Method and apparatus for proximity control between rotating and non-rotating aircraft components
The aircraft includes a rotor. The rotor includes a plurality of rotor blades. The aircraft further includes a non-rotating aircraft component. A proximity sensor is disposed with at least one of the non-rotating aircraft component and the rotor blades. A flight control computer is electrically coupled to the proximity sensor.
1. An aircraft rotor-proximity detection system comprising:
a rotor having a plurality of rotor blades;
a first proximity sensor disposed in a non-rotating aircraft component and configured to detect a proximity of a rotor blade of the plurality of rotor blades to the non-rotating component; and
a flight control computer in communication with the first proximity sensor.
2. The aircraft rotor-proximity detection system of claim 1 , wherein the first proximity sensor is configured to emit ultrasonic sound waves toward the plurality of rotor blades.
3. The aircraft rotor-proximity detection system of claim 1 , wherein the first proximity sensor is configured to measure air pressure.
4. The aircraft rotor-proximity detection system of claim 1 , wherein the first proximity sensor is configured to emit light waves toward the plurality of rotor blades.
5. The aircraft rotor-proximity detection system of claim 4 , wherein the first proximity sensor is oriented at an acute angle relative to an axis parallel to a mast of the rotor.
6. The aircraft rotor-proximity detection system of claim 1 , wherein the first proximity sensor comprises a light source and a receiver that form a first tripwire therebetween.
7. The aircraft rotor-proximity detection system of claim 6 , wherein the flight control computer is configured to issue a warning responsive to the first tripwire being tripped by the plurality of rotor blades.
8. The aircraft rotor-proximity detection system of claim 6 , comprising:
a second proximity sensor disposed in the non-rotating aircraft component;
wherein the second proximity sensor comprises a light source and a receiver that form a second tripwire therebetween.
9. The aircraft rotor-proximity detection system of claim 8 , wherein the flight control computer is configured to take a corrective action responsive to the second tripwire being tripped.
10. The aircraft rotor-proximity detection system of claim 9 , wherein the corrective action comprises adjusting at least one of a nacelle position, a rotor-blade position, a rotor speed, and a control surface position.
11. The aircraft rotor-proximity detection system of claim 1 , comprising:
at least one of an actuator and a servo motor electrically coupled to the flight control computer; and
wherein the flight control computer is operable to signal the at least one of the actuator and the servo motor to adjust a flight parameter responsive to a determination that the plurality of rotor blades are less than a minimum safe distance from the non-rotating aircraft component.
12. The aircraft rotor-proximity detection system of claim 11 , wherein the flight parameter includes at least one of a nacelle position, a rotor-blade position, a control surface position, or a landing gear position.
13. An aircraft rotor-proximity detection system comprising:
a rotor having a plurality of rotor blades;
a proximity sensor disposed in a non-rotating aircraft component, the proximity sensor configured to detect a proximity of the plurality of rotor blades to the non-rotating aircraft component by performing at least one of the following: emitting light waves toward the plurality of rotor blades, creating a tripwire for detection of a rotor blade of the plurality of rotor blades, measuring air pressure to determine a proximity of a rotor blade of the plurality of rotor blades, emitting ultrasonic soundwaves toward the plurality of rotor blades; and
wherein the proximity sensor is configured to present a warning to a pilot responsive to the plurality of rotor blades being located at least a minimum safe distance from the non-rotating aircraft component.
14. The aircraft rotor-proximity detection system of claim 13 , wherein the warning comprises at least one of a warning light, an audible alarm, and a vibration of a pilot's seat.
15. The aircraft rotor-proximity detection system of claim 13 , comprising a flight control computer in communication with the proximity sensor and configured to take a corrective action responsive to the plurality of rotor blades being located at least a minimum safe distance from the non-rotating aircraft component.
16. A method of controlling rotor-blade clearance, the method comprising:
measuring, via a proximity sensor disposed within a non-rotating component, a position of a rotor blade relative to the non-rotating aircraft component;
determining, via a flight control computer, if the rotor blade is located at least a minimum safe distance from the non-rotating aircraft component; and
responsive to a negative determination, initiating, via the flight control computer, a corrective action.
17. The method of claim 16 , wherein the proximity sensor is configured to emit ultrasonic sound waves toward the rotor blade.
18. The method of claim 16 , wherein the proximity sensor is configured to measure air pressure.
19. The method of claim 16 , wherein the proximity sensor is configured to emit light waves toward the rotor blade.
20. The method of claim 16 , wherein the proximity sensor comprises a light source and a receiver that form a tripwire therebetween.