1、This specification is approved for use 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. ! Beneficial comments (recommendations, additions, deletions) and any per- tinent data which may be of use in improv
2、ing this document should be ad- dressed to: Commanding Officer, Naval Air Engineering Center, Systems Engineering and Standardization Department (SESD) Code 93, Lakehurst, New Jersey 08733, by using the self-addressed Standardization Document Im- provement Proposal (DD Form 1426) appearing at the en
3、d of this document or by letter. 1. SCOPE MIL-L-5590 10 W 999990b 0365358 MIL-L-85590 (AS) 8 April 1985 MILITARY SPECIFICATION LAUNCHER, ROCKET, LAU-61 C/A THERMAL PROTECTED AND LAU-68D/A THERMAL PROTECTED I 1.1 Scope. This specification establishes the requirements for manufac- ture an-eptance of t
4、he LAU-GlC/A and LAU-68D/A Thermal Protected Rocket Launcher, referred to herein as the launcher. 1.2 Classification. The launchers covered by this specification are clas- sified as follows: Type I: Type II: LAU-68D/A - carries seven rockets LAU-61C/A - carries 19 rockets 2. APPLICABLE DOCUMENTS FSC
5、 1055 THIS DOCUMENT CONTAINS .- T#- PAGES Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-_ MIL-L-B5590 LO a 9999906 03b5359 O 6- MIL-L-85590 (AS) 2.1 Government documents. 2.1.1 Specifications, standards, and handbooks. Unless otherwise speci- fied,
6、 the following specifications and standards of the issue listed in that issue of the Department of Defense Index of Specifications and Standards (DoDISS) specified in the solicitation form a part of this specification to the extent specified herein, SPECIFICATIONS MILITARY MIL-P-116 Preservation, Me
7、thods of MIL-N-18307 Nomencl ature and Identification for Electronic, Aeronautical, and Aeronautical Support Equip- ment, Including Ground Support Equipment and Electronic Equipment MIL-S-45743 -Soldering, Manual Type, High Reliability, Electrical UNITED STATES ARMY MISSILE COMMAND MIS-231 56 STANDA
8、RDS MI L I TARY M I L -S TD- 1 O 9 MIL-STD-129 MIL-STD-143 MI L-STD-454 MIL-STD-810 MIL-STD-889 MIL-STD-1648 Intervalometer, 2.75-Inch Rocket Launcher Quality Assurance Terms and Definitions Marking for Shipping and Storage Specifications and Standards, Order of Precedence for the Selection of Stand
9、ard General Requirements for Electronic Equipment Environmental Test Methods Dissimilar Metals Criteria and Test Procedures for Ordnance Exposed to an Aircraft Fuel Fire I 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-L-85570 LO m 7777906 036
10、5360 7 b 2.1.2 Other Government documents, drawings, and publications. The follow- ing Government drawings and publications form a part of this specification to the extent specified herein. PUBLICATIONS NAVAL AIR SYSTEMS COMMAND (Code Ident 30003) WR-54 Palletizing Fleet Issue Unit Loads of Weapon C
11、omponents WR-54/174 Palletizing Fleet Issue Unit Load Rocket Launcher, LAU-61 /A, LAU-68/A or LAU-69/A in Pal let Loading and Storage, MHU 108/E DRAWINGS NAVAL AIR SYSTEMS COMMAND (Code Ident 30003) DL 958AS120 Launcher, L.AU-GlC/A Shipping and F1 ight Configuration DL 958AS150 Launcher, LAU-68D/A S
12、hipping and Flight Configuration (Copies of specifications, standards, handbooks, drawings, and publica- tions required by manufacturers in connection with specific acquisition functions should be obtained from the contracting activity or as directed by the contracting officer. 2.1.3 Order of preced
13、ence. In the event of a conflict between the text of this specification and the references cited herein, the text of this specifi- cation shall take precedence. 3. REQUIREMENTS 3.1 First article. When specified, a sample shall be subjected to first article inspection (see 4.4 and 6.4). 3.2 Design an
14、d construction. The launcher shall be fabricated and assembled in accordance with the drawings, parts list, and other documents listed on DL 958AS120 for Type I launchers and on DL 958AS150 for Type II 1 aunchers. 3.2.1 Materials, processes, and parts. Materials, processes, and parts shall be as spe
15、cified herein. 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I_-_ _- MIL-L-5590 10 W 7999706 03b53b1 7 I 3.2.1.1 Dissimilar metals. Unless suitably protected against electrolytic corrosion. dissimilar metals shall not be used in intimate contact
16、with each other, Dissimilar metals shall be as defined and classified in MIL-STD-889, and shall be protected in accordance with the requirements of MIL-STD-889. 3.2.1.2 Selection of materials. Specifications and standards for all materials and parts, and Government certification and approval of proc
17、esses and equipment, whichare not specifically designated herein, and which are necessary for the execution of this specification, shall be selected in accordance with MIL-STD-143. 3.2.1.3 Standard parts. Standard parts (MS, AN, or JAN) shall be used wherever they are suitable for the purpose, and s
18、hall be identified on the drawing by their part number. Commercial utility parts such as screws, bolts, nuts, cotterpins, etc., may be used provided they possess suitable properties and are replaceable by the standard parts (MS, AN, or JAN) without alteration, and provided the corresponding standard
19、 part numbers are refer- enced in the parts list, and, if practicable, on the contractors drawings. In the event there are no suitable corresponding standard parts in effect on date of invitation for bids, commercial parts may be used provided they have been certified, accompanied by objective quali
20、ty evidence (as specified in MIL-STD-109) that the parts meet all the requirements of this specification (see 6.2.2). 3.2.2 Nomenclature and nameplates. Nomenclature assignment and nameplate approval for equipment identification shall be in accordance with MIL-N-18307. 3.2.3 Interchangeability. All
21、parts having the same part number shall be Parts joined together by welding or riveting shall be inter- completely interchangeable with each other with respect to installation and changeable as assemblies. . performance. 3.2.4 Standards of manufacture. Manufacturing processes and finishes other than
22、 shown on applicable drawings shall receive prior approval of the procuring activity by engineering change proposals or by requests for waivers or deviations (see 6.2.2). The responsibility for any malfunction or failure of the component parts or the assembled equipment to pass the requirement test
23、due to fit, proper application or process, clearances, tolerances, or internal stress shall be assumed by the contractor. 3.2.4.1 Painting limitations. Neither primer nor paint shall be applied to thread, bearing, or working surfaces as specified on drawings and in speci fi cations. 3.2.5 Service li
24、fe. Each launcher tube shall be capable of performing as specified herein for not less than 10 firings. In addition, two randomly selected tubes of each designated launcher shall be operated for up to 15 additional firings to demonstrate extended service life. 4 Provided by IHSNot for ResaleNo repro
25、duction or networking permitted without license from IHS-,-,-MIL-L-5570 10 = 7777906 03b53b2 O MIL-L-85590( AS) 3.3 Characteri stics. 3.3 1 Performance. 3.3.1.1 Insulation resistance. The insulation resistance of the wiring harness after installation in the launcher shall be not less than 20 megohms
26、 (Mohms) at 500 210 Volts direct current (Vdc) from conductor to conductor and conductor to ground. 3.3.1.2 Continuity. The continuity resistance of the MK 40 firing circuit after installation in the launcher shall be not greater than 0.3 ohm. The continuity resistance of the MK 66 firing circuit af
27、ter installation in the launcher shall be not greater than 0.1 ohm. Continuity resistance of any ground circuit shall be not greater than 0.1 ohm. 3.3.1.3 Rocket loading. The launcher shall require not greater than 20 pounds push or pull force exerted on the plug gage. make sufficient contact with t
28、he surface of the rocket igniter contact to transmit a pulse which shall fire a rocket. The firing contact shall 3.3.1.4 Detent pull. The detent shall not release before 400 +50, -0 pounds pull force is reached. 3.3.2 Functi onal. 3.3.2.1 Static firing, With 22.0 +1.0, -0.0 Vdc applied to pin A of J
29、1 or 52 (pin E grounded), the launcher shall ignite all functional rockets, remain intact on the suspension device, and sustain no damage other than darkening of the exposed surfaces. Upon completion of the static firing test, the launcher shall meet the requirements of 3.3#1.1, 3.3.1.2, 3.3.1.3, an
30、d 3.3.1.4. 3.3.2.2 Flight firing. During flight firing, the launcher shall ignite all functional rockets, remain intact on the aircraft rack, and sustain no damage other than darkening of the exposed surfaces. flight firing test, the launcher shall show no evidence of damage or defects, and shall me
31、et the requirements of 3.3.1.1, 3.3.1.2, 3.3.1.3, and 3.3.1.4. 3.4 Environmental conditions. The launcher shall not be damaged, nor shall subsequent performance be degraded, by exposure to any natural combina- tion of service-use environments, These shall include, but shall not be limited to, the fo
32、llowing environments. Upon completion of the 3.4.1 Temperature shock. The launcher shall perform as specified in 3.3.1.1, 3.3.1.2, 3.3.1.3, and 3.3.1.4 after exposure to the temperature shock test of 4.6.2.1. 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from
33、 IHS-,-,-.-I -_II - - MIL-L-5570 LO W 777770b 0365363 2 I MIL-L-85590( AS) 3.4.2 Shock. When tested in accordance with 4.6.2.2, the launcher shall withstand-ries of three half-sine shock pulses of 10.0 +0.5 gravity units (g), 60 to 80 milliseconds (ms) duration, applied to The positive and negative
34、vertical axes; and a series of three half-sine shock pulses of 13.5 - +0.5 g, 60 to 80 ms duration, applied to the positive and negative longitudi- na1 axes. The motors shall not release from the detents, and the intervalo- meter (MIS-23156) shall not advance during the shock pulses. The launcher sh
35、all meet the requirements of 3.3.1.1, 3.3.1.2, 3.3.1.3, and 3.3.1.4 upon completion of the shock test. 3.4.3 Transportation vibration. The palletized launcher shall withstand two 45 t1 minute sinusoidal excitations, covering the frequency range of five to-200 to five Hertz (Hz) in 15 +1 minutes at a
36、 constant amplitude of 1.5 g peak amplitude (PA), applied toeach of the pallets three axes for a total of six vibrations. The motors shall not release from the detents and the intervalometer shall not advance during the vibrations. The launcher shall meet the requirements of 3.3.1.1, 3.3.1.2, 3.3.1.
37、3, and 3.3.1.4 upon completion of the vibration test. 3.4.4 Flight vibration. 3.4.4.1 High speed aircraft. The launcher shall withstand two series of random vibrations, 0.020 M.O02 gravity units squared per Hz (g2/Hz) covering I the frequency range of 10-to 2000 Hz, applied to each of its three axes
38、 for a total of six vibrations. The intervalometer shall not advance and electri- cal continuity between any detent contact arm and pin E of J1 or 52 shall be continuous during all vibrations. Within any 10 ms interval there shall be not greater than five ms of cumulative discontinuity. The launcher
39、 shall meet the requirements of 3.3.1.1, 3.3.1.2, 3.3.1.3, and 3.3.1.4 upon comple- tion of the vibration test. 3.4.4.2 Helicopter. While being subjected to its respective helicopter flight vibration test, the intervalometer shall not advance, and electrical continuity between any detent contact arm
40、 and pin E of J1 or 52 shall be continuous during all vibrations. Within any 10 ms interval there shall be not greater than five ms of cumulative discontinuity, meet the requirements of 3.3.1.1, 3.3.1.2, 3.3.1.3, and 3.3.1.4 after being subjected to its respective helicopter flight vibration test, a
41、nd shall show no evidence of damage or defects. after being subjected to the salt fog test as specified in MIL-STD-810, Method 509, and shall meet the requirements of 3.3.1.1 and 3.3.1.2 immediately before the test and following a 48-hour drying period after the test. The launcher shall 3.4.5 Salt f
42、og. The launcher shall show no evidence of damage or defects 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-L-85590( AS) 3.5 Fast cook-off. While the loaded launcher is being subjected to the fast cook-off test as specified in MIL-STD-1648, th
43、ere shall be no reaction greater than burning from motors, warheads, or fuzes for a period of not less than five mi nutes. Q 3.6 Government-furnished equipment. When specified in the contract or purchase order (see 6.2.1), the Governinent will furnish the contractor with dummy and inert stores to be
44、 used for testing the launcher (see 6.3). 3.7 Workmanship. Workmanship practices shall, be in accordance with MIL- STD-454, Requirement 9. 3.7.1 Soldering practices. Soldering practices shall be in accordance with MIL-S-45743. 4. QUALITY ASSURANCE PROVISIONS 4.1 Responsibility for inspection, Unless
45、 otherwise specified in the con- tract or Durchase order. the contractor is responsible for the performance of all inspection requirements as specified herein. Except as otherwise speci- fied in the contract or purchase order, the contractor may use his own or any other facilities suitable for the p
46、erformance of the inspection requirements specified herein, unless disapproved by the Government, The Government re- serves the right to perform any of the inspections set forth in the specifi- cation where such inspections are deemed necessary to assure supplies and servi ces conform to prescribed
47、requirements. 4.2 Classification of insDections. The inmection reauirements speci- fied herein are classified as follows: a. b. Quality conformance inspection (see 4.5). First article inspection (see 4.4). 4.3 Inspection conditions. Unless otherwise specified here tions shall be performed in accorda
48、nce with the following test a. Temperature: +21 .O - +5.5“C (+70 +lOF). b. Relative humidity: Not greater than 80 percent. n, all condi t i nspec- ons: 7 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-_- MIL-L-5570 LO 7777906 0365365 6 Requirement P
49、aragraph 4.3.1 Power source. The power source for the static firing test and ser- vice life test shall be 22.0 +1.0, -0.0 Vdc and shall be capable of providing not less than three amperes to the launcher connector. be applied through a 5.0 - t0.5 ohm 25 watt resistor. sist of the contractors inspection and the Governments inspection. contractors inspection shall consist of the tests specified in Table I. The tests of
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