second control system controller controls said second means for actively balancing said second propeller system during aircraft flight. 12. A method as claimed in claim 11 wherein said first means includes: said first control system controller receiving a first counterweight rotating balancing rotor position signal and a second counterweight rotating balancing rotor position signal, andsaid first control system controller receiving a first propeller system vibration signal from a first vibration sensor sensing first propeller system vibrations proximate said first control system controller wherein said first control system controller positions a first and a second counterweight rotating balancing rotor to minimize said first propeller system vibrations. 13. A method as claimed in claim 12 wherein said second means includes: said second control system controller receiving a third counterweight rotating balancing rotor position signal and a fourth counterweight rotating balancing rotor position signal, andsaid second control system controller receiving a second propeller system vibration signal from a second vibration sensor sensing second propeller system vibrations proximate said second control system controller wherein said second control system controller positions a third and a fourth counterweight rotating balancing rotor to minimize said second propeller system vibrations. 14. A method as claimed in claim 13, including: providing a third aircraft propeller system with a third rotation axis,providing a third means for actively balancing said third propeller system during aircraft flight,providing a third control system controller and disposing said third control system controller proximate said third aircraft propeller system wherein said third control system controller controls said third means for actively balancing said third propeller system. 15. A method as claimed in claim 14 wherein said third means includes: said third control system controller receiving a fifth counterweight rotating balancing rotor position signal and a sixth counterweight rotating balancing rotor position signal, andsaid third control system controller receiving a third propeller system vibration signal from a third vibration sensor sensing third propeller system vibrations proximate said third control system controller wherein said third control system controller positions a third and a fourth counterweight rotating balancing rotor to minimize said third propeller system vibrations. 16. A method as claimed in claim 15, including: providing a fourth aircraft propeller system with a fourth rotation axis,providing a fourth means for actively balancing said fourth propeller system during aircraft flight,providing a fourth control system controller and disposing said fourth control system controller proximate said fourth propeller system wherein said fourth control system controller controls said fourth means for actively balancing said fourth propeller system during aircraft flight. 17. A method as claimed in claim 16 wherein said fourth means includes: said fourth control system controller receiving a seventh counterweight rotating balancing rotor position signal and an eighth counterweight rotating balancing rotor position signal, andsaid fourth control system controller receiving a fourth propeller system vibration signal from a fourth vibration sensor sensing fourth propeller system vibrations proximate said fourth control system controller wherein said fourth control system controller positions a seventh and an eighth counterweight rotating balancing rotor to minimize said fourth propeller system vibrations. 18. A method as claimed in claim 11 wherein providing a first means for actively balancing said first propeller system during aircraft flight, includes: providing a first counterweight rotating balancing rotor with a first rotor bearing support flange arc oriented with a first mass concentration andproviding a second counterweight rotating balancing rotor with a second rotor bearing support flange arc oriented with a second mass concentration, with said first rotor bearing support flange arc retaining a first rotor outboard rotating bearing support assembly wherein said first counterweight rotating balancing rotor is rotationally supported by said first rotor outboard rotating bearing support assembly, and with said second rotor bearing support flange arc retaining a second rotor outboard rotating bearing support assembly wherein said second counterweight rotating balancing rotor is rotationally supported by said second rotor outboard rotating bearing support assembly. 19. A method as claimed in claim 11 wherein providing a first means for actively balancing said first propeller system during aircraft flight includes providing a rotating outer casing with a decoupling void. 20. A method as claimed in claim 11 wherein said rotation restraint includes a rotation restraint electrical connector for coupling and decoupling with a mating electrical connector on a nonrotating machine member.