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ASTM E2582-07

(Practice)

Standard Practice for Infrared Flash Thermography of Composite Panels and Repair Patches Used in Aerospace Applications

Standard Practice for Infrared Flash Thermography of Composite Panels and Repair Patches Used in Aerospace Applications

SIGNIFICANCE AND USE
FT is typically used to identify flaws that occur in the manufacture of composite structures, or to track flaw development during service. Flaws detected with FT include delamination, disbonds, voids, inclusions, foreign object debris, porosity or the presence of water that is in contact with the back surface. With dedicated signal processing and the use of representative test samples, characterization of flaw depth and size, or measurement of component thickness and thermal diffusivity may be performed.
Since FT is based on the diffusion of thermal energy from the inspection surface of the specimen to the opposing surface (or the depth plane of interest), the practice requires that data acquisition allows sufficient time for this process to occur, and that at the completion of the acquisition process, the radiated surface temperature signal collected by the IR camera is strong enough to be distinguished from spurious IR contributions from background sources or system noise.
This method is based on accurate detection of changes in the emitted IR energy emanating from the inspection surface during the cooling process. As the emissivity of the inspection surface deviates from ideal blackbody behavior (emissivity = 1), the signal detected by the IR camera may include components that are reflected from the inspection surface. Most composite materials can be examined without special surface preparation. However, it may be necessary to coat low-emissivity, optically translucent inspection surfaces with an optically opaque, high-emissivity water-washable paint.
This practice applies to the detection of flaws with aspect ratio greater than one.
This practice is based on the thermal response of a specimen to a light pulse that is uniformly distributed over the plane of the inspection surface. To ensure that 1- dimensional heat flow from the surface into the sample is the primary cooling mechanism during the data acquisition period, the height and width dimensions of ...
SCOPE
1.1 This practice describes a procedure for detecting subsurface flaws in composite panels and repair patches using Flash Thermography (FT), in which an infrared (IR) camera is used to detect anomalous cooling behavior of a sample surface after it has been heated with a spatially uniform light pulse from a flash lamp array.
1.2 This practice describes established FT test methods that are currently used by industry, and have demonstrated utility in quality assurance of composite structures during post-manufacturing and in-service examinations.
1.3 This practice has utility for testing of polymer composite panels and repair patches containing, but not limited to, bismaleimide, epoxy, phenolic, poly(amide imide), polybenzimidazole, polyester (thermosetting and thermoplastic), poly(ether ether ketone), poly(ether imide), polyimide (thermosetting and thermoplastic), poly(phenylene sulfide), or polysulfone matrices; and alumina, aramid, boron, carbon, glass, quartz, or silicon carbide fibers. Typical as-fabricated geometries include uniaxial, cross ply and angle ply laminates; as well as honeycomb core sandwich core materials.
1.4 This practice has utility for testing of ceramic matrix composite panels containing, but not limited to, silicon carbide, silicon nitride and carbon matrix and fibers.
1.5 This practice applies to polymer or ceramic matrix composite structures with inspection surfaces that are sufficiently optically opaque to absorb incident light, and that have sufficient emissivity to allow monitoring of the surface temperature with an IR camera. Excessively thick samples, or samples with low thermal diffusivities, require long acquisition periods and yield weak signals approaching background and noise levels, and may be impractical for this technique.
1.6 This practice applies to detection of flaws in a composite panel or repair patch, or at the bonded interface between the panel and a supporting sandwich cor...

General Information

Status
Historical
Publication Date
30-Jun-2007
ICS
49.035 - Components for aerospace construction
Technical Committee
E07 - Nondestructive Testing
Drafting Committee
E07.10 - Specialized NDT Methods
Current Stage
Ref Project

Relations

Replaced By
ASTM E2582-07(2014) - Standard Practice for Infrared Flash Thermography of Composite Panels and Repair Patches Used in Aerospace Applications
Effective Date
01-Oct-2014
Referred By
ASTM E3353-22 - Standard Guide for In-Process Monitoring Using Optical and Thermal Methods for Laser Powder Bed Fusion
Effective Date
01-Jul-2007
Referred By
ASTM E2533-21 - Standard Guide for Nondestructive Examination of Polymer Matrix Composites Used in Aerospace Applications
Effective Date
01-Jul-2007
Referred By
ASTM E2981-21 - Standard Guide for Nondestructive Examination of Composite Overwraps in Filament Wound Pressure Vessels Used in Aerospace Applications
Effective Date
01-Jul-2007

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ASTM E2582-07 - Standard Practice for Infrared Flash Thermography of Composite Panels and Repair Patches Used in Aerospace ApplicationsASTM E2582-07 - Standard Practice for Infrared Flash Thermography of Composite Panels and Repair Patches Used in Aerospace Applications
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ASTM E2582-07 - Standard Practice for Infrared Flash Thermography of Composite Panels and Repair Patches Used in Aerospace Applications
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Standards Content (Sample)

NOTICE: This standard has either been superseded and replaced by a new version or withdrawn.
Contact ASTM International (www.astm.org) for the latest information
Designation: E2582 − 07
StandardPractice for
Infrared Flash Thermography of Composite Panels and
1
Repair Patches Used in Aerospace Applications
This standard is issued under the fixed designation E2582; the number immediately following the designation indicates the year of
original adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the year of last reapproval. A
superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
This standard has been approved for use by agencies of the U.S. Department of Defense.
1. Scope panel and a supporting sandwich core or solid substrate. It does
not apply to discontinuities in the sandwich core, or at the
1.1 This practice describes a procedure for detecting sub-
interface between the sandwich core and a second panel on the
surface flaws in composite panels and repair patches using
far side of the core (with respect to the inspection apparatus).
Flash Thermography (FT), in which an infrared (IR) camera is
used to detect anomalous cooling behavior of a sample surface 1.7 This practice does not specify accept-reject criteria and
after it has been heated with a spatially uniform light pulse is not intended to be used as a basis for approving composite
from a flash lamp array. structures for service.
1.8 This standard does not purport to address all of the
1.2 This practice describes established FT test methods that
safety concerns, if any, associated with its use. It is the
are currently used by industry, and have demonstrated utility in
responsibility of the user of this standard to establish appro-
quality assurance of composite structures during post-
priate safety and health practices and determine the applica-
manufacturing and in-service examinations.
bility of regulatory limitations prior to use.
1.3 This practice has utility for testing of polymer compos-
ite panels and repair patches containing, but not limited to,
2. Referenced Documents
bismaleimide, epoxy, phenolic, poly(amide imide),
2
2.1 ASTM Standards:
polybenzimidazole, polyester (thermosetting and
D3878 Terminology for Composite Materials
thermoplastic), poly(ether ether ketone), poly(ether imide),
E1316 Terminology for Nondestructive Examinations
polyimide (thermosetting and thermoplastic), poly(phenylene
sulfide), or polysulfone matrices; and alumina, aramid, boron,
3. Terminology
carbon, glass, quartz, or silicon carbide fibers. Typical as-
fabricated geometries include uniaxial, cross ply and angle ply
3.1 Definitions—Terminology in accordance with Termi-
laminates; as well as honeycomb core sandwich core materials.
nologies D3878 and E1316 and shall be used where applicable.
1.4 This practice has utility for testing of ceramic matrix
3.2 Definitions of Terms Specific to This Standard:
compositepanelscontaining,butnotlimitedto,siliconcarbide,
3.2.1 aspect ratio—the diameter to depth ratio of a flaw. For
silicon nitride and carbon matrix and fibers.
irregularlyshapedflaws,diameterreferstotheminoraxisofan
equivalent rectangle that approximates the flaw shape and area.
1.5 This practice applies to polymer or ceramic matrix
composite structures with inspection surfaces that are suffi- 3.2.2 discrete discontinuity—a thermal discontinuity whose
ciently optically opaque to absorb incident light, and that have projection onto the inspection surface is smaller than the field
sufficient emissivity to allow monitoring of the surface tem- of view of the inspection apparatus.
perature with an IR camera. Excessively thick samples, or
3.2.3 extended discontinuity—a thermal discontinuity
samples with low thermal diffusivities, require long acquisition
whose projection onto the inspection surface completely fills
periods and yield weak signals approaching background and
the field of view of the inspection apparatus.
noise levels, and may be impractical for this technique.
3.2.4 first logarithmic derivative—the rate of change of the
1.6 Thispracticeappliestodetectionofflawsinacomposite
natural logarithm of temperature (with preflash temperature
panel or repair patch, or at the bonded interface between the
subtracted) with respect to the natural logarithm of time.
1
This practice is under the jurisdiction of ASTM Committee E07 on Nonde-
2
structive Testing and is the direct responsibility of Subcommittee E07.10 on For referenced ASTM standards, visit the ASTM website, www.astm.org, or
Specialized NDT Methods. contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
Current edition approved July 1, 2007. Published July 2007. DOI: 10.1520/ Standards volume information, refer to the standard’s Document Summary page on
E2582-07. the ASTM website.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1

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Standard Practice for Infrared Flash Thermography of Composite Panels and Repair Patches Used in Aerospace Applications

SIGNIFICANCE AND USE
5.1 Typically, FT is used to identify flaws that occur in the manufacture of composite structures, or to identify and track flaws that develop during the service lifetime of the structure. Flaws detected with FT include delamination, disbonds, voids, inclusions, foreign object debris, porosity, or the presence of fluid that is in contact with the backside of the inspection surface. For example, the effect of variable ply number (or thickness), bridging, and an insert simulating delamination on heat flow into a composite is shown in Fig. 1 (left). Bridging (Fig. 1, right) or delaminated areas show up as hot spots due to discontinuous heat flow, causing heating to be localized close to the inspection surface. With dedicated signal processing and the use of representative test samples, characterization of flaw depth and size, or measurement of component thickness and thermal diffusivity, may be performed.
FIG. 1 Variation of Heat Flow Into a Composite With Variable Ply Thickness (Scenarios 1, 3, and 4), Bridging (Scenario 2) And an Insert (Scenario 5) (Left), And a Post Layup Line Scan Showing Bright Spots Attributed to Bridging (Right) (Courtesy of NASA Langley Research Center)  
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1.1 This practice describes a procedure for detecting subsurface flaws in composite panels and repair patches using Flash Thermography (FT), in which an infrared (IR) camera is used to detect anomalous cooling behavior of a sample surface after it has been heated with a spatially uniform light pulse from a flash lamp array.  
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FIG. 1 Test Procedure A, Pulse Echo Apparatus Set-up  
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FIG. 2 Test Procedure B, Through Transmission Apparatus Set-up  
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1.3 This practice is intended to be used to establish a metric for AM parts in downstream documents.  
1.4 This practice is not intended to establish criteria for any downstream processes, but rather to establish a metric that these processes can use.  
1.5 The part classification metric could be utilized by the engineering, procurement, non-destructive inspection, testing, qualification, or certification processes used for AM aviation parts.  
1.6 The classification scheme in this practice establishes a consistent methodology to define and communicate the consequence of failure associated with AM aviation parts.  
1.7 This practice is not intended to supersede the requirements and definitions of the applicable regulations or policies, including but not limited to the ones listed in Annex A1.  
1.8 Tables A1.1-A1.3 align the existing regulations and guidance with the four part classes established herein. However, this alignment should not be construed as an alignment of the existing regulations to each other.  
1.9 The material or process, or both, in general does not affect the consequence of failure of a part, therefore the classification scheme defined in this document may be used outside AM.  
1.10 The user of this standard should not assume regulators’ endorsement of this standard as accepted mean of compliance.  
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Standard Test Method for Measuring Optical Angular Deviation of Transparent Parts

SIGNIFICANCE AND USE
5.1 One of the measures of optical quality of a transparent part is its angular deviation. It is possible that excessive angular deviation, or variations in angular deviation throughout the part, will result in visible distortion of scenes viewed through the part. Angular deviation, its detection, and quantification are of extreme importance in the area of certain aircraft transparency applications, that is, aircraft equipped with Heads-up Displays (HUD). It is possible that HUDs will require stringent control over the optics of the portion of the transparency (windscreen or canopy) which lies between the HUD combining glass and the external environment. Military aircraft equipped with HUDs or similar devices require precise knowledge of the effects of the windscreen or canopy on image position in order to maintain weapons aiming accuracy.  
5.2 Two optical parameters have the effect of changing image position. The first, lateral displacement, is inherent in any transparency which is tilted with respect to the line of sight. The effect of lateral displacement is constant over distance, and seldom exceeds a fraction of an inch. The second parameter, angular deviation, is usually caused by a wedginess or nonparallelism of the transparency surfaces. The effect of angular deviation is related to the tangent of the angle of deviation, thus the magnitude of the image position displacement increases as does the distance between image and transparency. The quantification of angular deviation is then the more critical of the two parameters. Both parameters are illustrated in Fig. X1.1.
SCOPE
1.1 This test method covers measuring the angular deviation of a light ray imposed by transparent parts such as aircraft windscreens and canopies. The results are uncontaminated by the effects of lateral displacement, and it is possible to perform the procedure in a relatively short optical path length. This is not intended as a referee standard. It is one convenient method for measuring angular deviations through transparent windows.  
1.2 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.  
1.3 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.

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ASTM
ASTM E2582-21(Practice)
Standard Practice for Infrared Flash Thermography of Composite Panels and Repair Patches Used in Aerospace Applications

SIGNIFICANCE AND USE
5.1 Typically, FT is used to identify flaws that occur in the manufacture of composite structures, or to identify and track flaws that develop during the service lifetime of the structure. Flaws detected with FT include delamination, disbonds, voids, inclusions, foreign object debris, porosity, or the presence of fluid that is in contact with the backside of the inspection surface. For example, the effect of variable ply number (or thickness), bridging, and an insert simulating delamination on heat flow into a composite is shown in Fig. 1 (left). Bridging (Fig. 1, right) or delaminated areas show up as hot spots due to discontinuous heat flow, causing heating to be localized close to the inspection surface. With dedicated signal processing and the use of representative test samples, characterization of flaw depth and size, or measurement of component thickness and thermal diffusivity, may be performed.
FIG. 1 Variation of Heat Flow Into a Composite With Variable Ply Thickness (Scenarios 1, 3, and 4), Bridging (Scenario 2) And an Insert (Scenario 5) (Left), And a Post Layup Line Scan Showing Bright Spots Attributed to Bridging (Right) (Courtesy of NASA Langley Research Center)  
5.2 Since FT is based on the diffusion of thermal energy from the inspection surface of the specimen to the opposing surface (or the depth plane of interest), the practice requires that data acquisition allows sufficient time for this process to occur, and that at the completion of the acquisition process, the radiated surface temperature signal collected by the IR camera is strong enough to be distinguished from spurious IR contributions from background sources or system noise.  
5.3 This method is based on accurate detection of changes in the emitted IR energy emanating from the inspection surface during the cooling process. As the emissivity of the inspection surface falls below that of an ideal blackbody (blackbody emissivity = 1), the signal detected by the IR camera may include comp...
SCOPE
1.1 This practice describes a procedure for detecting subsurface flaws in composite panels and repair patches using Flash Thermography (FT), in which an infrared (IR) camera is used to detect anomalous cooling behavior of a sample surface after it has been heated with a spatially uniform light pulse from a flash lamp array.  
1.2 This practice describes established FT test methods that are currently used by industry, and have demonstrated utility in quality assurance of composite structures during post-manufacturing and in-service examinations.  
1.3 This practice has utility for testing of polymer composite panels and repair patches containing, but not limited to, bismaleimide, epoxy, phenolic, poly(amide imide), polybenzimidazole, polyester (thermosetting and thermoplastic), poly(ether ether ketone), poly(ether imide), polyimide (thermosetting and thermoplastic), poly(phenylene sulfide), or polysulfone matrices; and alumina, aramid, boron, carbon, glass, quartz, or silicon carbide fibers. Typical as-fabricated geometries include uniaxial, cross ply, and angle ply laminates; as well as honeycomb core sandwich core materials.  
1.4 This practice has utility for testing of ceramic matrix composite panels containing, but not limited to, silicon carbide, silicon nitride, and carbon matrix and fibers.  
1.5 This practice applies to polymer or ceramic matrix composite structures with inspection surfaces that are sufficiently optically opaque to absorb incident light, and that have sufficient emissivity to allow monitoring of the surface temperature with an IR camera. Excessively thick samples, or samples with low thermal diffusivities, require long acquisition periods and yield weak signals approaching background and noise levels, and may be impractical for this technique.  
1.6 This practice applies to detection of flaws in a composite panel or repair patch, or at the bonded interface between the panel and a supporting ...

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ASTM
ASTM F3498-21(Practice)
Standard Practice for Developing Simplified Fatigue Load Spectra

SIGNIFICANCE AND USE
4.1 This standard practice provides one means for determining fatigue load spectra for aeroplane durability assessments. This information can be used in conjunction with Specification F3115/F3115M, Section 5, Load Considerations.  
4.1.1 Users of this practice may propose alternate spectra, subject to the approval of their CAA.  
4.2 The methods are applicable to the durability evaluation of wings of small aeroplanes. Additional calculation (such as methods noted in ACE-100-01) are needed to properly develop load spectra for fatigue evaluation of empennage and/or configurations with canards (or forward wings) and/or winglets (or tip fins), fuselage, and potentially other components, with approval from appropriate regulatory agency.  
4.3 Much of the material presented herein is directly taken from AC 23-13A. The FAA developed the flight load spectra, presented herein, based on a statistical analysis of the data presented in DOT/FAA/CT-91/20. The ground load spectra are directly from AFS-120-73-2.  
4.4 The flight load spectra, presented in Section 7, includes an adjustment (1.5 standard deviations) to the average measured load frequency. The adjustment accounts for the variability in the loading spectra experienced by individual aeroplanes, as well as across aeroplane types. The magnitude of the adjustment was selected to maintain the probability that a component will reach its safe-life without a detectable fatigue crack established by scatter factor (see paragraph 2–15 of AC 23-13A).
SCOPE
1.1 This practice provides data to develop simplified loading spectra that can be used to perform structural durability analysis for aeroplanes, specifically for wings of small aeroplanes. The material was developed through open consensus of international experts in general aviation. The information was created by focusing on Level 1, 2, 3, and 4 Normal Category aeroplanes. The content may be more broadly applicable; it is the responsibility of the applicant to substantiate broader applicability as a specific means of compliance.  
1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable civil aviation authorities, or CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to the ASTM Committee F44 web page (www.astm.org/COMMITTEE/F44.htm).  
1.3 The values stated in inch-pound units are to be regarded as standard. No other units of measurement are included in this standard.  
1.4 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.  
1.5 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.

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