ASTM B645-98

Standard Practice for Plane-Strain Fracture Toughness Testing of Aluminum Alloys

SCOPE
1.1 This practice is applicable to the fracture toughness testing of all aluminum alloys, tempers, and products especially in cases where the tests are being made to establish whether or not individual lots meet the requirements of specifications and should be released to customers.  
1.2 Test Method E399 is the basic standard test method for plane-strain fracture toughness testing of aluminum alloys. This practice augments Test Method E399 in three main areas:  
1.2.1 Specimen size selection,  
1.2.2 Fatigue cracking requirements, and  
1.2.3 Interpretation of results of invalid tests.  
1.2.4 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 and health practices and determine the applicability of regulatory limitations prior to use.

General Information

• Status: Historical
• Publication Date: 09-Nov-1998
• ICS: 77.120.10 - Aluminium and aluminium alloys
• Technical Committee: B07 - Light Metals and Alloys
• Drafting Committee: B07.05 - Testing

Relations

• Replaced By: ASTM B645-02 - Standard Practice for Plane-Strain Fracture Toughness Testing of Aluminum Alloys
• Effective Date: 10-Apr-2002

Standards Content (Sample)

Designation: B 645 – 98
AMERICAN SOCIETY FOR TESTING AND MATERIALS
100 Barr Harbor Dr., West Conshohocken, PA 19428
Reprinted from the Annual Book of ASTM Standards. Copyright ASTM
Standard Practice for
Plane–Strain Fracture Toughness Testing of Aluminum
1
Alloys
This standard is issued under the fixed designation B 645; 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 (e) indicates an editorial change since the last revision or reapproval.
INTRODUCTION
Plane-strain fracture toughness testing of aluminum alloys is performed essentially in accordance
with Test Method E 399. However, there is a need, in the application of Test Method E 399 for quality
assurance testing, to deal with the interpretation of the results for material qualification and release in
cases where all requirements for valid measurements of plane-strain fracture toughness cannot be met.
It is the purpose of this practice to provide consistent methods of dealing with those situations.
1. Scope E 399 Test Method for Plane-Strain Fracture Toughness of
3
Metallic Materials
1.1 This practice is applicable to the fracture toughness
E 1823 Terminology Relating to Fatigue and Fracture Test-
testing of all aluminum alloys, tempers, and products, espe-
3
ing
cially in cases where the tests are being made to establish
whether or not individual lots meet the requirements of
3. Terminology
specifications and should be released to customers.
3.1 General—Terms, definitions, symbols, and orientation
1.2 Test Method E 399 is the basic standard test method to
designations in Test Method E 399 and Terminology E 1823
be used for plane-strain fracture toughness testing of aluminum
are applicable herein.
alloys. The purpose of this practice is to provide supplementary
3.2 The following additional definitions are applicable:
information for plane-strain fracture toughness of aluminum
3.2.1 invalid plane-strain fracture toughness—test result,
alloys in three main areas:
Kq, that does not meet one or more of the validity requirements
1.2.1 Specimen sampling,
in Test Method E 399 and, where so characterized, is of no
1.2.2 Specimen size selection, and
value in judging the true plain-strain fracture toughness of a
1.2.3 Interpretation of invalid test results.
material but may, under certain conditions, adequately guaran-
1.3 The values stated in inch-pound units are to be regarded
tee the material’s fracture toughness for lot release purposes.
as the standard. The values given in parentheses are provided
3.2.2 meaningful plane-strain fracture toughness—test re-
for information only.
sult, designated Kq, that does not meet one or more of the
1.4 This standard does not purport to address all of the
validity requirements in Test Method E 399, but for which
safety concerns, if any, associated with its use. It is the
there is experimental or analytical evidence that the departure
responsibility of the user of this standard to establish appro-
from validity is small enough that the value of Kq is expected
priate safety and health practices and determine the applica-
to be within 5 or 10 % of the value of K that would have been
Ic
bility of regulatory limitations prior to use.
obtained had all the validity criteria been met.
2. Referenced Documents 3.2.3 valid plane-strain, fracture toughness—test result
meeting all the validity requirements in Test Method E 399,
2.1 ASTM Standards:
that is, a value of K .
Ic
B 646 Practice for Fracture Toughness Testing of Alumi-
2
num Alloys
4. Summary of Practice
4.1 This practice supplements Test Method E 399 and Prac-
tice B 646 in three main areas:
4.1.1 Specimen sampling,
4.1.2 Specimen size selection, and
1
This practice is under the jurisdiction of ASTM B-7 on Light Metals and Alloys
, and is the direct responsibility of Subcommittee B07.05 on Testing.
Current edition approved Nov. 10, 1998. Published March 1999. Originally
published as B 645–78. Last previous edition B 645–95.
2 3
Annual Book of ASTM Standards, Vol 02.02. Annual Book of ASTM Standards, Vol 03.01.
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B 645
4
NOTE 2—Experimental studies have shown that more uniform values
4.1.3 Interpretation of results which fail the validity require-
of Kq are obtained for high toughness aluminum alloys when B,a $ 5
ments in Test Method E 399 in one of the following areas in
2
(Kq/sys) .
order to determine if the invalid results are acceptable for lot
8.1.2 When it is not possible to obtain a specimen thickness
release:
2
4.1.3.1 Pmax/Pq requirements, B $ 5 (Kq/sys) , it is recommended that the thickness be the
maximum possible considering the basic product dimensions,
4.1.3.2 Specimen size requirements, and
2
4.1.3.3 Fatigue precracking requirements. and that crack length, a, be maintained at $ 5 (Kq/sys) or as
large as possible while still meeting
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