Method and apparatus for proximity control between rotating and non-rotating aircraft components

• US 10,583,916 B2
• Filed: 05/02/2019
• Issued: 03/10/2020
• Est. Priority Date: 07/02/2018
• Status: Active Grant

• Current Assignee: Textron Innovations Incorporated (Textron Inc)
• Original Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Inventors: Cravener, Kyle Thomas, Atkins, Brady Garrett, Cook, Stuart Benjamin, Vargas Calvet, Joaquin, White, Andrew Michael, Bailey, Karl, Jagneaux, Corrine, Mauga, Maika Lopati
• Primary Examiner(s): Marc, McDieunel
• Application Number:
  US16/401,332
• Publication Number:
  US 20200001979A1
• Time in Patent Office: 313 Days
• CPC Class Codes: B06B 1/0688 with foil-type piezoelectric elements, e.g. PVDF
• CPC Class Codes: B64C 11/06 for variable-pitch blades
• CPC Class Codes: B64C 11/301 characterised by blade position indicating means
• CPC Class Codes: B64C 11/305 characterised by being influenced by other control systems, e.g. fuel supply
• CPC Class Codes: B64C 13/16 actuated automatically, e.g. responsive to gust detectors
• CPC Class Codes: B64C 19/02 Conjoint controls
• CPC Class Codes: B64C 27/008 Rotors tracking or balancing devices
• CPC Class Codes: B64C 27/52 Tilting of rotor bodily relative to fuselage of see-saw type construction B64C27/43
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage
• CPC Class Codes: B64D 43/00 Arrangements or adaptations of instruments arrangements of cameras B64D47/08; aeronautical measuring instruments per se G01C
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00

Abstract

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.

Claims

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.