ARMY MIL-F-48863 C-1985 FUZE GUIDED MISSILE M934E6 PARTS ASSEMBLY LOADING AND PACKING FOR《制导导弹引信M934E6零件的装载 组装和包装》.pdf

1、- 5-3747 MIL-F-4 886 3C (AR1 .I 1 July 1985 SUPERSEDING MIL-F-4 8863B (AR) 24 January 1983 MILITARY SPECIFICATION FUZE, GUIDED MISSILE, M934E6 PARTS ASSEMBLY, LOADING AND PACKING FOR This specification is approved for use by the U Army Armament Munitions and Chemical Command, and is available for us

2、e by all Departments and Agencies of the Department of Defense. 1. SCOPE 1.1 Scope. This specification contains the performance requirements and quality assurance provisions for the fabrication and acceptance of components, assemblies, loading and packaging for one type of fuze designated as Fuze, G

3、uided Missile, M934E6. I 2. APPLICABLE DOCUMENTS 2.1 Government documents 2.1.1 spec i f ied listed in Specif ica solici tat specified Specifications and standards. Un , the following specifications and that issue of Che Department of De tions and Standards (DoDISS) specif ion, form a part of this s

4、pecificat herein. less otherwise standards of the fence Index of ied in the ion to the exten issue t SPECIFICATIONS MILITARY MIL-B-2427 MIL-S-8660 - Silicone Compound MIL-S-45743 - Boxes, Ammunition Packing; Wood, Nailed - Soldering, Manual Type, High Relia- bility, Electrical Connections, for Missi

5、le Systems, Procedures ror Beneficial comments (recommendations, additions, deletions) and any pertinent data which may be Of use in improving this document should be addressed to: Commander, US Army Armament Research mnd Development Center, Attn: AMSMC-QA, Dover, New Jersey 07801-5001 by umng the s

6、elf-addressed Standardization Document Improvement Prowsal (DD Form 1426) aDDCWW at the end of this daeurnmf tw h lrtin FSC 1336 DISTRIBUTION STATEMENT A, Approved for public release; distribution is unlimited, i _- THIS DOCUMENT CONTAINS 75 PAGES 2. . Provided by IHSNot for ResaleNo reproduction or

7、 networking permitted without license from IHS-,-,-MIL-F-VBb3C 13 7779706 032Ll7Ll - MIL-S-46860 MIL-A-48078 . MIL-E-81111 STANDARDS FEDERAL FED-STD-209 MI LI TARY MIL-STD-105 MIL-STD-129 MIL-STD-331 MIL-STD-794 MIL-STD-81OC MIL-F- 4 8 86 3C (AR) - Soldering of Metallic Ribbon Lead Materials to Sold

8、er Coated Conductors, Process for Reflow - Ammunition, Standard Quality Assurance Provisions, General Specif icytions or - Explosive, Plastic-Bonded Molding Powder (PBXN-5) - Clean Room and Work Station Require- ments, Controlled Environment - Sampling Procedures and Tables for Inspection by Attribu

9、tes - Marking for Shipment and Storage - Fuze and Fuze Components, Environmental Performance Tests for - Parts and Equipment, Procedures or Packaging and Packing of - Environmental Test Methods (Revision C) 2.1.2 Other Government documents, drawinqs, and publications. and publications form a part of

10、 this specification to the extent: specified herein. The following other Government documents, drawinas, DRAWINGS US ARMY ARMAMENT, RESEARCH AND DEVELOPMENT CENTER (ARDC) 929706.6 -. Fuze, Guided MissiLe, M934E6 (Copies of specifications, standards, handbooks, drawings, and publications required by

11、manufactureres in connection with specific acquisition functions should be obtained from the contracting activity or as directed by the contracting officer) 2.2 Other publications. The following document forms a part of this specification to the extent specified herein. UnXess otherwise indicated, t

12、he issue in effect on date of invitation for bids shall apply. 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-F-48863C (AR) CODE OF FEDERAL REGULATIONS 49 CFR 170-189 - Department of Transportation Rules for Regulations for the Transpor- tatio

13、n of Explosive and Other Dangerous Articles. (The Department: of Transportation Regulations are now a part of the Code of Federal Regulations (1949 Edition and revisions) available from the superintendent of Documents, Government Printing Office, Washington, D. C Orders for the above publication sho

14、uld cite “49 CFR 0-199 (latest revision) I.) 2.3 Order of precedence. In the event of a conflict between the text of this specification and the references cited herein, the text of this specification shall take precedence. 3. REQUIREMENTS 3.1 Item definitions, The M934E6 fuze shall provide an explos

15、ive output to detonate the Stinger warhead, and electrical outputs to control missile flight motor ignition (FMI). The fuze circuitry shall sense proper missile launch through phases of launcher umbilical retract, launch acceleration and launch motor separation. Internal circuitry shall recognize in

16、puts from the warhead target engagement sensor (the Hard Target Sensor (HTC). Change of velocity resulting from impact shall be recognized by the internal Impact Switch (IS). The fuze shall provide timing for FMIr arming, self-destruct (SD) and detonator delay after IS closing. all performance chara

17、cteristics shall be demonstrated under the following ambient conditions: 3.2 Performance characteristics. Unless otherwise specified, a) Temperature range: +18O to +35OC (+650 to b) Relative humidity: 10 to 95 percent c) Barometric pressure: Local average 2 2 inches of +950F) mer cur y 3.2.1 Electri

18、cal power. The fuze shall function as specified herein when connected to a source of electrical power conforming to the interface criteria of 3.2.13.1 and its subparagraphs. 3.2.2 Power interruption. The fuze, after arming, shall be capable of providing proper electrical and explosive functions for

19、as long as four milliseconds after power source disconnect or shorting occurring simultaneous with, or after generation of, a signal by the HTS cx IS. 3 - Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-flIL-F-4b3C 13 = 777770b 032478b 1 . MIL-F-4886

20、3C (KR) 3.2.3 Isolation. An externally applied umbilical retract signal conforming to 3.2.13.3 and present 20 2 15 milliseconds prior to initial launch switch closure shall be required in order to produce a groper FMI signal. shall be initiated by launch switch closure. The launch switch shall close

21、 when the fuze is subjected to an acceleration greater than 30 g in the N to M direction as specified in Figure 1. Switch closure shall not occur for acceleration less than 22 g. Launch switch closure of 75 microseconds or longer shall be recognized as initial closure. Normal fuze functions shall oc

22、cur only when the launch switch is closed for a minimum of 20 milliseconds during the first 40 + 5 milliseconds after initial closure. conforming to 3.2.13.2 shall be required in order to produce proper FMI and arm signals. within 220 milliseconds after initial launch switch closure. 3.2.6 Flight mo

23、tor ignition. The fuze shall provide FMI signals 260 30 milliseconds after initial launch switch closure subject to sustained closure defined in 3.2.4 and proper interlock signal as defined in 3.2.5. The FMI pulse duration shall be 80 f 50 milliseconds. The FMI signals shall conform to 3.2.13.7. 3.2

24、.7 Arming. The fuze shall provide an electrical arm signal through a current limiting resistor to initiate the electro explosive arm actuator. 3.2.13.9. The rotor shall be free to rotate after occurrence of the arm signal. The rotor shall move to the arm position when the arm signal occurs during su

25、stained longitudinal acceleration equal to or greater than 30 g applied in the N to M direction as specified in Figure 1. The rotation of the rotor into the arm position shall be indicated by an arm position signal 1000 2 150 milliseconds after initial launch switch closure conforming to 3.2.13.10.

26、The fuze shall not arm when the acceleration applied in the N to M direction is less than 22 g, 3.2.8 HTS interrogation. Coincident with the arm signal occurrence, the fuze shall interrogate and determine the signal state of the HTS signal per 3.2.13.4. signal state during interrogation shall result

27、 in elimination of the HTS mode of fuze detonation. Indication of the quiescent signal state shall allow the HTS as a mode for subsequent fuze detonation. 3.2.9 Deto-nation. Coincident with the fuze arm signal occurrence (see 3.2.7) al1 modes of fuze detonation shall be enabled as specified in 3.2.9

28、.1 through 3.2.9.3, within the constraints of 3.2.8. generate a detonator firing signal conforming to 3.2.13.8 and shall initiate the explosive output of 3.2.10. 3.2.4 Launch switch closure (to,. The major fuze functions 3.2.5 Interlock. An externally applied interlock signal The interlock signal sh

29、all be present The arm signal shall conform ta Observance of an active HTS Any of these modes of fuze detonation shall 4 ?+fail Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- . MIL-F-4b3C 13 m 7979906 032Ll787 3 m MIL-F-4 8 86 3 C (AR) i N BASE DIR

30、ECTION OF LONG I TUD I NAL ACCELERATION DI RECTI ON OF FLIGHT , (FORWARD) Figure 1. Fuze Reference Axes Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NIL-F-4b3C L3 9 777770b 03,24788 5 - - MIL-F- 4 8 8 6 3C (AR) 3.2-9.1 Impact switch mode. The impa

31、ct switch shall sense a decrease in velocity in the N to M direction of Figure 1. The impact switch contact shall close as a result of a velocity change of 22,O inches per second minimum applied within 150 microseconds maximum. The impact switch closure shall cause generation of the detonator firing

32、 signal after a variable time delay which is a function of the time between launch switch closure and impact switch closure as specified in Figure 2. The variable delay time shall be measured from the leading edge of the impact switch monitoring signal pulse to the leading edge of the detonator firi

33、ng signal. The impact switch shall not close as a result of a velocity change of less than 14 inches per second maximum, applied in 150 microseconds, maximum. After an j.nitia1 closure of 30 microseconds, additional switch closures (contact bounce) are permissible. active in accordance with 3.2.13.4

34、 shall cause generation of the detonator firing signal within 100 microseconds, 3.2.9.3 Self-destruct mode. The fuze shall generate the detonator firing signal 17 2 2 seconds after initial launch switch closure . 3.2.10 Explosive output. The explosive output of the fuze shall cause a dent equal to o

35、r greater than 0.015 inch in depth in a steel witness block when measured and tested in accordance with MIL-STD-331, Test 301 except that the steel blocks shall .be Rockwell 875 to 895 hardness. 3.2.9.2 H,TS mode. An HTS signal change from quiescent to 3.2.11 Rotor .pg-ie$on. 3.2.11.3. m. The fuze r

36、otor shall be pinned into the in-line position with the explasive lead pe-rpendicular t the base and the lead .aperture opposite the detonator. The orange color on the rotor shall 6e visible through the view window OE the fuze housing . 3.2,11,2 Safe. The fuze rotor shall be pinned into a position 7

37、5 +t6, -4 degrees out-of-line from the arm position. green color an the rotor s The e through the view window Of the fuze husingb 3.2.11.3 Abart. The fuze rotor shall be pinned into a position 60 +ln degrees out- .1 o Provided by IHSNot for ResaleNo reproduction or networking permitted without licen

38、se from IHS-,-,-MIL-F-4 8 86 3C (AR) 3.2.13.1.2 Voltaqe loss. After power source activation, and before first terminal impact, the voltage source shall not be shorted, disconnected, or become equivalent to missile ground for periods greater than 100 microseconds and such conditions shall not occur a

39、t intervals more frequent than 1 millisecond, nor shall they exceed 5 occurrences per 100 milliseconds. 3.2.13.1.3 Neqative voltage maintenance. After the time of power source activation, and before first terminal impact, the negative voltage supply to the fuze shall not become more positive than gr

40、ound (except for the initial 50 milliseconds, a voltage of +5 volts maximum at a current of 50mA max. shall not impair fuze function). Before activation, a potential on the -2Ov fuze power line of -.70 to +1.05 VDC with a 6 milliamp current maximum shall not impair subsequent fuze functioning. 3.2.1

41、3.1.4 Voltage drop. During umbilical retract squib activation, a voltage drop on the negative power supply line to between -11V and -2OV for 13 msec maximum shall not impair fuze functioning. 3.2.13.1.5 Flight motor iqnition power connection. The fuze power return shall be connected to pin 15. The -

42、20 volt electrical power for flight motor ignition shall be connected to pin 7 through a 2.43 ohm 2 1 percent current limiting resistor. +20 volt electrical power for flight motor ignition shall be connected to pin 5 through a second 2.43 ohm - + 1 percent current limiting resistor. 3.2.13.2 Interlo

43、ck siqnal. The interlock indication supplied to the fuze to inhibit fuze functions prior to staging shall be a resistance of 150 ohms or less between pins 20 and 21. The interlock indication is activated by increasing the resistance to greater than 500 kilohms for a minimum of 10 milliseconds prior

44、to flight motor ignition and lasting for a minimum of 5 milliseconds after flight motor ignition. 3.2.13.3 Umbilical retract siqnal. The umbilical retract indication to inhibit flight motor ignition shall be a resistance of 30 ohms or less between pins 18 and 15, external to the fuze. Increasing thi

45、s resistance to greater than 30 kilohms for a minimum of 355 milliseconds shall enable the flight motor ignition. 3.2.13.4 HTS siqnai. The HTS indication in the quiescent condition as supplied to the fuze shall be a resistance of 50 ohms or less between-pins 2 and 13. Increasing the resistance to an

46、 open circuit between pins 2 and 13, or creating a short circuit between pins 2 and 15, or between pins 13 and 15, will activate the HTS circuit. 11 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-F-4b3C 13 9979906 0324794 O 9 MIL-F-48863C (AR 5.

47、2.13.5 Simulated launch signal. The simulated launch signal shall be a voltage pulse of 10.0 2 1.5 volts applied to pin 3 and referenced to the negative voltage source at pin 8. The impedance of the pulse source shall be 680 f. 200 ohms. The pulse shall have a duration of greater than 23 millisecond

48、s to enable the fuze functions. 32.13.6 Substandard simulated launch signal. The substandard simulated launch sisnal shall be the same as 3.2.13.5 except that the pulse duration Shall be less than 17 milliseconds. A greatei: than 50 microsecond pulse shall be used for test purposes. The pulse shall

49、not enable the fuze functions. 3.2.13.7 Flight motor ignition signal. The fuze shall produce flight motor ignition signals during the flight motor dwell time in conformance with 3.2.6. When tested per 4.5.1.1, the flight motor ignition signals shall be +16.5 volts on pin 10 and 4 -16.5 volts on pin 11, both referenced to pin 21. Before and after the dwell period, pins 10 and 11 shall be connected inte