NASM 1312-5-1997 紧固件试验方法5 应力耐久性.pdf

1、NASM 1312-5-1997 紧固件试验方法5 应力耐久性_STD-AIA/NAS NASM3332-5-ENGL L997 M 0338743 0505427 4T5 NASM1312-5 29 August 1997 ADOPTION NOTICE NASM13 12-5, “Fastener Test Methods Method 5 Stress Durability” was adopted on 29 August 1997 for use by the Department of Defense OD). Proposed changes by DoD activities

2、must be submitted to the DoD Adopting Activity: Commander, Naval Air Warfare Center Aircraft Division, Code 4141OOB120-3 Highway 547, Lakehurst, NJ 08733-5100. DoD activities may obtain copies of this standard fiom the Standardization Document Order Desk, 700 Robbins Avenue, Building 4D, Philadelphi

3、a, PA 191 1 1-5094. The private sector and other Government agencies may purchase copies from the Aerospace Industries Association, 1250 Eye Street W, Washington, DC 20005. NASM1312-5 Should be used instead of MIL-STD-1312-54 which was cancelled on 29 August 1997. Custodians: Navy - AS Air Force - 1

4、 1 hy - AV Preparing activity: Navy - AS (Project No. 53GP-0285-05) Review Activities: Navy - AS, SH Air Force - 1 1 Army - AV, AR DLA - IS COPYRIGHT Aerospace Industries Association of America, Inc. (AIA NAS)Licensed by Information Handling ServicesSTD.AIA/NAS NASM1312-5-ENGL L997 M 0318743 0505002

5、 b27 NATIONAL AEROSPACE STANDARD COPYRIGHT 1997 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, MC ALL RIGHTS RESERVED NASM1312-5 STANDARD PRACTICE FASTENER TEST METHODS METHOD 5 STRESS DURABILITY THE INITIAL RELEASE OF TKIS DOCUMENT SUPERSEDES MIL-STD-13 12-5A DESIGNATION FOR THIS TEST METHOD REMAINS

6、MIL-STD-1312-5 FSC 53GP SHEET 1 OF 14 APPROVAL DATE AUGUST 1997 USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY AEROSPACE STANDARD IS ENTIRELY VOLUNTARY AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY CONFORMANCE OF ITEMS PRODUCED UNDER AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1)

7、 THE SUITABILITY OF ITEMS FOR ANY PARTICULAR APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO OF PATENT OR TRADEMARK RIGHTS. COPYRIGHT Aerospace Industries Association of America, Inc. (AIA NAS)Licensed by Information Handling ServicesSTD.AIA/NAS NASMLIL2-5-ENGL L777 m 03387q3 0505003 5b

8、5 NATIONAL AEROSPACE STANDARD COPYRIGHT 1997 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC ALL RIGHTS RESERVED NASM1312-5 FOREWORD This standard sets forth a standard test method for determining the capability of externally threaded fasteners to withstand the various stress load conditions encoun

9、tered when used in military weapons systems. SHEET 2 APPROVAL DATE AUGUST 1997 USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY AEROSPACE STANDARD IS ENTIRELY VOLUNTARY AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY CONFORMANCE OF ITEMS PRODUCED UNDER AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM

10、 RESPECTING (1) THE SUITABILITY OF ITEMS FOR ANY PARTICULAR AIPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO OF PATENT OR TRADEMARK RIGHTS. COPYRIGHT Aerospace Industries Association of America, Inc. (AIA NAS)Licensed by Information Handling ServicesNATIONAL AEROSPACE STANDARD COPYRIGHT

11、1997 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC ALL RIGHTS RESERVED NASM13 12-5 Paragraph 1 . 1.1 2 . 2.1 2.1.1 3 . 4 . 4.1 4.1.1 4.1.2 4.1.3 4.1.4 4.2 5 . 5.1 5.1.1 5.2 5.3 5.4 5.5 5.6 5.7 6 . 6.1 TABLE OF CONTENTS Sheet SCOPE . 4 Applicablllty . 4 . REFERENCED DOCUMENTS . 4 Government docume

12、nts . 4 Specifications. Standards and handbooks . 4 DEFINITIONS . 4 GENERAL REQUIREMENTS . 4 Test apparatus . 4 Elongation method of loading . 5 External loading method . 5 Torque method of loading . 5 Strain gage method of loading . 5 Test specimen sample size . 5 DETAIL REQUIREMENTS . 5 Torque met

13、hod . 5 Elongation method . 6 Strain gage method . 7 Test procedures . 5 External load method-flexure fixture . 7 Alternative loading method . 7 Specimen examlnatlon 7 Test results . 7 . . NOTES . 7 Test report . 7 FIGURES Fipure Sheet 1 . 2 . 3 . 4 . 5 . 6 . Test block . 9 Test spacer . 10 Tapped b

14、lock . 11 Torque and elongation testing assembly . 12 Testing assembly . 13 Flexure type test fixture . 14 SHEET 3 APPROVAL DATE AUGUST 1997 USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY AEROSPACE STANDARD IS ENTIRELY VOLUNTARY AIA DOES NOT QUALIFY SUPPLIERS OR CERTIFY CONFORMANCE OF ITEMS PRODUCED U

15、NDER AEROSPACE STANDARDS . AIA MAKES NO REPRESENTATION OR CWM RESPECTING (1) THE SUITABILITY OF ITEMS FOR ANY PARTICWAR APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO OF PATENT OR TRADEMARK RIGHTS . COPYRIGHT Aerospace Industries Association of America, Inc. (AIA NAS)Licensed by Inform

16、ation Handling ServicesNATIONAL AEROSPACE STANDARD COPYRIGHT 1997 AEROSPACE INDUSTRIES ASSOCIATION OF AMERICA, INC ALL RIOHTS RESERVED NASM13 12-5 1. SCOPE 1.1 Applicabilitv. This method outlines a standard procedure for testing the stress durability of exteridly, threaded fasteners. This procedure

17、applies to all types of externally threaded fasteners which may be subject to any type of embrittlement and is not limited by configuration or size. 2. REFERENCED DOCUMENTS 2.1 Government documents. 2.1.1 Specifications. standards and handbooks. Unless otherwise specified, the following specificatio

18、ns, standards and handbooks of the issue listed in the current Department of Defense Index of Specifications and Standards (DoDISS) and the supplement thereto (if applicable), form a part of this standard to the extent specified herein. SPECIFICATIONS FEDERAL GGG-W-686 Wrench, Torque MILITARY MIL,-T

19、-5544 Thread Compound, Antiseize, Graphite-Petrolatum MIL,-1-6866 Inspection; Penetrant Method of MIL-1-6868 Inspection Process, Magnetic Particle (Copies of specifications, standards, handbooks, drawings and publications required by contractors in connection with specific acquisition fnctions shoul

20、d be obtained from the contracting activity or as directed by the contracting officer.) 3. DEFINITIONS fiat applicable. 4. GENERAL REQUIREMENTS 4.1 Test apparatus. SHEET 4 APPROVAL DATE AUGUST 1997 QUALIFY SUPPLIERS OR CERTIFY CONFORMANCE OF ITEMS PRODUCED UNDER AEROSPACE STANDARDS. AIA MAKES NO REP

21、RESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF ITEMS FOR ANY PARTICULAR APPLICATION OR (2) THE EXISTENCE OF OR APPLICABILITY THERETO OF PATENT OR TRADEMARK RIGHTS. USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY AEROSPACE STANDARD IS ENTIRELY voLwrmY AIA DOES NOT COPYRIGHT Aerospace Industries

22、Association of America, Inc. (AIA NAS)Licensed by Information Handling ServicesNATIONAL AEROSPACE STANDARD COPYRIGHT 1997 AEROSPACE NDUSTRIES ASSOCIATION OF Ah4EItICA INC ALL RIGHTS RESERVED NASMI 3 12-5 4.1.1 Torque method of loading. Torque wrenches calibrated for accuracy within the limits specif

23、ied by GGG-W-686 will be required, as well as the necessary adapters to fit the configuration of the fastener under test. Also required are steel blocks as shown on figure 1, heat treated to a minimum hardness of Rockwell C 45, or steel spacers as shown on figure 2, heat treated to a minimum hardnes

24、s of Rockwell C 45, and an internally threaded member (figures 3 and 4) with sufficient strength to develop full tensile strength of the fastener being tested. 4.1.2 Elongation method of loading. Equipment in accordance with 4.1.1 shall be used, except that any suitable wrenching device may be used

25、and a precision measuring instnlment is required to measure elongation of the test fastener according to acceptable methods. 4.1.3 External loadinp method. Suitable equipment and fixtures, such as those used in tensile testing of fasteners, shall be used to develop and maintain the required test loa

26、d on the fastener. 4.1.4 Strain gage method of loading. A precision calibrated load cell of sufficient capacity to develop full tensile strength of the fastener under test shall be used, and be of proper dimensions to accommodate the fastener. Strain gages shall be fastened by standard approved meth

27、ods to the load cell as indicated on figure 5. Hardened steel washers or plates, as shown on figure 5 of sufficient strength to develop full tensile strength of fastener, shall be required. In addition, an accurate strain indicator is required which, at the option of the tester, may be coupled with

28、a multi-channel switch and balance unit. Also required are a suitable wrenching device for the test fastener, and an internally threaded member as specified in 4.1.1. 4.2 Test specimen sample size. The number of specimens to be tested from each lot shall be as specified in the acquisition document o

29、r product specification. The test specimen shall not be altered other than as specified in 5.2. 5. DETAIL REQUIREMENTS 5.1 Test procedures. Unless otherwise specified, stress durability tests shall be conducted in accordance with one of the following methods listed below. Selection of method to be a

30、n option of the manufacturer. In the event of controversy, the external loading method shall be used as the referee method. 5.1.1 Torque method. Test fastener shall be assembled in the test units, utilizing not more than three spacers in accordance with figure 4. The threads of the fastener, the bea

31、ring surface of the fastener head, and the bearing surface of the nut shall be lubricated with a lubricant conforming to MIL-T-5544. A minimum of two full threads of the test specimen shall extend above the face of the nut or tapped block toward the head of the bolt. The tapped test block or the unt

32、apped block nearest to the nuts shall be held in a vise. The specimen shall be tightened with a torque wrench to a torque equivalent to the required test load. Unless otherwise specified, the induced load shall be 75-80 percent of the minimum ultimate tensile strength specified in the product specif

33、ication. The specimen assembly shall remain in a torqued condition at room temperature for a period of time specified by the procurement document. SHEET 5 APPROVAL DATE AUGUST 1997 USE OF OR RELIANCE UPON THIS DOCUMENT OR ANY AEROSPACE STANDARD IS ENTIRELY VOLUNTARY AIA DOES NOT QUALIFY SUPPLIERS OR

34、 CERTIFY CONFORMANCE OF ITE PRODUCED UNDER AEROSPACE STANDARDS. AIA MAKES NO REPRESENTATION OR CLAIM RESPECTING (1) THE SUITABILITY OF ITEMS FOR ANY PARTICULAR APPLICATION OR (2) THE EXlSTENCE OF OR APPLICABILITY THERETO OF PATENT OR TRADEMARK RIGHTS. COPYRIGHT Aerospace Industries Association of Am

35、erica, Inc. (AIA NAS)Licensed by Information Handling ServicesNATIONAL AEROSPACE STANDARD COPYRIGHT 1997 AEROSPACE MDUSTRlES ASSOCIATION OF AMERICA, INC ALL RIGHTS RESERVED NASM13 12-5 5.1.1.1 The torque value may be determined from the following equation or torque tension curves developed from test

36、s utilizing hardened steel threaded members: T=KDL where T = torque in inch-pounds K = O. I (fiction factor) D = nominal diameter of specimen (inches) L = induced load (pounds) 5.2 Elongation method. The test fastener shall be assembled in the test units, utilizing not more than three blocks in acco

37、rdance with figure 4. The threads of the fastener, the bearing surface of the fastener head, and the bearing surface of the nut shall be lubricated with a lubricant conforming to MIL-T-5544. A minimum of two full threads of the test specimen shall extend above the face of the nut or tapped block tow

38、ard the head of the bolt. The tapped test block or the untapped block nearest the nut shall be held in a vise. The specimen shall be tightened with any suitable wrenching device until the predetermined elongation of the specimen has been reached by actual measurement with a precision measuring devic

39、e, usually a micrometer, over the ends of the specimen. The assembly shall be allowed to stand at room temperature for the period of time specified by the procurement document. The predetermined amount of elongation shall be obtained from a load versus elongation curve developed from data obtained utilizing a standard tensile testing machine, comparable fixtures, and fasteners from the lot being ev