ARMY MIL-P-48349-1974 PROPELLANT M3OA1 FOR USE IN 155MM PROPELLING CHARGES《155毫米发射装药系统用M3OA1发射药》.pdf

《ARMY MIL-P-48349-1974 PROPELLANT M3OA1 FOR USE IN 155MM PROPELLING CHARGES《155毫米发射装药系统用M3OA1发射药》.pdf》由会员分享，可在线阅读，更多相关《ARMY MIL-P-48349-1974 PROPELLANT M3OA1 FOR USE IN 155MM PROPELLING CHARGES《155毫米发射装药系统用M3OA1发射药》.pdf（9页珍藏版）》请在麦多课文档分享上搜索。

1、MILITARY MIL-P-Q8349(PA) 26 August 1974 SPECIFICATION PROPELLANT M30A1 FOR USE IN 155I“i PROPELLING CHARGES This specification is approved for use by all Departments and Agencies of the Department of Defense. 1. SCOPE 1.1 This specification covers M30A1 Propellant for use in Cartridges employed with

2、 the xMi98 Cannon prior to DT/OT II Testing. 2. APPLICABLE DOCUMENTS 2.1 The following documents of the issue in effect on date of invitation for bids, or request for proposal, form a part of this specification to the extent specified herein. SPECIFICATIONS MILITARY MIL-A-2550 - Ammunition and Speci

3、al Weapons; General Specification for STANDARDS MILITARY MIL-STD-109 - Quality Assurance Terms and Definitions MIL-STD-652 - Propellants Solid for Cannons Require- MIL-STD-1168- Lot Numbering of Ammunition MIL-STD-1171- Acceptance and Description Sheets for MIL-STD-414 - Sampling Procedures and Tabl

4、es for ments and Packing Propellants and Explosives Inspection by Variables for Percent Defective FSC: i376 ,/- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-P-48349 13 W 9799906 0319134 T = MIL-P-48349 (PA) 2.2 Other publications. The followin

5、g documents form a part of this specification to the extent specified herein. Unless otherwise indicated, the issue in effect on date of invitation for bids shall apply. CODE OF FEDERAL REGULATIONS Title 49, Department of Transportation: Parts 0-199 AMC PAMPHLET 706-114 Experimental Statistics, Sect

6、ion 5, Tables The Code of Federal Regulations is available from the Superintendent of Documents, Government Printing Office, Washington,D.C., 20402, Orders for the above publication should cite: 49 CFR 0-199 (latest revision). 3. REQUIREMENTS 3.1 Materials. The propellant shall be M3OAl, Type II con

7、forming to the requirements of MIL-STD-652, except para 4.2.3.3.1.2. 3.2 Proving Ground. The propellant, when fired in the mi98 Cannon and with the weight of projectile (96 pounds (lbs) for which it was manufactured, shall comply with the following requirements when tested as specified in 4.3. 3.2.1

8、 Assessment. At 70 degrees Fahrenheit (OF) and standard weapon conditions, the propellant shall be capable of charge assessment to a velocity of 2710 feet per second (fps) without an associated expected pressure greater than 47500 pounds per square inch (psi). for the lot at 7O0F shall not exceed 6.

9、5 fps. at recommended charge weight shall not produce a chamber pressure greater than 58,500 psi at any operating temperature (-50F to S145OF) when fired in a standard weapon. 3.2.2 Uniformity of velocity. The standard deviation in velocity 3.2.3 Permissible Individual Maximum Pressure. The propella

10、nt 2 .+ Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-P- 483 49 (PA ) f. 3.3 Straightness. Twenty seven pounds of stick propellant, cut to the length specified in the contract, shall fit into a 6.1 inch inside diameter cylinder. In addition, ea

11、ch of these individual sticks of propellant shall not bow more than .25 inch. 3.4 Workmanship. The best commercial practices shall be used in the formulation of propellant furnished under this specification, and all other applicable documents. The propellant and its standarc ingredients shall be pro

12、tected from the action of direct sunlight and acid fumes. No reground propellant or nitrocellulose shall be used in the manufacture of propellant procured under this specification unless otherwise specified. 3.5 Physical Properties. The following physical properties shall be determined as specified

13、in 4.3.6 and reported for information (see 6.3): a. Density b. c. Deformation at maximum load. Compressive strength at 77 t 4OF 4. QUALITY ASSURANCE PROVISIONS 4.1 Responsibility for inspection, Unless otherwise specified in the contract or purchase order, the supplier is responsible for the perform

14、ance of all inspection requirements as specified herein, Except as otherwise specified in the contract or order, the supplier may use his own or any other facilities suitable for the performance of the inspection requirements specified herein, unless disapproved by the Government. The Government res

15、erves the right to perform any of the inspections set forth in the specification where such inspections are deemed necessary to assure supplies and services conform to prescribed requirements. Reference shall be made to MIL-STD-109, in order to define terms used herein. The provisions of MIL-A-2550

16、shall apply, 4.1.1 Submission of product. At the time the completed lot of product is submitted to the Government for acceptance, the contractor shall supply the following information accompanied by a certificate which attests that the information provided is correct and applicable to the product be

17、ing submitted: a. A statement that the lot complies wibh all of th.e quality assurance provisions specified within this specification. 3 o Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-P-qB347 L3 9997906 0317136 3 . MIL-P-48349 (PA) b. Number o

18、f batches of product inspected (shall be made available upon request by the contracting officer). c. Results obtained, by defect code, for all inspections peyformed (shall be made available upon request by the contracting officer ) d. Drawing, specification number, and date, together with an identif

19、ication and date of changes. e. Certificates of conformance on all material purchased by the contractor when such material is controlled by Government or commercial specifications referenced in any of the contracting documents (shall be made available upon request by the contracting officer). f. Num

20、ber of items in the lot. g. Date submitted. h. Eight copies of propellant description sheet SMU Form 1047 containing the applicable data (see 6.6) 4.1.2 The certificate shall be signed by a responsible agent The initial certificate submitted of the certifying organization. shall be substantiated by

21、evidence of the agents authority to bind his principal. will not be required with subsequent certificates unless, during the course of the contract, this authority is vested in another agent of the certifying organization. Substantiation of the agents authority 4.2 Inspection provisions 4.2.1 Lot fo

22、rmation. The term “lot“ as used throughout this specification, refers to an inspection lot, which is defined as an essentially homogeneous quantity of propellant from which the sample was drawn and shall not be construed to represent any prior or subsequent quantities presented for inspection. A lot

23、 shall consist of one or more sub-lots or one or more batches of M30A1 propellant produced by one manufacturer, in accordance with the same specification, and same specification revision, under one continuous set of operating conditions, Each lot shall consist of that quantity of M30A1 propellant wh

24、ich has been subjected tothe same unit chemical or physical process intended to make the final product homogeneous. 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- MIL-P-483Y9 33 999990b 0339337 5 MIL-P-48349 (PA) 4.2.2 Testing 4.2.2.1 Materials (

25、see 3.1). Each lot of propellant shall be sampled and tested for composition, form, dimensions and chemical- physical properties in accordance with MIL-STD-652. 4.2.2.2 Proving Ground (see 3.2). Each lot of propellant shall be sampled for proving ground tests in accordance with MIL-STD-652. 4.2.2.2.

26、1 Assessment (see 3.2.1) Informational. The lot shall be referred if the assessed charge weight of propellant has an expected pressure greater than 47,500 psi (see 6.8) If the product of the factor (see 6.4) times the velocity standard deviation of the rounds tested in accordance with 4.3.3 exceeds

27、the applicable requirement the lot shall be referred (see 6.8). 4.2.2.2.3 Individual pressure (see 3.2.3) Informational. If any individual pressure observed during uniformity firings at any operating temperature (-5OOF to 145OF) after correction for difference between as fired and recommended servic

28、e charge weight exceeds 58,500 psi, the lot shall be referred (see 6.8). 4.2.2.3 Straightness (see 3.3). Ten samples each containing 27 pounds of stick propellant, shall be randomly selected from each lot of propellant and tested for straightness. If any of the ten samples, or individual sticks, fai

29、ls the straightness requirement, an additional ten samples shall be selected and tested for straightness. If any of these samples fail the straightness requirement, the lot shall be rejected. 4.2.2.2.2 Velocity Uniformity (TOOF) (See 3.2.2) Informational, 4.3 Test methods and procedures 4.3.1 Provin

30、g ground tests. These tests shall be conducted at a Government proving ground (designated by the contracting officer) in accordance with the applicable Proving Ground Acceptance Test Procedure. 4.3.2 Charge assessment 5 o Provided by IHSNot for ResaleNo reproduction or networking permitted without l

31、icense from IHS-,-,-MLL-P-q349 13 99799136 0319138 7 MIL-P-48349 (PA) 4.3.2.1 Charge Slope Method. Three or more groups of rounds loaded with selected charge weights of propellant (weights selected should bracket expected service charge weight) shall be conditioned and fired at 70F. From the data ob

32、tained, a charge weight shall be calculated which will yield the prescribed service velocity. This calculated charge weight shall then be loaded into rounds for the uniformity series (see 4.3.3). The difference between the corrected velocity obtained during the uniformity series and the service velo

33、city shall be compensated for by a final adjustment in charge weight using the slope of the velocity charge weight curve previously 4.3.2.2 Constant Slope Method. After ten (10) lots of a given production series have been fired to provide a good knowledge of the propellant characteristics, the charg

34、e slope method of assessment may be discontinued and the charge weight determined by the constant slope method. A composite velocity versus charge weight versus pressure curve can be established from test results generated. This curve can then be used as in 4.3.2.1 above to calculate the charge weig

35、ht needed to achieve service velocity. This calculated charge weight is then to be loaded into rounds for the uniformity series and final adjustment is to be made as indicated above for the charge slope method. 4.3.3 Uniformity series 4.3.3.1 145OF. Thirty rounds using Stick Propellant Charges shall

36、 be assembled with the assessed charge of propellant, conditioned to 145OF (as indicated by a thermocoupled control round (rnd) and fired alternately with calibration rounds. The velocity and pressure means as well as the standard deviations associated with these parameters shall be calculated. All

37、results shall be corrected to recommended charge weight conditions (i.e. difference between as fired charge weight and recommended charge weight ) . 4.3.3.2 TOOF. Thirty rounds using Stick Propellant Charges shall be assembled with the assessed charge of propellant, conditioned to 70F (as indicated

38、by thermocoupled control rnd and fired alternately with calibration rounds. The velocity 6 o Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-P-48349 (PA) and pressure means, as well as the standard deviations associated with these parameters shal

39、l-be calculated. All results shall be corrected to standard shell weight (96 lbs) and standard weapon/firing conditions (i.e. the difference between calibration performance under test conditions and standard Conditions) and to recommended charge weight conditions. 4.3.3.3 -50OF. Thirty rounds using

40、Stick Propellant Charges shall be assembled with the assessed charge of propellant, conditioned to -50F (as indicated by a thermocoupled control rnd) and fired alternately wi-th calibration rounds. The velocity and pressure means as well as the standard deviations associated with these parameters sh

41、all be calculated. All results shall be corrected to recommended charge weight conditions (i.e. difference between as fired charge weight and recommended charge weight). 4.3.3.4 Pressure/Time Evaluation (for information only).Ten Stick Propellant Charges each shall be fired at -50F, t7O0F and t145OF

42、 for pressure versus time evaluation in an instrumented XM198 Cannon where Piezo pressure versus time and ignition delay is recorded in the breech spindle and at a point 45.5 inch RFT (tapped in cannon tube). Muzzle velocity and pressures shall also be recorded. that test conditions have detrimental

43、ly affected the test result, additional charges as required shall be tested. 4.3.5 Straightness. Test bundles of stick propellant shall be placed into a 6.1 inch ID rigid cylinder having a length of 25 inches minimum without the use of tools such as hammers or wedges. Stick straightness shall be mea

44、sured by rolling the stick on a flat plate and measuring the maximum distance observed between the plate and the stick. 4.3.4 Refiring. If for any reason the proving ground considers 4.3.6 Physical Properties (Informational) 4.3.6.1 Density. The propellant specific gravity test shall be conducted on

45、 each lot in accordance with Method 510.1 of MIL-STD-286, except that a 10 ml pycnometer may be used. 7 c Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-P-48347 13 777770b 03L7140 5 MIL-P-48349 (PA) 4.3.6.2 Compressive strength. Prepare one test

46、 specimen from each of five propellant sticks per lot. machined to a length of 0.375 $- .O05 inch with specimen ends perpendicular to the specimen outside diameter within 0.005 inch. A compression test shall be conducted on each specimen at 77 & 4OF. The compressive load shall be applied at a maximu

47、m rate of 1 inch/ inch gage length/minute, until the specimen fails. Failure shall be that point at which the load is maximum. sectional area shall be determined for each specimen prior to test. The compressive strength shall be determined for each specimen as follows : Each specimen shall be The or

48、iginal cross Compressive stress = Applied load at failure Original cross sectional area 4.3.6.3 Deformation. The deformation at the point of maximum load shall be determined on the specimens tested in 4.3.6.2, and shall be expressed as: X Deformation = (Original length-length at max. load) X 100 Ori

49、ginal length 5. PREPARATION FOR DELIVERY 5.1 Packing and marking. Packing and marking shall be in accordance with MIL-STD-652 or other instructions provided by the contracting officer. 6. NOTES 6.1 Ordering data. Procurement documents should specify the 6.1.1 Procurement Requirements following. a. Title, number and date of this specification. b. Packing required (see 5.1) c. Process, Details of the manufacturing process and the equi