ARMY MIL-C-63422 A (2)-1983 CORE FOR PROJECTILE 105MM APFSDS-T M833《M833型105MM APFSDS-T核心弹丸》.pdf

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1、MIL-C-63422A (AR) . AMENDMENT 2 8 July 1983 SUPERSEDING AMENDMENT 1 10 December 1982 MILITARY SPECIFICATION CORE, FOR PROJECTILE, 105MM, APFSDS-T, M833 This Amendment forms a part of Military Specification MIL-P-63422A(AR), dated 28 May 1982, and is approved for use by the U.S. Army Armament Researc

2、h and Development Command, and is available for use by all Departments and Agencies of the Department of Defense. PAGE 3 3.3: Delete paragraph 3.3 in its entirety and substitute the following: “3.3 (U) Traceability. Core traceability must be main- tained throughout the production cycle. This traceab

3、ility shall include identification of derby material, lot or batch of titanium, casting or melt, ingot (not required when con- tracting officer authorizes implementation of paragraph 3.4.1) bars, cores, solutionizing cycle, and aging cycle. The melt identification number and corresponding aging cycl

4、e (consecutive aging cycle run numbers shall be assigned) through which each melt was processed shall be annotated on the ammunition data card of the applicable shipment lot. mented and include as a minimum, the date, reason for rejection, and applicable identification numbers.“ Rejection of any mat

5、erial during production must be docu- 3.7: Delete paragraph 3.7 in its entirety and substitute the follow i ng : “3.7 (U) Ammunition data cards. As a minimum, block 23 ofthe ammunition data card must contain comrilete information as to the melt lots and associated aging cyles which are contained wit

6、hin each shipment lot.“ 1 of 13 FSC 1315 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NIL-C-63q22A (2) 13 m 7977706 0350325 T m MIL-C-634 22A (AR) AMENDMENT 2 PAGE 5 Add paragraph 3.11 as follows: “3.11 (U) Process control document. This document

7、shall include descriptions of all production processes, procedures and equipment -(including in-process inspection equipment) used to manufacture and inspect the production material. The descriptions shall identify, as a minimum, the complete sequence of operations and schematic line layouts, basic

8、fabrication processes (i.e.! casting, forging, extrusion, machining, etc.), fabrication equipment (i.e., type, model no., dies associated with fabrication processes (i.e., times, temperatures, feeds, speeds, pressures, etc:), associated processes (i.e., heat treatment, stress relieving, plating, etc

9、.), controls on these associated processes (i.e., equipment descriptions, times, temperatures, etc.) in-process inspections, gages and setups utilized and applicable in-process inspection procedures. Process control documents shall be submitted in accordance with DI-P-1604 (see 6.5.1). All initial a

10、nd revised process control documents shall be submitted to DRDAR-QAT-A for review and disposition (see 6.5) .I jigs, fixtures, etc.), controls PAGE 8 4.4.1.1: Delete paragraph 4.4.1.1 in its entirety and substitute the following: “4.4.1.1 (U) Core lots. All core lots shall comply with the lot format

11、ion provisions of MIL-A-48078. In addition, all core lots shall be composed only of heat treatment batches which have been found acceptable when tested in accordance with 4.4.2. A time frame of three months from aging shall not be exceeded for a heat treatment batch to be included in a core lot. Fur

12、thermore, cores from a particular melt lot shall not be included in more than three core lots. Cores not falling into these categories shall be formed into a hybrid lot. Disposition on the inspection and testing required to be performed on the hybrid lot shall be provided by the contract- ing office

13、r.“ 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-C-63422A (2) 33 m 777770b 0350326 3 m MIL-C- 63 4 2 2A (AR) AMENDMENT 2 PAGE 11 4.4.2.3: Add Major Defect 115 as follows: “115 Distance from rear of core to starting surface, 0.40%, 3.2, Gage“

14、. PAGE 12 4.4.2.3: Add Minor Defect 212 as follows: “212 Aft thread pitch diameter, max, 0.65%, 3.2, Gage.“ * Add Minor Defect 213 as follows: “213 Rear nib diameter and length, max. 0.65%, 3.1, Gage.“ PAGE 14 4.5.5: Delete: “Figure 2“ in first sentence and substitute “Figure 3“. PAGE 17 Add paragra

15、phs 4.5.7.3.1, 4.5.7.3.2, and 4.5.7.3.3 as follows: “4.5.7.3.1 (U) Set up and calibration. Level II. 4.5.7.3.2 (U) Operator. Level I. 4.5.7.3.3 (U) Certification procedures. The contractor shall prepare and submit for approval, in accordance with data item description number DI-S-3628 and the DD For

16、m 1423, the detailed procedures for qualification and certification of personnel performing the nondestructive testing procedures r equ i r ed her e in . I PAGE 18 Add paragraphs 4.5.8.1.1, 4.5.8.1.2 and 4.5.8.1.3 as follows: “4.5.8.1.1 (U) Set up and calibration. Level II. 4.5.8.1.2 (U) Operator. L

17、evel I. 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-HIL-C-63LI22A (2) 13 I 7977706 0350127 3 W MIL-C-63422A (AR) AMENDMENT 2 4.5.8.1.3 (U) Certification procedures. The contractor shall prepare and submit for approval, in accordance with data i

18、tem description number DI-S-3628 and the DD Form 1423, the detailed procedures for qualification and certification of personnel performing the nondestructive testing procedures required herein.“ 4.5.9: Delete “Figure 3“ and substitute “Figure 2“. 4.5.10: Delete “Figure 3“ and substitute “Figure 2“.

19、PAGE 22 6.5.1: Add the following: “3 . 11 Manufacturing Methods Report (Modified) DI-P-1604 4.5.7.3.3 Nondestructive Inspection Plan DI-S-36 28 4.5.8 . 1.3 Nondestructive I nspec t ion Plan DI-S-3628“. PAGE 24 APPENDIX: Delete APPENDIX and substitute revised APPENDIX as PAGE 31 attached. FIGURE 1: C

20、hange specimen size from 111/2 inch“ to “1 inch“ for both specimens F and G. PAGE 34 FIGURE 4: Delete in its entirety. Add new page 36, Figure A.1, as attached. Add new page 37, Figure A.2, as attached. Custodian: A rmy-AR Preparing activity: Army-AR (Project 1315-A553) 4 Provided by IHSNot for Resa

21、leNo reproduction or networking permitted without license from IHS-,-,-_ _._ MIL-C-b3q22A (2) 13 W 7777706 035012 5 i MIL-C-634 22A (AR) APPENDIX APPENDIX TEST METHOD FOR SLOW BEND PRECRACKED CHARPY TEST 10. SCOPE 10.1 Scope. This appendix covers the test method for determining fracture toughness us

22、ing a Charpy specimen containing a fatigue crack and tested by slow bending. 20. APPLICABLE DOCUMENTS 20.1 ASTM Standards E-4 Verification of Testing Machines E-139 Recommended Practice for Conducting Creep, Creep-Rupture and Stress Rupture Tests of Metallic Materials E-399 Plane Strain Fracture Tou

23、ghness of Metallic Materials 30. SUbiiARY OF FTHOD 30.1 The methoz involves three point ben2 testing of notched ant2 fatigue-cracked specimens using fixtures which minimize the load-deformation characteristics of the test are recorded and the fracture tcughness is determined from these characteristi

24、cs and the original dimensions of the specimen. LA contribution of friction fcrces to the measured applied load. The 40. NOTES 40.1 When preparing specimens and testing, it is important that certain precautions be kept in mind. 40.1.1 Crack strenqth. The crack strength of some materials will be sens

25、itive to the rate of loading and loaing rates should be cocfinea to the range given in 80.3.2. 40.1.2 Temperature. The crack strength will be influenced by the testing temperature and calibration relations may change with testing temperature. 24 5 Provided by IHSNot for ResaleNo reproduction or netw

26、orking permitted without license from IHS-,-,- -_ MIL-C-b3q22A (2) 13 m 7977706 0350127 7 I , MIL-C- 634 22A (AR) APPEND1 X 50. DEFINITIONS 50.1 a - fatigue crack depth, Inches (In) B - specimen thickness (In) W - specimen depth (In) M - Bending Moment, Inches-Pound Force (In - lb) f (a/N) - Power s

27、eries cf ratio (a/w) from ASTM-E-399 S - Span between support rcllers; (In.) P max - Maximum Load Applied, (lb) P5 - The load determined by the intersection of the load displacement trace and the secant with a slope of 0.95 of the tangent to the initial linear portion of the load displacement trace.

28、 PQ - The load used to determine KQ (lb). Pp - A specific point at which the first load instability indicating unstable crack growth is recorded (Ibs). K - Stress intensity factor (Ksi Ir!) Kf (max) - Maximum stress intensity factor in fatiguing KQ- Calculated fracture toughness (Ksi In). KIC- Plane

29、 strain fracture toughness (Ksi In). (Ksi In). 60. APPARATUS 60.1 Tension testing machine. Tension Testing Machine conforming to the requirements of ASTk-E-4. 60.2 Bend-test fixture. The procedure involves the testing of the specimen in three point bending. The bend fixture should be so designed as

30、to minimize errors that arise from friction between the specimen and the supports. This can be accomplished by allowing the support rollers to rotate and move apart slightly during loading as described in Fig. A3.2 of ASTM-E-399. The nominal span shall be 1.57 in. If the diameter of the support roll

31、ers is between 0.30 in. to 0.40 in. there will be a negligible change in thespan during deformation of the specimen. 25 6 . - Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-C-63Y22A (2) 13 W 7977706 0350330 3 MIL-C-63422A (AR) APPEND1 X 60.3 Tem

32、perature control. When testing at -50F, an integral temperature conditioning chamber shall be used. Any suitable rriethod may be used to temperature condition the specimen providing the region including the notched and cracked section can be uniformly maintained within + 2OF of the desired test temp

33、erature. The cooling medium chail be free of contaminants, such as chlorie or water, which have an adverse effect on the staballoy. iirhen testing at 7OoF, no chamber is necessary, but the temperature rriust be hele to plus or minus 89 and humidity maintained below 40%RH. 60.4 Temperature measuremen

34、t. The device used to measure the temperature of the medium should be placed adjacent to the test specimens. If an agitated liquid medium is used, the specimens shall be held at the desired temperature, plus or minus 2OF, for at least 30 minutes. Specimens being tested in gas shall be held at the de

35、sired temperature, plus or minus 2OF, for at least 60 minutes. See ASTM-E-139 fcr a discussion of errors on measurements. 60.4.1 Calibration. The temperature measuring apparatus shoul be calibrated periodically against standards traceable to the National Bureau of Standards in order tc ensure that a

36、ccuracy specified above can be achieved. 60.5 Displacement Measurinq Device. An instrument for determination of actual specimen displacement under load shall be utilized. Displacements Gan be measred at the crack mouth as in ASTM-E-399, in the direction of the applied load at a location as close to

37、the mid-span of the specimen as possible. Specimen deflection may be approximated as the testing machine crosshead displacement, if approved by a Government inspection cf the testing machine and fixture. 70. TEST SPECIMENS, DIMENSIONS AND PREPARATION 70.1 Dimensions. The precracked Charpy ben specim

38、en is shown in Fig. A.l. The crack depth, a, (including notch) shall lie within the range between 0.40 to 0.60 W. 70.1.1 Crack starter. The crack starter may consist of a “V“ nctch havins an included anqle between 45Oan6 60Oprovided with a small radiu; at its tip. of less than 0.003 in. and minimum

39、machining surface compression stress is necessary in order to facilitate the initiation pf a fatigue crack at a low stress intensity level. Experience has shown tht a notch radius 26 7 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-r, - MIL-C-63422A

40、 (2) 23 m 9797706 0350131 5 I , MIL-C-63422A (AR) APPEND1 X 70.2 Fatigue crackinq. In order to ensure a sufficiently sharp fatigue crack and to facilitate the production of this crack, the following procedure shall be followed. conducted with the specimen in the condition of heat treatment in which

41、it is to be tested. 70.2.1 Specimen condition. The fatigue cracking shall be 70.2.2 Cracking method. The method used for fatigue cracking shall be such that the crack extension direction is perpendicular to the notched face of the specimen. Cantilever bending or three point bending may be used to pr

42、oduce fatigue cracks. Cantilever bending facilitates completely reversed loading which aids in starting and propagating the crack. Fcr practical purposes, the K calibration for three point bending may be used to estimate the stress intensity factor. The expression given in ASTN-E-399 for the K calib

43、ration in three point bending may be rewritten in terms of the bending moment M as foll.ows an2.used to compute the stress intensity in cantilever bending: K = (4M/BW3j2) f (a/w) where the values of the function f(a/W) are given in tabular form in ASTM-E-399. can be influenced by excessive clamping

44、forces to the extent that the fatigue crack will deviate from a plane normal to the notched face of the specimen. An alternate procedure to aid initiating a fatigue crack by 3 point bending shall be to apply one cycle reverse stress using 4 point bend loading prior to the regular 3 point cycling. al

45、lowable stress intensity in reverse one cycle loading shall be equal to or less than KQ. 70.2.3 Crackinq. During the last 0.020 in. of fatigue cracking, the maximum intensity of the fatigue cycle, Kf(max) shall not exceed 0.6 KQ. requirements the Kf shall be calculated using the low temperature KG l

46、ess than 0.9 Kf (max) . The stress distribution at the crack tip in cantilever bending The For low temperature toughness test The stress intensity amplitude during fatigue should not be 80. TEST PROCEDUm 80.1 Number of tests. Samples shall be selected as specified in the Technical Data Package. I 27

47、 8 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-C-634 22A (AR) APPEND1 X 80.2 Specimen measurement. All specimen dimensions shall be within the tolerances shown in Fig. A.l. 80.2.1. Measure the thickness (B) to the nearest 0.001 in. at not les

48、s than two positions, one on each side of the crack starter notch ard record the average value. 80.2.2 After fracture measure the initial fatigue crack depth (a) to the nearest .O01 inch at the following three positions: at the center of the crack front and midway between the center and the intersec

49、tion of the crack front with the specimen surfaces. Use the average of these three measurements as the crack depth in the calculation of KQ(see 90.1). the crack length measurements exceeds 10 percent of the average, or if part of the crack front is closer to the machined notch root than 10 percent of the average, the specimen should be discarded. Also, if the length of either surface trace of t