NAVY MIL-L-21910-1959 LAUNCHER ROCKET LAU-10 A《LAU-10 A型火箭发射器》.pdf

1、Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NIIL-L- 2191O(Aer) 3. I. 2 Manufacturing Processes and Finish - Unless otherwise approved irr wxing by t

2、he procuring service, the manufacturing processes and finishes shall be as ripecificd herein or on the applicable draw OF drawings. 3.2 Design and Construction: 3.2.1 Conformance to Drawings and Specifications - The launcher shall be constructed in accordance with the applicable drawings and specifi

3、cations listed in Drawing 55A.2751. No departure from, revision or change tothe drawings or specifications listed therein shall be made without prior written approval by the procuring service. 3. 2. 2 Interchangeability - All parts having the same part number shall be directly and completely interch

4、angeable with each other in respect to fit, function and performance. All applicable provisions of Military Specification MIL-1-8500 shall apply. 3. 2.3 Nomenclature and Nameplates - Nomenclature and nameplates shail be in accordance with Specification MIL-N- 18307. 3. 2.4 Weight - The weight of the

5、 launcher in Configuration B including ail attachments and less rockets shmexceed 106 pounds. 3. 2. 5 Electrical Connectors - All electrical connectors shaii conform to Specification MIL-C- 501 5. 3.3 Performance - In addition to the above requirements, the equipment shal meet Workmanship - All deta

6、ils of workmanship shau. be in accordance with high ail requirements imposed by the tests of Section 4. 3.4 quality armament manufacturing practice. Ali parts SU be free from excessive marks, grooves, indentations, cracks, flaws and any other defects which may impair the serviceabiiity, function or

7、performance of the assembled unit. All workmanship shall be of a quality satisfactory to the procuring service or direct representative thereof. 4. QUALITY ASSURANCE PROVIISIQNS 4.1 General - Equipments shall be subjected to the following tests to determine compliance with all the applicable require

8、ments. (1) Preproduction Tests (2) Acceptance Tests 4.2 Preproduction Tests - Preproduction tests duil be condud on ten equipments representative of the equipments to be supplied der the coatract. Preproduction tests shall be conducted at a laboratory designated by the Bureau of Aeronautics. Preprod

9、uction tests shall consist of all tests specified in 4.4 and any other tests deemed necessary by the Bureau of Aeronautics to determine conformance with this specification. 4.3 responsible for accomplishing individual acceptance tests. The launchers shall be submitted for acceptance by lots. Equipme

10、nts comprising e.ach lot shall first have passed the individual tests. Acceptance of each lot will be determined by the launchers successhiy passing the sampling tests. as sZpcified in 4.3.2. All inspection an13 testing at the contractors plant shall be under the supervision of the Government Inspec

11、tor. Acceptance or approval of material during the course of manufacture shall in no case be construed as a guaranty of the acceptance of the finished product. Acceptance tests shall consist of the foliowing: Acceptance Tests - The contractor shall furnish ail samples and shall be (i) Individual Tes

12、ts (2) Sampling Tests 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-_ HIL-L-2lqlO 10 qqqqqob 03037q0 q 9 -_ MlL-L-1191(Aer) individual Tests - individual tests shall be conductal at the COntraCfOrs piant (1) Examiatim of Product (See 4.4.1 ) (2)

13、Operatianal Tests (See 4.4.2) sampling Tests - Sampling tests shall be conducted at a laboratory designated on each equipment witwiitted for acceptance under the contract. and shall conrirt of the following: by the Bureau of Aeronautics on a quantity of equipments specified in 4.3.2.1. Equipmenta. s

14、ubmitted for sampling tests shall be selected by the Government inspector and first shall have passed the individual tests. Sampling tests shall include ali the tests specified in 4.4 and any other tests deemed necessary by the Bureau of Aeronautics to determine that production equipment continues t

15、o be equivalent in performance and construction to the approved preproduction model. Sampling Test Schedule - Sampling for acceptance testing shall be in accordance Lot Sizes - The maximum quantity of launchers required to be deivered monthly 4.3.2.1 with the appendix to MIL-STD-105, inspection leve

16、l L, AQL as specified in 4.5. 4.3.2.2 as specified in the contract. Examination of Product - Each equipment shall be subjected to a complete (1) Dimensions (2) Surface finishes of all parts (3) Assembly Check (4) Workmanship Material and Process Check - In addition to the requirements of 4.4.1 , exa

17、mination for the following to determine conformance with this specificatioa. 4.4.1. 1 the preproduction samples and acceptance lot sampxes shall be subjected to a complete material and process check to insure use of required and certified materiais and compliance with required and approved manufactu

18、ring processes. Also. the samples shall be weighed to determine compliance Operational Tests - ignition System - Continuity of the electrical circuits comprising the ignition system shall be checked. The grounding circuit conhuity and resistance shall also be checked. The resistance measured between

19、 any Detent Pawl (drawing 55A27B9) and the suspension lug threaded inserts (drawing 55AZIC58) shall not exceed O. 1 ohm. 4.4; 2.1 4.4-2.2 ntervalometer - The intervalometer of each launcher shall be checked in the Ripple and the Single firing positions to determine proper functioning in accordance w

20、ith the operational requirements aa specified on drawing 55A27Jl. Tetents - Ranom puU tests shall be conducted on individual detents. At least one detent ahail e puu-teStea 011 each launcher. The detent shall release with a puli of 1,600 to 2,4M) pounds total load, but shall not release with a pui o

21、f less than 1,600 pounds total load or fail to release with a*pull of as900 pounds total Load 4.4.2.3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-L-21710 10 7777706 0301771 O W -u MIL-L21910(Aer) 4.4.3 Waterproofness Test - The launcher in co

22、nfiguration IrAtr shall be tested in accordance with the waterproofness test of Specification MIL-P-116. 4.4.4 Moisture Penetration Resistance Test - Approximately one pound of completely re- activated desiccant in a bag shall be placed in the launcher. The launcher shall be conditioned for 24 hours

23、 at 100“ F f 2“ F and 95% relative humidity. After conditioning, the bag of desiccant shall be replaced with a fresh weighed bag of completely reactivated desiccant (approximately 1 pound). The launcher shall then be exposed for a period of 64 to 68 hours, to the conditions set forth above, after wh

24、ich it shall be reopened and the bag of desiccant reweighed. The weight increase shall not exceed .O7 grams per 100 square inches of external launcher surface area (A) per 24 hours and shall be calculated as shown below: (W2-W1) 2400 TXA Transmission Rate - W1 - Weight (in grams) at the beginning of

25、 the exposure period. W2 - Weight (in grams) at the end of the exposure period. T - Exposed period in hours (64 to 68 hours). A - Area (total exposed in square inches, ) 4.4.5 Environmental Testing - 4.4. 5.1 High Temperature Test - The launcher in Configuration (see 1. ) shall be placed within a he

26、-ternal temperature of the chamber raised to+71“C with an internal relative humidity of not more than 5% and retained at this condition for a continuous period of 50 hours. At the end of the conditioning period, an ignition system continuity and resistance check shail be made, withthe intervalometer

27、 removed, in accordance with Drawing 55 A 2753. The grounding circuit continuity and resistance shail also be checked. The resistance measured between any Detent Pawl, (Drawing 55A27B9) and the suspension lug threaded inserts (Drawing 55A27C58) shail not exceed O. 1 ohm. The temperature shall then b

28、e reduced to room temperature (approximately 70F (ZlOC) ). A waterproofness test shall be conducted in accordance with 4.4.3. 4.4.5.2 Law Temperature Test - The launcher in Configuration “Atr (see 1.1) shaii be placed in a cooling chamber and the internal temperature of the chamber reduced to and ma

29、intained at -53.9“C for a continuous period of 24 hours. At the end of this conditioning period, ignition system and ground circuit continuity and resistance tests shall be conducted in accordance with 4.4.2.1. The temperature shall be raised to room temperature (approximately 2OOC) and a waterproof

30、ness test shall then be conducted in accordance with 4.4.3. 4.4.5.3 Salt Spray Test - Salt spray tests shall be performed in accordance with the salt spray test procedure of Specification MIL-E-5272. The launcher in Configuration IAtt, (see 1.1) shall be subjected to salt spray for a period of 50 ho

31、urs. At the end of the salt spray period, ignition system and grounding circuit continuity and resistance tests shall be conducted in accordance with 4.4.2.1. The interior of the launcher shall be inspected for moisture penetration. if evidence of moisture penetration is found, a waterproofness test

32、 shall be conducted in accordance with 4.4.3. followed by a pressure retention test in accordance with 4.4.4. 4.4.6 Vibration Test 4.4.6.1 Flight Vibration Test - The launcher is Configuratia ttB1t (see 1.1) loaded with four inert 5.0-inch Folding Fin Aircraft Rockets, complete with inert warheads a

33、nd fuzes, shall be subjectedb translational vibration in each of the three principal axes in turn, The launcher shall be vibrated ?or a minimum period of one-haif hour through a frequency range of 8 to 300 cps during which a search shail be made for conditions of resonance or complex motion. Lf a co

34、ndillon of resonance or complex motion is found, fie launcher graduaiy diminishes to zero at the ase, with equal forces applied over the periphery of the cone Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-L-21710 LO 7777706 0301773 Li- c ._ MiL

35、-L-21910(Aer) 4.4.9 (2) . Side (externally applied) - a side load of 437 pounds total load equally distributed from the tip of the cone to the base shall be applied in a manner that also distributes the load over approxi- mately one-half of the circumference. The fairings shall withstand the above l

36、oads without showing any visible signs of failure or damage other than a slight pull of the materia1 at the fairing to fairing band rivets. Detent Tests - 4.4. 9. I Pull Test - mill tests shall be conducted on individual detents. The detent shall release with a pull of 1,600 to 2,400 pounds total lo

37、ad, but shail not release with a pull of less than 1,600 pounds total load or fail to release with a pull of 2,400 pounds total load. 4.4. 9. 2 Shock Load Test - The launcher center section, loaded with four inert 5.0- inch Folding Fin Aircraft Rockets, complete with inert warheads and fuzes, shall

38、be subjected to the forward and aft shock loads experienced during catapult take-off and arrested landing. The load applied shall be 13.5 G in each direction. The time duration of the shock load shall be a minimum of 30 milliseconds to a maximum of one second. The detents shall not break or release

39、rockets during or as a result of this test. 4.4.10 Ground Firing Test - The loaded launcher complete with warheads and fuzes (warheads and fuzes may be inert) in Configuration (see 1.1) shall be suspended from a bomb rack or simulated bomb rack having 14-inch or 30-inch suspension provisions and tes

40、t fired. The ignition connection may be made through either the forward or aft receptacle. The ignition potential shall be between 18 and 29 volts DC. There shall be a ! improper fit and assembly of the shock pan may result in failure to pass the rough handling test, waterproofness test or both. ) P

41、rovided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I MIL-L-21710 10 7797706 0301775 5. PREPARATION FOR DELIVERY 5.1 Palletizing - The complete rocket launcher shali be pailetized for delivery in accordance with procuring service instructions on governmen

42、t furnished pallets. Delivery shall be as directed by the procuring service. 5.2 Marking and Labeling - 5.2.1 Pailets - Marking of the pallets containing the rocket launcher packages shall be in accordance with requirements of MIL-STD-129. 6. NOTES 6.1 Availability of Dummy Stores for Testing - The

43、contractor shall submit requests to the Bureau of Aeronautics for dummy and inert stores to be used for testing as required by this specification. 6.2 Adherence to Drawings and Specifications - Conflict Elimination - Insofar as the contractor is required by provisions of this specification to adhere

44、 rigidly to the drawings listed in Section 2, which may make it impossible in some instances also to comply with the performance and test requirements specified herein; then, in that event, the contractor should promptly notify the procuring activity of such fact, and appropriate changes will be mad

45、e in the applicable drawings, parts, and/or performance requirements as authorized by the procuring activity. Resulting changes to the drawings or specifications shall be executed in accordance with 3. 2.1. 6.3 (Copies of American Society for Testing Materials Standard may be obtained from the Ameri

46、can Society for Testing Materials Standard ASTM-D-999 Vibration Test for Shipping Containers. Society, 1916 Race Street, Philadelphia 3, Pennsylvania. ) NOTICE: When Government drawings, specifications or other data are used for any purpose other than in connection with a definitely related Governme

47、nt procurement operation, the United States Government thereby incurs no responsibility for any .obligation whatsoever; and the fact that the Government may have formulated, furnished, or in any way supplied the said drawings, specifications, or other data is not to be regarded by implication or oth

48、erwise as in any manner licensing the holder or any other person or corporation, or conveying any rights or permission to manufacture, use or seil any patented invention that may in any way be related thereto. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-