| CPC B64C 27/57 (2013.01) [B64C 27/59 (2013.01)] | 13 Claims |
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1. An aircraft comprising:
a rotor assembly comprising:
a lower rotor hub assembly; and
an upper rotor hub assembly rotatably coupled to the lower rotor hub assembly, the upper rotor hub assembly comprising:
a central section; and
a blade pitch adjustment linkage coupling a plurality of rotor blades to opposite ends of the central section, the blade pitch adjustment linkage configured to maintain the plurality of rotor blades at a first blade pitch while a rotational velocity of the upper rotor hub assembly is slower than a first rotational velocity threshold and to maintain the plurality of rotor blades at a second blade pitch while the rotational velocity of the upper rotor hub assembly is faster than a second rotational velocity threshold; and
a blade pitch detection apparatus comprising:
a magnet coupled to a movable component of the blade pitch adjustment linkage that has a first orientation while the plurality of rotor blades are at the first blade pitch and a second orientation while the plurality of rotor blades are at the second blade pitch;
a sensor coupled to a component of the lower rotor hub assembly and configured to generate a signal in the presence of the magnet, wherein:
when the movable component is in the first orientation, the magnet repeatedly triggers the sensor to generate the signal while the upper rotor hub assembly is rotating, and
when the movable component is in the second orientation, the magnet does not trigger the sensor while the upper rotor hub assembly is rotating; and
processing circuitry in communication with the sensor and configured to determine whether the plurality of rotor blades are at the first blade pitch or the second blade pitch based on signals received from the sensor.
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