Apparatus for in-situ nondestructive measurement of young's modulus of plate structures

• US 20030233876A1
• Filed: 04/24/2003
• Published: 12/25/2003
• Est. Priority Date: 06/22/2000
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Huang, Jerry Qixin, DeLangis, Leo M., Perez, Robert J.
• Granted Patent: US 6,920,790 B2
• Time in Patent Office: Days
• US Class Current: 73/574
• CPC Class Codes: G01M 5/00 Investigating the elasticity of structures, e.g. deflection of bridges or air-craft wings G01M9/00 takes precedence
• CPC Class Codes: G01M 5/0016 of aircraft wings or blades
• CPC Class Codes: G01M 5/0041 by determining deflection or stress
• CPC Class Codes: G01N 2203/0055 using mechanical waves, e.g. acoustic
• CPC Class Codes: G01N 2203/0075 Strain-stress relations or elastic constants
• CPC Class Codes: G01N 2203/0282 Two dimensional, e.g. tapes, webs, sheets, strips, disks or membranes
• CPC Class Codes: G01N 2203/0658 using acoustic or ultrasonic detectors
• CPC Class Codes: G01N 2291/0231 Composite or layered materials
• CPC Class Codes: G01N 2291/0258 Structural degradation, e.g. fatigue of composites, ageing of oils
• CPC Class Codes: G01N 2291/02827 Elastic parameters, strength or force
• CPC Class Codes: G01N 2291/0421 Longitudinal waves
• CPC Class Codes: G01N 2291/048 Transmission, i.e. analysed material between transmitter and receiver
• CPC Class Codes: G01N 2291/102 one emitter, one receiver
• CPC Class Codes: G01N 2291/2694 Wings or other aircraft parts
• CPC Class Codes: G01N 29/07 by measuring propagation velocity or propagation time of acoustic waves
• CPC Class Codes: G01N 3/32 by applying repeated or pulsating forces
• CPC Class Codes: G01N 3/38 generated by electromagnetic means

Abstract

A method and apparatus for determining stiffness of a plate-like structure including a monolithic or composite laminate plate entails disposing a device for generating an acoustical pulse against a surface of the plate and disposing a detecting device against the same surface spaced a known distance from the pulse-generating device, and using the pulse-generating device to emit a pulse so as to create an extensional wave in the plate. The detecting device is used to determine a time of flight of the wave over the known distance, and the wave velocity is calculated. A Young'"'"'s modulus of the plate is determined by a processor based on the wave velocity. Methods and apparatus for evaluating both isotropic plates and anisotropic laminates are disclosed.

Claims

1. An apparatus for quantitatively evaluating a material stiffness of a composite laminate plate along an in-plane direction, the plate having a plurality of plies arranged in a balanced symmetric ply lay-up and having opposite major surfaces defining a thickness of the plate therebetween, the apparatus comprising:

a transducer for initiating an elastic extensional-mode wave that propagates through the plate along said in-plane direction;

a sensor, spaced apart from said transducer by a distance d, for detecting arrival of the extensional-mode wave; and

a processor, responsive to said transducer and said sensor, for calculating a material stiffness of the plate along said in-plane direction based on the distance d and an elapsed time between the initiation of the extensional-mode wave by said transducer and the arrival of the extensional-mode wave at said sensor.

2. The apparatus of claim 1, wherein said transducer is in acoustical communication with the plate at a first point located on a first of the major surfaces of the plate so as to cause the extensional-mode wave to originate at said first point and propagate along the plate.

3. The apparatus of claim 2, wherein said sensor is in acoustical communication with the plate at a second point located on said first major surface and spaced in said in-plane direction from the first point by the distance d.

4. The apparatus of claim 3 wherein said processor calculates the material stiffness of the plate along the in-plane direction based on the distance d between the first and second points along said first major surface of the plane in said in-plane direction and the elapsed time t required for the extensional-mode wave to travel the distance d from the first point to the second point.

5. The apparatus of claim 1, wherein the processor calculates the material stiffness by calculating a Young'"'"'s modulus along said in-plane direction.

6. The apparatus of claim 5, adapted for evaluating a quasi-isotropic composite laminate plate, wherein said processor calculates the Young'"'"'s modulus E based on the equation

E=(1−

ν

²)ρ

(d/t)²,

where ν

is a predetermined Poisson'"'"'s ratio for the material of the plate and ρ

is a predetermined density of the material of the plate.

7. The apparatus of claim 1, wherein said transducer imparts energy to the plate by using acoustic energy to create the extensional-mode wave.

8. The apparatus of claim 7, wherein said transducer is disposed against the first major surface of the plate at the first point and is activated to emit acoustic energy.

9. The apparatus of claim 8, wherein said sensor comprises an acoustic energy detector disposed against the first major surface of the plate at the second point.

10. The apparatus of claim 1 adapted to quantitatively evaluate Young'"'"'s moduli of the composite laminate plate along two orthogonal in-plane x- and y-directions of the plate, wherein said processor determines a velocity c_x of the extensional wave along said x-direction, determines a velocity c_y of the extensional wave along said y-direction, and determines Young'"'"'s moduli E_xx and E_yy respectively along the x- and y-directions by solving a set of simultaneous equations relating the extensional wave velocities, the Young'"'"'s moduli, and Poisson'"'"'s ratios and in-plane stiffness parameters for the plate to one another.

11. The apparatus of claim 10, wherein said processor determines the Young'"'"'s moduli E_xx and E_yy by solving the set of equations:

C_x={square root}{square root over (A₁₁/ρ

h)}

C_y={square root}{square root over (A₂₂/ρ

h)}

12. The apparatus of claim 1 wherein said transducer and said sensor are permanently bonded to the first major surface of the plate.

13. The apparatus of claim 1, wherein said transducer and said sensor are disposed upon a portion of an aircraft that includes the composite laminate plane.

14. An apparatus for quantitatively evaluating a change in Young'"'"'s modulus of a composite laminate plate along an in-plane direction, the plate having a plurality of plies arranged in a balanced symmetric ply lay-up and having opposite major surfaces defining a thickness of the plate therebetween, the apparatus comprising:

a transducer for imparting energy to the plate so as to cause extensional-mode waves to originate and propagate along the plate in said in-plane direction;

a sensor for detecting arrival of a respective extensional-mode wave, said sensor spaced a predetermined distance d in said in-plane direction from said transducer; and

a processor for determining an elapsed time t required for a respective extensional-mode wave to travel the predetermined distance d during both a first test from which t₁ is determined and a subsequent second test from which t₂ is determined, and for separately calculating Young'"'"'s modulus for the plate along said in-plane direction for both the first and second tests, said processor also adapted to calculate a change in Young'"'"'s modulus for the plate along said in-plane direction based on a degree of difference of the times t₁ and t₂.

15. The apparatus of claim 14, wherein said transducer and said sensor originate and detect the extensional-mode waves at two different times, whereby the change in Young'"'"'s modulus represents a change over time.

16. The apparatus of claim 15, wherein said processor calculates the change in Young'"'"'s modulus based on an assumption that density and Poisson'"'"'s ratio for the material of the plate are constant between the two different times at which the f extensional-mode waves are originated and detected.

17. The apparatus of claim 14, wherein said processor calculates the change in Young'"'"'s modulus based upon the Young'"'"'s modulis calculated for the first test and further based on a ratio of the times t₁ and t₂.

18. The apparatus of claim 17, wherein said processor calculates the ratio of Young'"'"'s moduli by the equation

E₂/E₁=(t₁/t₂)²,

where E₁ is Young'"'"'s modulus from the first test and E₂ is Young'"'"'s modulus from the second test.

19. The apparatus of claim 14 wherein said transducer and said sensor are disposed upon a first major surface of the plate according to a technique selected from the group consisting of permanently bonding said transducer and said sensor to the first major surface of the plate, embedding said transducer and said sensor in the plate and placing said transducer and said sensor on the first major surface of the plate.

20. The apparatus of claim 14, wherein said transducer and said sensor are disposed upon a portion of an aircraft that includes the composite laminate plane.