NAVY MIL-P-85364 A-1993 PROPELLANT CTBN 23-17《CTBN 23-17型推进剂》.pdf

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1、- MIL-P-853b4A W 999990b 1949862 970 = 1 INCH POUNDI MIL-P-85364A(AS) 23 September 1993 SUPERSEDING MIL-P-85364(AS) 9 February 1981 MILITARY SPECIFICATION PROPELLANT, CTBN 23-17 This specification is approved for use by the Naval Air Systems Command, Department of the Navy, and is available for use

2、by all Departments and Agencies of the Department of Defense. 1. SCOPE 1.1 Scope. This specification covers the minimum requirements for one type of solid propellant grain (see 6.1). 2. APPLICABLE DOCUMENTS 2.1 Government documents. 2.1.1 Specifications, standards, and handbooks. The following speci

3、fications, standards, and handbooks form a part of this document to the extent specified herein. Unless otherwise specified, the issues of these documents are those listed in the issue of the Department of Defense Index of Specifications and Standards (DODISS) and supplement thereto, cited in the so

4、licitation (see 6.2). SPECIFICATIONS MIL I TARY MIL-G-155 Graphite, Dry (For Use in Ammunition) MIL-A-23950 Aluminum Powder, Spherical MIL-R-82657 Resin, Epoxy, Trifunctional MIL-A-82667/2 Ammonium Perchlorate, Conditioned Beneficial comments (recommendations, additions, deletions) and any pertinent

5、 data which may be of use in improving this document should be addressed to: Commanding Officer, Naval Air Warfare Center Aircraft Division Lakehurst, Systems Requtemments Department, Code SR3, Lakehurst, NJ 08733-5100, by using the self-addressed Standardization Document Improvement Proposal (DD Fo

6、rm 1426 appearing at the end of this document or by letter. AMSC NIA FSC 1340 DISTRIBUTION STATEMENT A. Approved for public release; distribution is unlimited. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4 MIL-P-85364A 9999906 3949863 807 m (Unle

7、ss otherwise indicated, copies of federal and military specifications, standards, and handbooks are available from DODSSP - Customer Service, Standardization Documents Order Desk, 700 Robbins Avenue, Bldg 40, Philadelphia, PA 19111-5094.) 2.1.2 Other Government documents, drawinqs, and publications.

8、 The following other Government documents, drawings, and publications form a part of this document to the extent specified herein. Unless otherwise specified, the issues are those cited in the solicitation. PUBLICATIONS NAVAL SEA SYSTEMS COMMAND OD 18877 OD 18893 Water Content, Determination of OD 1

9、8978 OD 19554 Determination of Burning Rate Versus Pressure from Average Particle Size by the Fisher Air Permeability Apparatus Particle Size Distribution by Micromerograph Analysis PRABL (Application for copies should be addressed to the Commanding Officer, Naval Ship Weapon Systems Engineering Sta

10、tion, NAVSEA Data Support Activity (Code 5H30), Port Hueneme, CA 93043-5007.1 WS 4968 Leci thin (Application for copies should be addressed to Commanding Officer, Naval Ordnance Station, Attn: Code 802, Louisville, KY 40214.) DRAW1 NGS NAVAL AIR SYSTEMS COMMAND 1255AS128 1255AS137 Resin 1255AS138 Ir

11、on oxide, Monohydrate, Yellow 1255AS139 Stannous Octoate 1255AS140 Carboxyterminated Polybutadiene Acrylonitrile An ti ox iden t Copo 1 yme r (Applica.tion for copies should be addressed to Commanding Officer, Naval Air Technical Services Facility (Code 31211, 700 Robbins Avenue, Philadelphia, PA 19

12、111 2.2 Non-Government pub1 ications. The fol lowing documents form a part of thi s document to the extent specified herein. Unless otherwise specified, the issues of the documents which are DOD adopted are those listed in the issue of the DODISS cited in the solicitation. Unless otherwise specified

13、, the issues of documents not listed in the DODISS are the issues of the documents cited in the solicitation (see 6.2). AMERICAN SOCIETY FOR TESTING AND MATERIALS (ASTM) ASTM E 203 Water Using Karl Fischer Reagent ASTM D 792 Density and Specific Gravity (Relative Density) of Plastics by Displacement

14、 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I (Application for copies should be addressed to the American Society for Testing and Materials, 1916 Race Street, Philadelphia, PA 19103-1187.) CHEMICAL PROPULSION INFORMATION AGENCY (CPIA) Publicatio

15、n No. 21 JANNAF Solid Propellant Mechanical Behavior Manual (Application for copies should be addressed to Chemical Propulsion Information Agency, The Johns Hopkins University Applied Physics Laboratory, John Hopkins Road, Laurel, MD 20707.) (Non-Government standards and other publications are norma

16、lly available from the organizations that prepare or distribute the documents. These documents also may be available in or through libraries or other informational services.) 2.3 Order of precedence. In the event of a conflict between the text of this document and the references cited herein, the te

17、xt of this document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. 3. REQUIREMENTS 3.1 Materials. Materials used in making the propellant shall conform to the specifications/drawings listed in table I. 3.

18、2 Composition. The propellant shall contain the materials listed in table I. 3.2.1 Ammonium perchlorate (6). Nominal 6p ammonium perchlorate (AP) shall be ground from the specified 200p AP. 3.2.2 Ammonium perchlorate (45). Nominal 45p AP may be ground from the specified 200p AP. 3.3 Burning rate. Th

19、e burning rate shall be determined at 0F over the range of pressures from 1,000 to 3,000 psi. The burning rate shall be at least that calculated from the following lower limit equation: and not greater than that calculated from the following upper limit equation: At a temperature of 140F the corresp

20、onding equation shall be: 0.0465Po.395 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I MIL-P-853b4A m 99999Ob 1949865 b8T m MIL-P-85364A(AS) where rL = the lower limit of acceptable burning rate in inches per second (in/s ru = the upper limit of

21、acceptable burning rate in in/s P = the combustion pressure in pounds per square inch absolute (psia) NOTE: Burn rate samples shall be taken on all lots but burn rate data shall be measured only if the lot fails ballistic performance. Samples shall be held until the motor lot is placed in Condition

22、Code A. TABLE I. Propellant formulation. Materi al Binder 1/ Carboxytermi nated polybutadi ence acrylonitrile copolymer Resin, epoxy, difunctional Resin, epoxy, trifunctional Stannous octoate 11 Antioxidant (Vanox 13) Leci thin Graphite Iron oxide, monohydrate, yellow - 3/ Aluminum powder, spherical

23、, type II Ammonium perchlorate i/ 200p Speci fi cati on/ drawing 1255AS 1 40 1255AS137 MIL-R-82657 1255AS139 1255AS128 WS 4968 MIL-G-155 1255AS138 MI L-A-2 3950 MIL-A-82667/2, Type III Class 2 MIL-A-82667/2, Type III Class 1 1 14.22 0.71 0.99 O. 060 O. 620 O. 400 0.50 0.50 2 .o0 30.00 22 .o0 28.00 W

24、ei ghout to1 erance - +0.14 - +0.01 - +0.01 - +O. 003 - +0.012 - +o. o1 - +o t o1 - +0.01 - +O. 04 - +O. 30 - +o. 22 - +O, 28 - 1/ Binder composition may be adjusted as long as total equals 15.92. - 2/ The catalyst (stannous octoate) may be adjusted from 0.04 percent to 0.08 percent, provided only t

25、he Vanox is adjusted correspondingly, for a bi-weight percent of 0.680. - 31 Iron oxide may be adjusted from O to 0.8 maximum for burn rate. - 4/ AP adjustment blend or grind ratios may be adjusted for burn rate as long as total equals 80 percent. - 5/ See 3.2.1. 4 Provided by IHSNot for ResaleNo re

26、production or networking permitted without license from IHS-,-,-MIL-P-853b4A m 9999906 19498bb 51b m MIL-P-85364A(AS) O“ F 3.4 Physical properties. The physical properties of the propellant shall conform to table II (see 4.4.3). 140F TABLE II. Ph.ysica1 properties. Max elongation (%I min Youngs modu

27、lus (psig) min Max stress (psig) min 1 9 6 460 190 6660 3000 I ProDerty i Temperatur e 3.4.1 Uncured propellant. The uncured propellant shall have (percent wt) content of 0.05 (see 4.4.4). a maximum water 3.4.2 Cured propellant. The cured propellant shall have a maximum density at 25C of 1.680 and a

28、 minimum density of 1.650 (see 4.4.5). 3.5 Workmanship. The material shall be uniform, and free from contamination, foreign material, or any other defect that would prevent its use for the purpose i ntended. 4. QUALITY ASSURANCE PROVISIONS 4.1 Responsibility for inspection. Unless otherwise specifie

29、d in the contract or purchase order, the contractor is responsible for the performance of al 1 inspection requirements (examinations and test) as specified herein. Except as otherwise specified in the contract or purchase order, the contractor may use his own or any other facilities suitable for the

30、 performance of the inspection requirements specified herein, unless disapproved by the Government. The Government reserves the right to perform any of the inspections set forth in this specification where such inspections are deemed necessary to ensure supplies and services conform to prescribed re

31、quirements. 4.1.1 Responsibility for compliance. All items shall meet all requirements of section 3. The inspection set forth in this specification shall become a part of the contractors overall inspection system or quality program. The absence of any inspection requirements in the specification sha

32、ll not relieve the contractor of the responsibility of ensuring that all products or supplies submitted to the Government for acceptance comply with al 1 requirements of the contract. Sampl ing inspection, as part of manufacturing operations, is an acceptable practice to ascertain conformance to req

33、uirements; however, this does not authorize submission of known defective material, either indicated or actual, nor does it commit the Government to accept defective material. 4.2 Inspection conditions. Unless otherwise specified in the contract (see 6.2), all inspections shall be performed under th

34、e following conditions: a. Temperature: Room ambient 18C to 25C (65F to 95F) b. Altitude: Normal ground c. Vibration: No requirement O d. Humidity: 50 percent relative, maximum 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4.3 Qual i ty conforman

35、ce inspection. Quality conformance inspection sha consist of the test methods listed in 4.4. I 1 4.3.1 m. A propellant lot shall be manufactured in one batch from single lots of ingredients. Unless otherwise specified in the contract or purchase order, a lot shall consist of not more than 4,500 poun

36、ds (see 6.2). 4.3.2 Sampling. Sampling shall be as specified in the individual test method. 4.4 Test methods. 4.4.1 6p Ammonium percholorate 4.4.1 .1 fisher subsieve. The particle size shall be determined in accordance with OD 18877 using a sample weight of 1.95 grams. The particle size shall be mea

37、sured at the optimum porosity determined for the sample. 4.4.1.2 Micromerograph. The particle size distribution shall be determined in accordance with OD 18978 using a 45 mg sample with a 200 psi test pressure. The weight average micron value shall be calculated from the 10-point spread (95 percent-

38、 85 percent - etc) method, wherein a summation is made of the percent weighted average particle size of each 10 percent fraction (distribution). 4.4.1.3 Surface water. The surface water (percent wt) shall be determined accordance with OD 18893 using a 10 gram sample dissolved in 100 mL of methano pr

39、e-saturated with 15 grams of ground AP. OD 19554 using a 1- by 2.60- by 6.00-inch slab. accordance with section 4 of CPIA Pub1 ication NO. 21. 4.4.2 Burning rate. The burning rate shall be determined in accordance wi 4.4.3 Physical properties. The test for physical properties shall be in in h 4.4.4

40、Water. The water (percent wt) of the uncured propellant shall be determined in accordance with ASTM E 203 using a 10- to 20-gram sample in 100 mL of 3:l chloroformmethanol solution. Allow the sample to stir for 10 minutes and run a timed blank on the neutralized carrier. 4.4.5 Density. The density o

41、f the cured propellant shall be tested in accordance with ASTM D 792 using a l-inch cube sample and hexane as the immersion 1 iquid. 5. PACKAGING This section is not applicable to this specification. 6. NOTES (This section contains information of a general or explanatory nature that may be helpful b

42、ut is not mandatory.) 6.1 Intended use. The propellant described herein is intended for use in the Mk 23 Mods 2 and 3 Rocket Motor. 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-flIL-P-85364A 999990b 19Y98b 399 6.2 Acquisition requirements. Acqui

43、sition documents should specify the a. Title, number, and date of the specification. following: b. Issue of DODISS to be cited in the solicitation, and if required, the specific issue of individual documents referenced (see 2.1 .1 and 2.2). c. Inspection conditions, if other than as specified (see 4

44、.3). d. Lot size, if other than as specified (see 4.3.1). e. That the safety precaution requirements of the “Contractors Safety Manual for Ammunition and Explosives,“ DOD 4145.26#, are applicable. specification is used as part of the description of work to be accomplished by a Government activity, t

45、he safety precaution requirements of “Ammunition and Explosives Ashore,“ OP 5, are applicable. NOTE: When this 6.3 Subject term (key word) listing. MK 23 Mod 2 Jato MK 23 Mod 3 Jato 6.4 Changes from previous issue. Marginal notations are not used in this revision to identify changes with respect to the previous issue due to the extensiveness of the changes. Preparing activity: Navy - AS (Project 1340-N848) Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-