A motor assembly that includes a motor (102) having a rotatable shaft, a hub coupled to the rotatable shaft, the hub having a propeller indexer to receive a propeller (104), when the propeller is present, a sensor trigger rotatable with the shaft (100) and positioned at a propeller offset angle θPRO
A motor assembly that includes a motor (102) having a rotatable shaft, a hub coupled to the rotatable shaft, the hub having a propeller indexer to receive a propeller (104), when the propeller is present, a sensor trigger rotatable with the shaft (100) and positioned at a propeller offset angle θPROP from the propeller indexer, and a sensor coupled to the motor and positioned to detect the sensor trigger so that the propeller indexer may be positioned at the propeller offset angle θPROP from the sensor through rotation of the shaft so that said sensor is proximate to the sensor trigger.
대표청구항▼
1. A method of securing a propeller, comprising: commutating a sensor trigger by commutating a shaft of a motor, said motor having stators and rotors;commutating a propeller indexer by commutating said shaft, said propeller indexer configured to align a propeller, when a propeller is present, at an
1. A method of securing a propeller, comprising: commutating a sensor trigger by commutating a shaft of a motor, said motor having stators and rotors;commutating a propeller indexer by commutating said shaft, said propeller indexer configured to align a propeller, when a propeller is present, at an angular position that is a propeller offset angle θPROP from said sensor trigger as referenced by a center of rotation of said shaft;sensing said sensor trigger as said sensor trigger rotates to a point adjacent a sensor fixedly coupled to said motor; andswitching a control signal to rotatably hold said rotors driving said rotatable shaft in response to said sensor sensing said sensor trigger;wherein said propeller indexer may be held in position at the propeller offset angle θPROP from the sensor by commutating said shaft and holding the rotors so that the sensor is proximate to the sensor trigger; andwherein said propeller propels an aircraft having an aircraft wing, and wherein said sensing said sensor trigger step further comprises sensing said sensor trigger as said propeller aligns with the aircraft wing. 2. The method of claim 1, wherein said switching a control signal comprises turning off two of three phase circuits driving said rotors so that a third phase current remains to provide a holding force to said rotors so that said sensor trigger is proximate to said sensor. 3. The method of claim 2, further comprising: increasing current to said third phase circuit in response to said sensor sensing said sensor trigger is drifting away from said sensor. 4. The method of claim 3, further comprising: commutating said shaft in response to said sensor trigger drifting away from said sensor. 5. The method of claim 3, further comprising: holding said increasing current at a maximum holding current to recapture said sensor trigger; andreducing said maximum holding current to a nominal holding current in response to said sensor sensing said sensor trigger. 6. The method of claim 1, wherein said sensing said sensor trigger comprises sensing a magnet using a Hall Effect sensor. 7. The method of claim 1, wherein said sensor trigger is a mirror and said sensing said sensor trigger comprises sensing electromagnetic radiation reflected by said mirror. 8. A method of securing a propeller, comprising: commutating a sensor trigger by commutating a shaft of a motor, said motor having stators and rotors;commutating a propeller indexer by commutating said shaft, said propeller indexer configured to align a propeller, when a propeller is present, at an angular position that is a propeller offset angle θPROP from said sensor trigger as referenced by a center of rotation of said shaft;sensing said sensor trigger as said sensor trigger rotates to a point adjacent a sensor fixedly coupled to said motor;switching a control signal to rotatably hold said rotors driving said rotatable shaft in response to said sensor sensing said sensor trigger;calculating a sensor trigger angular location verses timedetermining said sensor trigger will not pass said sensor in a next rotation of the sensor trigger; andinitiating said switching said motor to electrically couple phase circuits in response to said determining said sensor will not pass said sensor in a next rotation of the sensor trigger step;wherein said propeller indexer may be held in position at the propeller offset angle θPROP from the sensor by commutating said shaft and holding the rotors so that the sensor is proximate to the sensor trigger; andwherein said switching a control signal to rotatably hold said rotors comprises switching the motor to electrically couple phase circuits to magnetically hold said rotors. 9. The method of claim 8, wherein said initiating said switching motor to electrically couple phase circuits further comprises calculating a nearest position of said sensor trigger to said sensor for a next rotation of said sensor trigger and initiating said switching motor to electrically couple said phase circuits at said nearest position. 10. A method of securing a propeller, comprising: commutating a sensor trigger by commutating a shaft of a motor, said motor having stators and rotors;commutating a propeller indexer by commutating said shaft, said propeller indexer configured to align a propeller, when a propeller is present, at an angular position that is a propeller offset angle θPROP from said sensor trigger as referenced by a center of rotation of said shaft;sensing said sensor trigger as said sensor trigger rotates to a point adjacent a sensor fixedly coupled to said motor; andswitching a control signal to rotatably hold said rotors driving said rotatable shaft in response to said sensor sensing said sensor trigger;wherein said propeller indexer may be held in position at the propeller offset angle θPROP from the sensor by commutating said shaft and holding the rotors so that the sensor is proximate to the sensor trigger; andwherein said propeller propels an aircraft having an aircraft wing and wherein said sensing said sensor trigger step further comprises sensing said sensor trigger as said propeller is not aligned with the aircraft wing. 11. A motor assembly, comprising: a motor having a rotatable shaft;a hub coupled to said rotatable shaft, said hub having a propeller indexer to receive a propeller, when the propeller is present;a sensor trigger rotatable with said shaft and positioned at a propeller offset angle θPROP from said propeller indexer; anda sensor coupled to said motor and positioned to detect said sensor trigger;wherein said propeller indexer is positioned at the propeller offset angle θPROP from the sensor through rotation of said shaft so that said sensor is proximate to the sensor trigger, and wherein said sensor trigger is coupled to said propeller. 12. The assembly of claim 11, wherein said sensor trigger is a magnet. 13. The assembly of claim 12, wherein said sensor is a Hall Effect sensor. 14. The assembly of claim 11, wherein said sensor trigger is coupled to said hub. 15. The assembly of claim 14, further comprising: a second sensor trigger coupled to said hub on a side of said hub opposite from said sensor trigger to weightably balance said hub. 16. The assembly of claim 11, wherein said sensor trigger is a mirror. 17. The assembly of claim 16, wherein said sensor is an infrared detector. 18. The assembly of claim 16, wherein said sensor is a light detector. 19. The assembly of claim 11, wherein said propeller indexer is a channel to receive said propeller. 20. The assembly of claim 11, wherein said propeller indexer is a tab to seat said propeller. 21. A motor assembly, comprising: an aircraft having a wing;a motor coupled to said aircraft to provide propulsion, said motor having a rotatable shaft;a hub coupled to said rotatable shaft, said hub having a propeller indexer to receive a propeller, when a propeller is present;a magnet coupled to said hub;a Hall Effect sensor coupled to an interior casing for said motor; anda motor controller electrically coupled to said motor, said motor controller configured to commutate said propeller to a horizontal position indicated by the proximity of said Hall Effect sensor to said magnetwherein the propeller, if present, is aligned with said wing, the alignment based on the proximity of said Hall Effect sensor to said magnet. 22. The assembly of claim 21, further comprising: a second magnet coupled to said hub on a side of said hub opposite from said magnet to weightably balance said hub. 23. A motor assembly, comprising: an aircraft having a wing;a motor mounted in said aircraft, said motor having a rotatable shaft;a propeller coupled to said rotatable shaft, said propeller having a magnet;a Hall Effect sensor coupled to an interior casing for said motor to detect said magnet; anda motor controller electrically coupled to said motor, said motor controller configured to commutate said propeller to a horizontal position indicated by a proximal location of said Hall Effect sensor with said magnetwherein said Hall Effect sensor is proximate to said magnet when said propeller is aligned with said wing. 24. A motor assembly, comprising: a motor having a rotatable shaft;a hub coupled to said rotatable shaft, said hub having a propeller indexer to receive a propeller, when a propeller is present;sensor trigger means rotatable with said shaft; andsensor means fixedly coupled to said motor and positioned to detect said sensor trigger means;wherein said sensor means and said sensor trigger means are aligned when said propeller is in a horizontal position, wherein said sensor trigger means is a magnet, wherein said sensor means is a Hall Effect sensor, and wherein said sensor trigger means is coupled to said propeller.
Tribe Alex E. (Thousand Oaks CA) Bottorff Marion R. (Ventura CA) Cottrell Ronald G. (Thousand Oaks CA) Ranes Richard L. (Simi Valley CA) Whistler William B. (Thousand Oaks CA), Aircraft.
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