Active prop rotor stability system
A system and method for adjusting a rotor blade upon detection of a harmful force exerted on an aircraft wing includes a sensor attached to the wing and a subsystem operably associated with the sensor. The method includes sensing the force exerted on the wing with the sensor and determining whether the sensed force is potentially harmful to the structural integrity of the wing. The method further includes counteracting the harmful force by adjusting the rotor blade movement.
1. A rotary aircraft comprising:
a fuselage;
a wing rigidly attached to the fuselage;
a rotary system pivotally attached to the wing, the rotary system having:
a plurality of rotor blades;
an actuator operably associated with the plurality of rotor blades; and
a control system operably associated with the rotary system, the control system having:
a first sensor carried on a pressure surface of the wing and a second sensor carried on the suction surface of the wing;
wherein the first sensor and the second sensor are operably associated with each other such that the first sensor senses movement of pressure surface of the wing and the second sensor senses movement of the suction surface of the wing, and wherein the sensed movement of the pressure surface and the sensed movement of the suction surface determine a bending movement exerted on the wing by the rotary system; and
a subsystem in data communication with the first sensor and the second sensor and configured to receive the sensed bending movement of the wing and determine whether the sensed bending movement is potentially harmful to the wing;
wherein the control system adjusts the movement of the plurality of blades via the actuators if the bending movement of the wing is potentially harmful.
2. The rotary aircraft of claim 1 , the rotary system further comprising:
a swashplate operably associated with the plurality of rotor blades, the swashplate being configured to adjust movement of the plurality of rotor blades.
3. The rotary aircraft of claim 2 ,
wherein the actuator is operably associated with the swashplate, the actuator being configured to adjust movement of the swashplate.
4. The rotary aircraft of claim 1 , wherein the control system adjusts the movement of the plurality of blades individually upon detection of a potentially harmful bending movement of the wing.
5. The rotary aircraft of claim 1 , the rotary system further comprising:
a mast; and
a yoke coupled to mast, the yoke being coupled to the plurality of rotor blades.
6. The rotary aircraft of claim 5 , wherein each of the plurality of rotor blades are coupled to the yoke with a delta-3 hinge having a delta-3 angle of about −45 degrees.
7. The rotary aircraft of claim 5 , wherein each of the plurality of rotor blades are coupled to the yoke with a delta-3 hinge having a delta-3 angle of greater than −15 degrees.
8. The rotary aircraft of claim 1 , wherein the plurality of rotor blades is at least three rotor blades.