1、!INCH-POUND! MI L-R-29565A(AS Beneficial comments (recommendations, additions, deletions) and any pertinent data which may be of use in improving this document should be addressed to: Commanding Offi Cer, Naval Ai r Engi neeri ng Center, Systems Engi neeri ng and Standardization Department (SESD) Co
2、de 53, Lakehurst, NJ 08733-5100, by using the Standardization Document Improvement Proposal (DD Form 1426) appearing at the end of this document 30 November 1990 SUPERSEDING MI L-R-2 95 65 ( AS ) 6 October 1988 MILITARY SPECIFICATION ROCKET MOTOR, MK 125 MOD 1 This specification is approved for use
3、by the Naval Air Systems Command, Department of the Navy, and is available for use by all Departments and Agencies of the Department of Defense. 1. SCOPE 1.1 Scope. This specification establishes the minimum requirements for the manufacture, test, and acceptance of the Mk 125 Mod 1 Rocket Motor. 2.
4、APPLICABLE DOCUMENTS 2.1 Government documents. 2.1 . 1 Sreci fi cations, standards and handbooks. The fol lowi ng spec! fi cations, standards, and handbooks, form a part of this specification to the extent specified herein, Unless otherwise specified, the issues of these documents are those listed i
5、n the issue of the Department of Defense Index of Specification and Standards (DODISS) and supplement thereto, cited in the solici tation (see 6.2). SPECIFICATIONS FEDERAL PPP-T-60 Tape, Packagi ng-, Waterproof PPP-c-1120 MILITARY MIL-P-116 MIL-D-3464 MI L-B-81705 Cushioning Material, Uncompressed B
6、ound Fi ber for Packaging Preservation, Methods of Desiccants, Activated, Bagged, Packaging Use and Stat! c Dehumi di cation Barri er Materi al s, F1 exi bl e, Electrostatic-Free, Heat Sealable AMSC NIA FSC 1340 DISTRIBUTION STATEMENT A. Approved for pub1 i c re1 ease; distribution i s un1 imi ted,
7、Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-R-27565A 13 m 9797906 OLI58731 T m STAN DARDS MI LI TARY MIL-STD-129 MI L-STD-414 MIL-STD-453 MI L-STD-81 O MI L-STD-1167 MI L-STD-1168 MI L-R-2 9565A ( AS Marking for Shipment and Storage Sampl i n
8、g Procedures and Tab1 es for Inspection by Variables for Percent Defec ti ve Inspection, Radiographic Environmental Test Methods and Engineer? ng Gui del i nes Ammuni tion Data Card Ammuni tion Lot Number1 ng MIL-STD-45662 Cal i bration Systems Requirements MS20995 Wire, Safety or Lock MS24347 Drums
9、, Metal , Reusabl e Shipping ang Storage (Un1 ess otherwise indicated, Copi es of federal and mi 1 i tary speci fi cations, standards, and handbooks are avai lable from the Standardization Documents Order Desk, Building 4D, 700 Robbins Avenue, Philadelphia, PA 19111-5094.) 2.1.2 Other Government doc
10、uments, drawl nas, and pub1 i cations. The fol lowi ng other Government documents, drawings, and publications form a part of this specification to the extent specified herein. Un1 ess otherwi se speci fi ed, the issues are those cited in the solicitation. DRAW I NGS NAVAL AIR SYSTEMS COMMAND 1777AS2
11、00 Motor, Rocket MK 125 MOD 1 (Un1 ess otherwi se i ndi cated. coj es are avai 1 ab1 e from the Commandi ng Offi Cer MD 20640-5000.) Naval Ordnance Station (Code 3720) , Indian Head PUBLICATIONS CODE OF FEDERAL REGULATIONS 14 CFR 49 Aeronaut 46 CFR 146 Shipping cs and Space 49 CFR 100-199 Transporta
12、ti on (Copies are available from the Superintendent of Documents, U.S. Government Printing Office, Washington, DC 20402-0001.) 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-l. ci i- MIL-R-29565A 13 W 7779906 CiLi58332 L W 2.2 m. In the event of a
13、 conflict between the text of this specification and the references cited herein, the text of this document takes precedence. Nothing in thi s document, however, supersedes appl i cab1 e laws and regulations un1 ess a specific exemption has been obtained. 0 3. REQUIREMENTS (see 6.3) 3.1 First articl
14、e. When specified (see 6.2), a sample shall be subjected to 3.2 Conformance to documents. The rocket motor shall conform to the first article inspection (see 6.4) in accordance with 4.3. requi rements of thi s speci fi cation and al 1 the requi rements of Draw! ng 1777AS200 (see 4.4.) 3.3 Finish. Al
15、l components shall be free from burrs and contamination which could result in malfunction of the equipment or be a safety hazard (see 4.5.1). 3.4 Rocket motor chamber. The rocket motor chamber shall not leak or exhibi.t permanent deformation as a result of rocket motor operation (see 4.5.2). 3.5 Pro
16、pel 1 ant grai n. No propel 1 ant grai n cracks, separations (propel lant-to-liner or liner-to-case), or fissures are permi tted. three voids having any dimension up to and including 1/8 inch are permitted if separated from each other by a minimum of 1 inch. the distance from similar voids are great
17、er than four times the larger void diameter (see 4.5.3). A maximum of Smaller voids are permitted if 3.6 Le ka e. Rocket motor assemblies shall not leak at a rate of more than 6.102 x 10- -3-93 in /s of helium (see 4.5.4). 3.7 Circuit resistance. The rocket motor ignition circuit resistance shall be
18、 between 0.45 and 0.60 ohms (see 4.5.5). 3.8 Environmental resistance requirements. The Mk 125 Rocket Motor shall meet the performance requirements of 3.9 after exposure to the environmental tests of 4.5.6. 3.9 Performance requirements. All first article rocket motors subjected to ballistic test sha
19、ll meet the performance requirements specified in table I. All conformance test rocket motors subjected to bal 1 i stic test shall be statistical ly analyzed using the requirements specified in 4.4.3.1. 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,
20、-,-NIL-R-29565A 13 = b 0458733 3 W t MI L-R-2 95 65A ( AS ) Paramet er mi ni mum Burn time (s) maxi mum mi ni mum Ignition delay (s) maxi mum Thruster delay (s) maxi mum mi ni mum Thruster force ( 1 bf 1 maxi mum mi ni mum Total impulse (1 bf-s) Maximum thrust (lbf) Thrust angle (degrees) maxi mum m
21、i ni mum Thrust angle change (degrees) TABLE I. Performance requi rements. Test temperature ( OF) -40 140 1740 1770 2.5 2.1 2.1 1.6 o. 020 o. 020 2.1 2.1 0.7 0.7 750 750 650 650 950 1360 27 27 24 24 2 2 Parameter Accuracy a. Thrust - +5.0% b. Time - +0.001 second c. Temperature - +5“ F d. Minimum fr
22、equency 680 Hz e. Pressure - +1 .O% res pons e 3.9.2 Test firinq. The rocket motor shall meet the following criteria during the test firing (see 4.6.4): a. No component shall be ejected b. c. d. No component subject to loading shall yield or fail No burn through or high degree of asymmetric nozzle e
23、rosion No hot spot on motor case or head cap shall occur 3.10 Production lot designation. The lot number shall identify the following (see 4.4.1): a. Manufacturers CAGE Code b. c. Lot sequence number . The month and year the oldest batch of propellant in the rocket motor lot was cast 4 Provided by I
24、HSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. a e a t z MIL-R-235bSA 13 99799Ob 045873q 5 MI L-R-2 9565A( AS) 3.11 Workmanship. Workmanship shall be that required by the best industrial practices governing the qual i ty production of interchangeable parts for
25、 maintaining the dimensions, finishes, tolerances, and quality specified herein and on the applicable drawings (see 4.3 and 4.4). 4. QUALITY ASSURANCE PROVISIONS (see 6.3) 4.1 Responsi bi 1 i ty for inspection. Un1 ess otherwi se speci fi ed i n the contract or purchase order, the contractor is resp
26、onsible for the performance of all inspection requirements (examinations and tests) 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 performance of the inspection requirements spec! fi ed her
27、ein, unless di ssapproved 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 servi ces conform to prescri bed requi rements. sections 3 and 5. part of the contractor
28、s overall inspection system or quality program. of any inspection requirements in the specification shall not relieve the contractor of the responsibility of ensuring that all products or supplies submitted to the Government for acceptance comply with all requirements of the contract. Sampling inspe
29、ction, as part of manufacturing operations, is an acceptabl e practice to ascertain conformance to requirements, however, thi s does not authorize submission of known defective material, either indicated or actual, nor does it commit the Government to accept defective material. 4.1.1 ResDonsibility
30、for compliance. All items shall meet all requirements of The inspection set forth in this specification shall become a The absence 4.2 Classification of inspections. The inspection requirements specified herein are classified as follows: a. b. Quality conformance inspection (see 4.4) First article i
31、nspection (see 4.3) 4.3 First article insDection. First article inspection shall be performed by the contractor after award of contract or major change in process or facilities and prior to production, at a location acceptable to the acquiring activity. First article inspection shall be performed on
32、 units which have been produced with equipment and procedures intended for use in production (see 6.3). activity reserves the right to monitor first article inspection. The acquiring 4.3.1 Sample size. Twelve rocket motors shall be subjected to the first article inspection. 4.3.2 Inspection routine.
33、 The rocket motors shall undergo the inspections and tests specified in table II. environmental resistance tests in the sequence shown in table III. motors shall be leak tested and radiographically inspected before the first envi ronmental treatment and after each subsequent envi ronmental .treatmen
34、t. The rocket motors shall be subjected to the The rocket 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-R-27565A 13 = 7777906 0458735 7 - . 9 . 3.4 3.5 3.6 3.7 3.8 3.9 MI L- R-2 95 65A (AS 4.5.2 4.5.3 4.5.4 4.5.5 4.5.6 4.6 TABLE II. First ari
35、ticle test. Treatment or test 123456789101112- _ Hi gh temperature AAAA AA - Thermal shock BBAA AA _ Salt fog cc Vi brati on Drop Ballistic test at -40F D B B at 140F D B B at -4O“F, head end E - at 140F. nozzle end E at -40F A B F B C C at 140F A B F B C C I Inspection or test I Reaui rement I Test
36、 I I Visual inspection 3.3 4.5.1 Inspection or test Read rement Vi sua1 i nspecti on 3.3 Hydrostatic proof 3.4 Radiographic inspection 3.5 Circuit resi stance test 3.7 Bal 11 sti c Derformance 3.9 Hydrostatik proof Radi ographi c i nspecti on Leak test Circuit resi stance test Envi ronmental test Ba
37、llistic test Test 4.5.1 4.5.2 4.5.3 4.5.5 . 4.6 TABLE III. Environmental test matrix. .L/ 4.4.1 Serialization. Each rocket motor shall be identified by a lot number 4.4.2 Nondestructive inspection and test sample. Unless otherwise specified and a unique serial number in accordance with MIL-SSD-1168
38、(see 6.2). in the applicable test method, sampling for nondestructive tests shall be 100%. 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-R-29565A 13 = 9747706 0458736 7 W . MI L-R-2 95 65A ( AS ) 4.4.3 Ballistic test sample. Ballistic test sa
39、mples shall be selected by the Government acquiring activity for test firing after completion of the production lot. propellant batches. 4.4.3.1 individual lots shall be in accordance with MIL-STD-414, reduced sampling plan, inspection level II, for each temperature tested except that as many batche
40、s as possible must be represented at each temperature extreme. be evaluated and accepted in accordance with MIL-STD-414, standard deviation method, single or double specification limit (as applicable), variability unknown with an AQL of 1 .O%. The ballistic test sample shall be as equally divided as
41、 possible among Ballistic test sample evaluation. The ballistic test sample size for The ballistic data shall 4.5 Nondestructive test methods (see 6.3). 4.5.1 Visual inspection. Each rocket motor component and assembly shall be visually inspected for conformance to drawings and workmanship. 4.5.2 Hv
42、drostatic proof test. Each rocket motor chamber shall be hydrostatically tested to 2630 1: 100 lb/in2. A high pressure pump capable of filling the chamber with an incompressible fluid to 2630 1: 100 lb/inZ shall be used to perform the test. 4.5.3 RadioaraPhic inspection. Each propellant grain shall
43、be The O“ reference plane shall be perpendicular to the rocket radiographi cal ly inspected for defects in accordance with MIL-STD-453, qual i ty level II. Unless otherwise specified herein, the units shall be radiographed in two views 90“ apart. motor thruster. 4.5.4 Leak test. Twelve rocket motor
44、assemblies for first article inspection shall be inspected for evidence of leakage using one of the methods described below. 4.5.4.1 Vacuum bomb. The rocket motor shall be placed in a closed bomb. The bomb shall be evacuated to -5 1.0 psig for 25 minutes. The bomb shall then be pressurized to 14.7 s
45、hall be reduced to ambient and the rocket motor removed to inspect for leakage. The rocket motor shall be placed in a leak detector capable of inspecting for leaks at 0.0 lr 1.0 psig. 1.0 psig with helium gas for 10 minutes. The bomb pressure 4.5.4.2 Internal pressurization, The interior of the rock
46、et motor shall be pressurized to 14.7 1: 1.0 psig with helium and be inspected for evidence of leakage in a leak detector capable of inspecting for leaks at 0.0 4.5.5 Circuit resistance. Each rocket motor circuit shall be tested with a low current ohmmeter (10 milliamperes maximum) typical of ordnan
47、ce operations. 1.0 psig. 4.5.6 Environmental resistance. 4.5.6.1 High temDerature storaue. Six rocket motors, in their storage configuration (see 6.5.61, shall be placed in a conditioning chamber at 140F for 42 days in accordance with MIL-STD-810, Method 501.3. 7 Provided by IHSNot for ResaleNo repr
48、oduction or networking permitted without license from IHS-,-,-MIL-R-29565A 13 m 9999906 0458737 O m MI L-R-2 9565A (AS ) 4.5.6.2 Thermal shock. Six rocket motors, in their storage configuration (see 6.5.61, shall be conditioned to 140F for not less than 5 hours. After this period, the rocket motor s
49、hall be transferred to a chamber conditioned to-4O0F for 5 hours. Maximum transfer time is 5 minutes. The forementioned series of temperature conditioning Is one thermal shock cycle. The contractor shall perform three complete thermal shock cycles on the rocket motor is shown on figure 1. 140. E i2 .w 2 W a a lu I- o -AO. 6 CONIfIONING ilhE (HOUF1.S) FIGURE 1. Thermal shock cycle, 4.5.6.3 Salt fog. Two rocket motors, in t
