A hybrid aircraft , comprising: a fixed-wing propulsion system configured to fly the aircraft once airborne; a multirotor propulsion system configured to allow the aircraft to take-off and land vertically, the multirotor propulsion system comprising: a propeller coupled to a first distal end of a motor shaft , the motor shaft drivable using a motor ; a motor mount mechanically coupled to the motor , the motor mount coupling the motor to the multirotor propulsion system ; a flywheel mechanically coupled to a second distal end of the motor shaft ; a magnetic orientation detent, the magnetic orientation detent comprising: a first plurality of magnets coupled to the motor mount ; and a second plurality of magnets coupled to the flywheel , wherein the first and second plurality of magnets magnetically couple when power is removed from the multirotor propulsion system ; and a processor configured to remove power from the multirotor propulsion system, the processor operable to execute a locking drive scheme, wherein, after the power is removed from the multirotor propulsion system, power is restored sufficient to allow the locking drive scheme to cause the motor to drive the motor shaft to rotate with a torque lower than required to overcome the magnetic coupling of the first and second plurality of magnets . a fixed-wing propulsion system configured to fly the aircraft once airborne; a multirotor propulsion system configured to allow the aircraft to take-off and land vertically, the multirotor propulsion system comprising: a propeller coupled to a first distal end of a motor shaft , the motor shaft drivable using a motor ; a motor mount mechanically coupled to the motor , the motor mount coupling the motor to the multirotor propulsion system ; a flywheel mechanically coupled to a second distal end of the motor shaft ; a magnetic orientation detent, the magnetic orientation detent comprising: a first plurality of magnets coupled to the motor mount ; and a second plurality of magnets coupled to the flywheel , wherein the first and second plurality of magnets magnetically couple when power is removed from the multirotor propulsion system ; and a propeller coupled to a first distal end of a motor shaft , the motor shaft drivable using a motor ; a motor mount mechanically coupled to the motor , the motor mount coupling the motor to the multirotor propulsion system ; a flywheel mechanically coupled to a second distal end of the motor shaft ; a magnetic orientation detent, the magnetic orientation detent comprising: a first plurality of magnets coupled to the motor mount ; and a second plurality of magnets coupled to the flywheel , wherein the first and second plurality of magnets magnetically couple when power is removed from the multirotor propulsion system ; and a first plurality of magnets coupled to the motor mount ; and a second plurality of magnets coupled to the flywheel , wherein the first and second plurality of magnets magnetically couple when power is removed from the multirotor propulsion system ; and a processor configured to remove power from the multirotor propulsion system, the processor operable to execute a locking drive scheme, wherein, after the power is removed from the multirotor propulsion system, power is restored sufficient to allow the locking drive scheme to cause the motor to drive the motor shaft to rotate with a torque lower than required to overcome the magnetic coupling of the first and second plurality of magnets . <EOS>