Systems and methods for structural health monitoring and protection

Patent metadata

Field	Value
Publication number	US-10486803-B2
Application number	US-201515303083-A
Country	US
Kind code	B2
Filing date	Apr 15, 2015
Priority date	Apr 15, 2014
Publication date	Nov 26, 2019
Grant date	Nov 26, 2019

Abstract

Structural health monitoring and protection systems and methods are provided. System and methods utilize structural information and/or enhanced built in testing capabilities for detecting failure modes that may cause damage to a structure. Systems and methods herein may protect a structure by mitigating one or more incorrect forces. The structure may be an aircraft, a rotary wing aircraft, or any other physical structure subject to vibrations and receptive to canceling of those vibrations.

First claim

What is claimed is:

1. A method of providing structural health monitoring and protection, the method comprising: providing an Active Vibration Control (AVC) system, comprising: at least one force generator (FG); at least one sensor detecting a structural vibration and generating a signal upon detecting a structural vibration; a controller in electronic communication with each of the at least one FG and the at least one sensor, wherein the controller receives the signal, generates at least one force command, and electronically communicates the at least one force command to the at least one FG, the electrical communication of the at least one force command causing the at least one FG to cancel the structural vibration; providing a Structural Health Monitoring (SHM) system comprising at least one structural health sensor detecting and measuring structural health information, the structural health information comprising at least one of structural load, a strain, or a vibration, wherein the at least one structural health sensor is separate from the at least one sensor of the AVC and generates a signal of the measured structural health information; communicating the measured structural health information from the SHM system to the controller in the AVC system via a communications interface disposed therebetween; within the controller, processing the signal communicated from the AVC system and the measured structural health information from the SHM system; correlating the structural health information with the structural vibration of the AVC system and determining if an incorrect force indicating an exceedance of at least one of structural load, a strain, or a vibration is being applied to a structure by the at least one FG, and if incorrect forces are being applied to a structure, then; determining and generating a corrective force command to mitigate the incorrect force at the controller; communicating the corrective force command to the FG; generating a corrective force with the FG based upon the corrective force command.

2. The method of claim 1 , wherein providing the at least one FG comprises providing at least one circular force generator (CFG), at least one linear FG, or a combination of at least one CFG and at least one linear FG.

3. The method of claim 1 , wherein providing the at least one sensor for measuring structural vibration comprises providing at least one accelerometer.

4. The method of claim 1 , wherein providing the at least one structural health sensor comprises providing at least one of a strain gauge, a tachometer, a load measurement node, or an accelerometer.

5. The method of claim 1 , wherein communicating structural health information comprises a communicating via at least one of a wired connection, a databus, or a wireless connection.

6. The method of claim 1 , wherein the exceedance of at least one of structural load, a strain, or a vibration further comprises measuring at least one structural load parameter using the at least one structural health sensor and electronically communicating the at least one structural load parameter as the structural health information from the SHM system to the controller.

7. The method of claim 6 , wherein measuring at least one structural load parameter comprises measuring at least one of a crack, a stiffness, an elongation, a vibration, a stress, a strain, or a load.

8. The method of claim 7 , further comprising estimating a remaining useful component life of an aircraft structural component.

9. The method of claim 1 , further comprising providing an electronics system in electrical communication with the AVC system.

10. The method of claim 9 , wherein providing an electronics system comprises providing an onboard Avionics/Health Usage and Monitory System (HUMS).

11. The method of claim 10 , further comprising communicating aircraft information received from an avionics databus regarding an operating regime to the AVC system via the Avionics/HUMS.

12. The method of claim 11 , wherein communicating the aircraft information received from the avionics databus includes communicating at least one of a weight-on-wheels (WoW), a gross vehicle weight, a maneuver loading, a forward flight speed, a main rotor speed, a collective position, or an engine torque.

13. The method of claim 1 , further comprising detecting a failure of the AVC system via the at least one structural health sensor and disabling the at least one FG when the failure is detected.

14. The method of claim 1 , further comprising adjusting the at least one force command using information communicated by the SHM system for staying below a critical structural load limit.

15. The method of claim 1 , further comprising, at the controller, receiving electronic communications and communicating an adaptive vibration control force to the FG thereby minimizing vibration, actively maintaining structural loads below a critical structural load limit.

Assignees

• Lord Corp

Inventors

• Black Paul
• Swanson Douglas
• Pedersen Douglas G
• Jolly Mark R
• Townsend Christopher
• Cassidy Ian

Classifications

• B64C2027/002

  mounted between the rotor drive and the fuselage · CPC title

• B64C2027/005

  using suspended masses · CPC title

• B64C27/001 Primary

  Vibration damping devices · CPC title

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title

• B64D2045/0085

  Devices for aircraft health monitoring, e.g. monitoring flutter or vibration · CPC title