FOR ROCKETS ROCKET SYSTES M ROCKET FUZES ROCKET … 43-0001-30... · ROCKETS, ROCKET SYSTEMS,...

157
TM 43-0001-30 TECHNICAL MANUAL ARMY AMMUNITION DATA SHEETS FOR ROCKETS ROCKET SYSTEM S ROCKET FUZES ROCKET MOTORS (Federal Supply Class 1340) This copy is a reprint which includes current pages from Changes 1 through 5. -—..—. HEADQUARTERS, DEPARTMENT OF THE ARMY DECEMBER 1981

Transcript of FOR ROCKETS ROCKET SYSTES M ROCKET FUZES ROCKET … 43-0001-30... · ROCKETS, ROCKET SYSTEMS,...

  • T M 4 3 - 0 0 0 1 - 3 0

    T E C H N I C A L M A N U A L

    A R M Y A M M U N I T I O N D A T A S H E E T S

    F O R

    R O C K E T S

    R O C K E T S Y S T E M S

    R O C K E T F U Z E S

    R O C K E T M O T O R S

    ( F e d e r a l S u p p l y C l a s s 1 3 4 0 )

    This copy is a reprint which includes current

    pages from Changes 1 through 5.

    — -—..—.

    H E A D Q U A R T E R S , D E P A R T M E N T O F T H E A R M Y

    D E C E M B E R 1 9 8 1

  • TM 43-0001-30C14

    CHANGE ) HEADQUARTERS) DEPARTMENT OF THE ARMY

    NO. 14 ) WASHINGTON, DC, 17 August 2001

    Army Ammunition Data Sheetsfor

    Rockets, Rocket Systems, Rocket Fuzes, Rocket Motors(Federal Supply Class 1340)

    DISTRIBUTION STATEMENT A: Approved for public release; distribution unlimited.

    TM 43-0001-30, 1 December 1981, is changed as follows:

    1. File this change sheet in front of the publication for reference purposes.2. Remove old pages and insert new pages as indicated below.3. New or changed material is indicated by a vertical bar in the outer margin of the page.4. Changed illustrations are indicated by a vertical bar adjacent to the illustration identification number.5. A revised appendix is indicated by a vertical bar adjacent to the title of the appendix.

    Remove Pages Insert Pages

    A and B A and Bi and ii i and ii1-1 thru 1-4 1-1 thru 1-4None 3-6.1 thru 3-6.43-7 thru 3-14 3-7 thru 3-143-25 thru 3-28 3-25 thru 3-28None 3-28.1 thru 3-28.43-33 thru 3-40 3-33 thru 3-403-45 thru 3-48 3-45 thru 3-485-15 thru 5-18 5-15 thru 5-18A-1 and A-2 A-1 and A-2

    DISTRIBUTION: To be distributed in accordance with the initial distribution number (IDN) 340851 requirements for TM 43-0001-30.

    0120803

  • TM 43-0001-30C13

    CHANGE ))

    No. 13 )

    HEADQUARTERSDEPARTMENT OF THE ARMY

    Washington, DC, 12 October 1993

    ARMY AMMUNITION DATA SHEETSFOR

    ROCKETS, ROCKET SYSTEMS, ROCKET FUZES, ROCKET MOTORS(FSC 1340)

    TM 43-0001-30, 1 December 1981, is changed as follows:

    1. Remove old pages and insert new pages as indicated below. New or changed material is indicatedby a vertical bar in the margin of the page.

    Remove Insert Pages

    A (B blank) A and B3-11 thru 3-13 3-11 thru 3-14

    2. File this change sheet in front of the publication for reference purposes,

    By Order of the Secretary of the Army:

    By Order of the Secretary of the Army:

    GORDON R. SULLIVANGeneral, United States Army

    Official: Chief of Staff

    MILTON H. HAMILTONAdministrative Assistant to the

    Secretary of the Army0s467

    To be distributed in accordance with DA Form 12-34-E, Block 0851, requirements for TM 43-0001-30.

  • TM 43-0001-30

    Change 14 A

    *Zero in this column indicates an original page

    LIST OF EFFECTIVE PAGESNOTE The portion of the text affected by the changes is indicated by a

    vertical line in the outer margins of the page. Changes to illustrations are indicated by a vertical line adjacent to the identification number.

    INSERT LATEST CHANGED PAGES. DESTROY SUPERSEDED PAGES.

    Dates of issue for original and changed pages are:

    TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 133, CONSISTING OF THE FOLLOWING:

    Page *Change Page *Change Page *ChangeNo. No. No. No. No. No.

    Original. . . . . . . . . . 0 . . . . . . . 1 December 1981 Change . . . . . . . . . . 8 . . . . . . . 15 February 1991Change . . . . . . . . . . 1 . . . . . . . . . . 1 March 1983 Change . . . . . . . . . . 9 . . . . . . 30 September 1991Change . . . . . . . . . . 2 . . . . . . . . . . 17 June 1983 Change . . . . . . . . . 10 . . . . . . . . . . .30 June 1992Change . . . . . . . . . . 3 . . . . . . . .15 October 1985 Change . . . . . . . . . 11 . . . . . . . . . 30 March 1993Change . . . . . . . . . . 4 . . . . . . . . . . .30 July 1986 Change . . . . . . . . . 12 . . . . . . . . . . .10 May 1993Change . . . . . . . . . . 5 . . . . . . . . . . . .1 July 1988 Change . . . . . . . . . 13 . . . . . . . . 12 October 1993Change . . . . . . . . . . 6 . . . . . . . . . . 30 June 1989 Change . . . . . . . . . 14 . . . . . . . . .17 August 2001Change . . . . . . . . . . 7 . . . . . . . . . 1 August 1990

    Cover ........................................ 0A............................................... 14B ............................................... 13i and ii....................................... 141-1 thru 1-4............................... 142-1 thru 2-17............................. 02-18 and 2-19 ........................... 42-20 .......................................... 02-21 .......................................... 42-22 .......................................... 72-23 and 2-24 ........................... 02-25 .......................................... 12-26 .......................................... 03-1 thru 3-6............................... 03-6.1 thru 3-6.4......................... 143-7 thru 3-14............................. 143-15 and 3-16 ........................... 03-17 .......................................... 53-18 thru 3-24........................... 03-25 thru 3-28........................... 143-28.1 thru 3-28.4..................... 143-29 thru 3-32........................... 03-33 thru 3-40........................... 143-41 thru 3-44........................... 33-45 thru 3-48........................... 144-1 thru 4-4............................... 04-5 ............................................ 94-6 blank .................................. 04-7 thru 4-9............................... 04-10 .......................................... 64-11 thru 4-16........................... 05-1 and 5-2 ............................... 45-2.1 thru 5-2.6......................... 4

    5-3 thru 5-14............................. 05-15 thru 5-18........................... 14A-1 and A-2.............................. 14

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    TECHNICAL MANUAL HEADQUARTERSDEPARTMENT OF THE ARMY

    No. 43-0001-30 Washington, DC, 1 December 1981

    Army Ammunition Data Sheetsfor

    Rockets, Rocket Systems, RocketFuzes, Rocket Motors

    (Federal Supply Class 1340)

    REPORTING ERRORS AND RECOMMENDING IMPROVEMENTS

    You can help improve this manual. If you find any mistakes or if you know of a way to improve the proce-dures, please let us know. Mail your letter, DA Form 2028 (Recommended Changes to Publications andBlank Forms), or DA Form 2028-2 located in the back of this manual directly to Commander, U.S. ArmyTACOM, Armament Research, Development and Engineering Center, ATTN: AMSTA-AR-WEL-S, Pica-tinny Arsenal, NJ 07806-5000. You may also send in your recommended changes via electronic mail or byfax. Our e-mail address is [email protected]. Our fax number is DSN 880-4633, Commercial (973)724-4633. A reply will be furnished to you.

    Page

    CHAPTER 1 INTRODUCTION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-11-1. Purpose . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-11-2. Scope . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-11-3. Quantity-distance Classes and Storage Compatibility Groups. . . . . . . . . . . . . . . . . . . . . . . 1-11-4. Metric Conversion Chart . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-21-5. Key To Abbreviations and Symbols. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-3

    CHAPTER 2 Ground Rockets . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1Rocket, High-Explosive, 3.5-Inch: AT, M28A2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3Rocket, Practice, 3.5-Inch: M29A2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-7Rocket, Ground: 3.5-Inch Smoke (WP) M30 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-11Light Antitank Weapon (LAW) System M72 Series . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-15Rocket, Heat, 66MM, M72, M72A1, M72A2, and M72A3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-17Rocket, Incendiary, 66MM: TPA, M74 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-21Rocket, Practice, 35MM, Subcaliber, M73 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-23

    CHAPTER 3 AIRCRAFT ROCKETS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1Complete Rounds . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1Typical 2.75-Inch Aircraft Rocket (LSFFAR) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-2Rocket, Flechette, 2.75-Inch, WDU-4A/A. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-3Rocket, Flechette, 2.75-Inch w/M255A1 Warhead . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-6.1Rocket, High-Explosive, 2.75-Inch w/M151 Warhead . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-7Rocket, High-Explosive, 2.75-Inch w/M229 Warhead . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-11Rocket, Smoke, WP, 2.75-Inch w/M156 Warhead . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-15Rocket, Practice, 2.75-Inch w/M230 Warhead . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-19Rocket, Practice, 2.75-Inch w/Inert Warhead WTU-1/B . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-23Rocket, Flare, 2.75-Inch w/M257 Illuminating Warhead . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-25

    *This manual supersedes TM 43-0001-30, 1 December 1981, including all changes.

  • TM 43-0001-30

    ii Change 14

    Page

    CHAPTER 3 AIRCRAFT ROCKETS - ContinuedRocket, Flare, 2.75-Inch: w/M278 IR Illuminating Warhead . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-28.1Rocket, 2.75-Inch, Smoke Screening WP, M259. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-29Rocket, Dual Purpose, 2.75-Inch HE w/Warhead, M247 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-31Rocket, High-Explosive, 2.75-Inch, Multipurpose

    Submunition (MPSM) w/M261 Warhead . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-33Rocket, 2.75-Inch, Practice w/M267 Warhead . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-37Grenade, General Purpose, HE: M73 Multipurpose

    Submunition (MPSM), High-Explosive . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-41Grenade, General Purpose, Practice: M75 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-43Rocket, Smoke, Signature, Practice, 2.75-Inch Warhead, M274 . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-45Rocket, 2.75-Inch, Smoke Screening, RP, M264. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-47

    CHAPTER 4 FUZES W/2.75-INCH ROCKETSFuze, Point Detonating, M423 (M427) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-3Fuze, Rocket, Electronic Time, M433 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-7Fuze, Rocket, Proximity, M429 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-9Fuze, Practice, Rocket, M435. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4-11Fuze, Rocket, M439, RC, Variable Time Delay, Remotely Settable . . . . . . . . . . . . . . . . . . . . . . . . 4-13

    CHAPTER 5 ROCKET MOTORS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1Introduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1Rocket Motor Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-2Rocket Motor MK22, Mod 2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-2.1Rocket Motor MK22, Mod 3 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-2.3Rocket Motor MK22, Mod 4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-2.5Motor, Rocket MK40, Mod 3. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-3Rocket Motor (JATO) M3A2. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-7Rocket Motor (JATO) M8 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-11Rocket Motor MK66, Mods 0, 1, 2, 3, and 4 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-15

    APPENDIX A REFERENCES. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . A-1

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    Change 14 1-1

    1.1 PURPOSE.

    1.1.1 This manual provides general and technical infor-mation concerning ground and aircraft rockets. It coversgeneral characteristics, specific data, means of identification,precautions and general information on packing. Generalinformation pertaining to all types and kinds of conventionalammunition and explosives, and color coding for earliermanufactured munitions are contained in TM 9-1300-200.General information on care, handling, preservation, storing,shipping and destruction of ammunition and explosives iscontained in AR 385-64 and DA PAM 385-64. Informationon training of troops in tactical use of 3.5-in. rockets will befound on 66MM rockets in FM 23-25.

    1.1.2 The rockets and components described in chapters2 and 3 belong to Federal Supply Class 1340. Other itemsused in conjunction with the rockets are covered in otherpublications.

    1.2 SCOPE.

    1.2.1 For each item of materiel, there are illustrations anddescriptions together with characteristics and related data.Included in the related data are type classification, logisticscontrol code (LCC), dimensions, weight, performance data,packing data, and shipping and storage data.

    1.2.2 Information concerning supply, operation, andmaintenance of the items will be found in the publicationsreferenced for those items. A complete listing of these pub-lications is maintained in DA PAM 25-30.

    1.2.3 Within this manual, items with the following typeclassifications are included:

    1.2.3.1 Standard (LCC-A, LCC-B) OTCM/AMCTCM.

    1.2.3.2 Contingency (CON).

    1.2.3.3 Limited Procurement (LP).

    1.2.3.4 Reclassified obsolete (OBS) for regular Armyuse, but used by National Guard or Reserve Units.

    1.2.3.5 Reclassified OBS for all Army use, but used byMarine Corps, Air Force, or Navy.

    1.2.3.6 Reclassified OBS, no users, but U.S. stocksremain.

    1.2.4 Items with the following type classification are notincluded: Reclassified OBS for all U.S. use. No U.S. stocksremain. (Foreign use or stock may remain.)

    1.2.5 Numerical values, such as weights, dimensions,candlepower, etc., are nominal values, except when specifiedas maximum or minimum. Actual items may vary slightlyfrom these values. Allowable limits can be obtained fromthe drawings indicated in the data sheets.

    1.3 QUANTITY-DISTANCE CLASSES AND STOR-AGE COMPATIBILITY GROUPS.

    Quantity-Distance (QD) classes and Storage CompatibilityGroups (SCG) listed in this manual are changed. For con-version to new system see table 1-1.

    Notes:

    1/New QD and SCGs are compatible with classes used byNATO nations.

    2/Numbers in parentheses are minimum distances x 100 feetto protect against specific fragment hazards and vary withitems and types of ammunition. (Refer to AR 385-64 andDA PAM 385-64.)

    3/There is no simple conversion from old SCGs to new sys-tem. The SCG groups listed in this column are typical forthe majority of items in the corresponding listed QD classbut do not apply to every individual item in the class. ForSCG of individual items refer to AR 385-64 and DA PAM385-64.

    Table 1-1. Quantity-Distance Classes and Storage Compatibility Groups.

    Quantity-Distance Hazard Class 1/

    Storage Compatibility Group 1/3/

    Old New 2/ Typical - New8 6.17 1.1 D6 1.2(18) E5 1.2(12)4 1.2(08) F3 1.2(04) G2 1.3 C1 1.4 S

    CHAPTER 1INTRODUCTION

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    1-2 Change 14

    1.4 METRIC CONVERSION CHART.

    For approximate conversions to metric measures see table 1-2.

    Table 1-2. Approximate Conversionsto Metric Measures.

    SymbolWhen You

    KnowMultiply

    By To Find Symbol

    LENGTH

    in. inches 2.5 centimeters cm

    ft feet 30 centimeters cm

    yd yards 0.9 meters m

    mi miles 1.6 kilometers km

    AREA

    in2 square inches 6.5 square centimeters cm2

    ft2 square feet 0.09 square meters m2

    yd2 square yards 0.8 square meters m2

    mi2 square miles 2.6 square kilometers km2

    acres 0.4 hectares ha

    WEIGHT

    oz ounces 28 grams g

    lb pounds 0.45 kilograms kg

    short tons (2000 lb)

    0.9 tonnes t

    VOLUME

    tsp teaspoons 5 milliliters ml

    Tbsp tablespoons 15 milliliters ml

    fl oz fluid ounces 30 milliliters ml

    c cups 0.24 liters l

    pt pints 0.47 liters l

    qt quarts 0.95 liters l

    gal gallons 3.8 liters l

    ft3 cubic feet 0.03 cubic meters m3

    yd3 cubic yards 0.76 cubic meters m3

    TEMPERATURE

    SymbolWhen You

    Know SubtractMultiply

    By To Find Symbol

    °F Fahrenheit 32 0.55 Celsius °C

    For approximate conversions from metric measures see table1-3.

    Table 1-3. Approximate Conversionsfrom Metric Measures.

    SymbolWhen You

    KnowMultiply

    By To Find Symbol

    LENGTH

    mm millimeters 0.04 inches in.

    cm centimeters 0.4 inches in.

    m meters 3.3 feet ft

    m meters 1.1 yards yd

    km kilometers 0.6 miles mi

    AREA

    cm2 square centi-meters

    0.16 square inches in2

    m2 square meters 1.2 square yards yd2

    km2 square kilo-meters

    0.4 square miles mi2

    ha hectares (10,000 m2)

    2.5 acres

    WEIGHT

    g grams 0.035 ounces oz

    kg kilograms 2.2 pounds lb

    t tonnes (1000 kg)

    1.1 short tons

    VOLUME

    mL milliliters 0.03 fluid ounces fl oz

    L liters 2.1 pints pt

    L liters 1.06 quarts qt

    L liters 0.26 gallons gal

    m3 cubic meters 35 cubic feet ft3

    m3 cubic meters 1.3 cubic yards yd3

    TEMPERATURE

    SymbolWhen You

    Know SubtractMultiply

    By To Find Symbol

    °C Celsius 1.8 32 Fahren-heit

    °F

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    1.5 KEY TO ABBREVIATIONS AND SYMBOLS.

    APERS ...............AntipersonnelAR ......................Army RegulationAT.......................AntitankBD ......................Base detonatingBE.......................Base ejectionCP .......................Candle powerDA ......................Department of the ArmyDS.......................Discarding sabotFM ......................Field manualFPS .....................Feet per secondFT .......................FeetG’s ......................Force of GravityHE.......................High explosiveHEAT-T-MP........High explosive antitank with tracer, multi-

    purposeHEDP .................High explosive dual purposeHEI .....................High explosive incendiaryHEP ....................High explosive plasticHERA .................High explosive, rocket assistedHVAP..................Hypervelocity, armor piercingHVTP .................Hypervelocity, target practiceIllum ................... IlluminatingJATO................... Jet assisted take offLAW ...................Light antitank weapon(LP)-T.................Test (DODAC)LSFFAR..............Low-spin folding-fin aircraft rocketMod ....................Modifiedmm......................MillimeterMPS....................Meters per second

    MPSM................ Multipurpose submunitionsMS...................... MillisecondsMT ..................... Mechanical timeMTSQ ................ Mechanical time and super-quickMV..................... Muzzle velocityOBS.................... ObsoletePD ...................... Point detonatingPDSQ ................. Point detonating super-quickPI ........................ Point initiatingPIBD .................. Point initiating, base detonatingProx.................... ProximityPWP ................... Plasticized white phosphorousRAD................... Ram air deceleratorRAP.................... Rocket assisted projectileRC ...................... Resistance capacitanceRF....................... Radio frequencyRPS .................... Revolutions per secondS&A ................... Safety and arming deviceSC....................... Supply CatalogSD ...................... Self destroyingSec...................... SecondsSM...................... Supply ManualSQ ...................... Super-quickT ......................... Time fuze or for training only-T........................ With tracerTB ...................... Technical BulletinTM ..................... Technical ManualTP....................... Target practiceTSQ.................... Time super-quickVX...................... Persistent toxic (casualty) nerve gasWP ..................... White phosphorous

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    CHAPTER 2

    GROUND ROCKETS

    2-1

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    ROCKET, HIGH-EXPLOSIVE, 3.5-INCH: AT, M28A2

    Type Classification:

    STD (LCC-B) OTCM 36841 Jul 58

    Use:

    The M28A2 HEAT rocket is usedprimarily against armored targets,tanks and secondary targets, such asgun emplacements, pillboxes and per-sonnel. It is capable of penetratingheavy armor at angles of impact greaterthan 30°. In an antipersonnel role, ithas a fragmentation area 10 yd wide and20 yd deep.

    Description:

    a. The warhead is cylindrical andtapered. The forward end, called theogive, is thin metal and hollow. Therear end, threaded internally to receivethe fuze which is encircled by a safefyband. The warhead contains a copper

    cone whose apex faces aft and acts to shapethe high explosive charge Composition B -

    (Comp B).

    b . The base detonating (BD) rocketfuze M404A2 consists of a body which con-tains the functioning parts; a safety band,a detonator and a booster pellet. The fuzebody and safety band are olive drab. Thefuze mechanism consists of an activatingplunger, a setback spring, a setbacksleeve, a firing pin assembly, a detent spring, an ejection pin and an ejectionspring. The spring-loaded ejection pinpasses through the fuze body.

    c . The motor assembly consists ofa tube which houses the propellant andigniter. The fin assembly is securely at-tached to this tube. The front end of thetube is assembled to the base of the fuze.The rear end forms a nozzle. The cylin-drical motor cavity is divided into four

    2 - 3

  • TM 43-0001-30

    sections by two spacer plates which sup-port the grains of propellant powder.

    d . Each grain of propellant is5-in. long and approximately 3/8-in. indiameter. Three grains are placed ineach of the four sections formed by thespacer plates. Each lot of propellant isadjusted at the time of manufacture togive standard velocity. The igniter ig-nites the propellant.

    e . The igniter consists of a short,cylindrical plastic case containing asmall black powder charge and an elec-trical squib. It is assembled in the for-ward end of the motor on top of the pro-pellant, spacer plates. The leads of theelectrical squib, running parallel to thegrains of propellant, pass from the ig-niter through the nozzle into the expan-sion cone. A green lead (ground) wireis connected to the aluminum supportring of the contact ring assembly. Ared lead (positive) wire is attached to apin which is insulated from the supportring, but is in contact with the coppercontact band. These connections arepositioned 180° apart. Blue lead is usedfor test purpose only.

    f . The fin assembly consists of sixaluminum alloy fins and a contact ringassembly. The contact ring assembly,which encircles the fins, consists ofthree rings. The aluminum support ring,which is innermost, is separated fromthe copper contact ring by a plastic in-sulating ring, The fins are spot weldedto the expansion cone, and the expansioncone is press fitted to the rear of themotor tube. The M24 and the M66 off-route mines utilizing M28A2 HEATrockets are described in TM 43-0001-36.

    Differences between Models:

    The BD rocket fuze M404A1 is similarto BD rocket fuze M404A2. The M404A1differs principally in minor design changesof the functioning parts and the shape of thesafety band.

    Functioning:

    a . When the safety band is removed,the ejection pin moves outward approxi-mately 3/8 of an inch but still prevents allparts of the fuze mechanism from moving.When the rocket is in the firing chamber,the ejection pin is partially depressed bythe chamber, thereby freeing the setbacksleeve so it can move to the rear when therocket is fired. The fuze is still safe,since the ejection pin prevents movementof the actuating sleeve and firing pin.

    b. If it becomes necessary to removethe rocket from the launcher, the ejectionpin will move outward and re-engage thesetback sleeve. This returns the fuze toits original safe condition.

    c_. When the rocket is fired, the forceof inertia causes the setback sleeve to moverearward. It is held in its rearward posi-tion by the lockpin. When the rocket leavesthe muzzle of the launcher, the ejection pinis thrown clear of the fuze by the ejectionpin spring. The fuze is then fully armed.

    d. During flight, tie firing pin leverand firing pin spring prevent the firing pinfrom striking the detonator, The creepspring retards the forward movement ofthe plunger and actuating sleeve. The ac-tion of the creep spring prevents the fuzefrom firing should the rocket strike lightobjects such as thin brush or undergrowth.

    2 - 4

  • TM 43-0001-30

    e . Upon impact with a more resis-tant object, the plunger and actuatingsleeve move forward until the sleeve hitsthe firing pin lever. This causes thefiring pin to strike and detonate the war-head.

    Tabulated Data:

    Rocket:Model - - - - - -Type - - - - - - -Diameter - - - -Length (max) - -Weight - - - - -Performance:

    Operatingtemperaturelimits - - - - -

    Muzzle velocity(at 70°F)(approx) - - - -

    Warhead:Type - - - - - - -Body - - - - - - -Color - - - - - -

    Diameter - - - -Length - - - - - -Weight - - - - -

    M28A2Service3.5 in.23.55 in.9.00 lb

    -20° to + 120°F(-28. 6 to +48.4C)

    325 ft/sec(99 reps)

    HEATSteelOlive drab w/yellowmarkings3, 5 in.10.5 in.4.47 lb

    High-explosive train:Detonator - - - -Booster

    (tetryl) - - - - -Filler (warhead)

    Type - - - - - -weight(approx) - - - -

    Fuze:Model - - - - -

    Type - - - - - - -Diameter - - - -

    M41

    0.17 oz (4.81 g)

    Comp B

    1.88 lb (.854 kg)

    M404A1 or M404A2Base detonating2.0 in.

    Length:Overall - - - -To shoulder(max) - - - - - -

    Weight - - - - - -Armingdistance - - - - -

    Motor:Diameter (atfins) - - - - - --L e n g t h - - - - - -Weight - - - - - -Thrust - - - - - -

    3.48 in.

    2.94 in.1.16 lb

    10 ft (3.05 m)

    3.5 in.10.413.30 lb6,000-10,000 lb

    Propelling initiating train:Igniter:

    Model - - - - - M20A1Charge (blackpowder) - - - - 0.13±0.007

    ( 3 . 5 ± . 2 g )Electricsquab - - - - - - M2

    Propelling charge:Propellant:

    Model - - - -Type - - - - -

    Configuration -

    Weight - - - - - -Burning time:

    At -20°F - - - -At +120°F - - -

    Launchers - - - - -

    Packing - - - - - - -

    Box:Weight (withcontents) - - - -

    M 7SolventMonoperforated,cylindrical, extrudedgrains (12)0.44 lb (198 g)

    0.05 sec0.02 sec

    M20, M20A1,M20A1B1, M20B1

    1 per metal/fiber con-tainer, 3 containersper wooden box

    53.0 lb

    2 - 5

  • TM 43-0001-30

    Dimensions:W/metalcontainer - - - 29-9/16 in. x

    14-1/16 in. x16-19/32 in.

    W/fibercontainer - - - 29-3/16 in. x

    13-7/8 in. x16-19/32 in.

    Cube:W/metal 3container - - - - 1.6ftW/fiber 3container - - - - 1.5ft

    Shipping and storage data:Storage class/SCG - - - - - - - - 1.1EDOT shippingclass - - - - - - - - ADOT designation - ROCKET AMMUNI-

    TION WITH EXPLO-SIVE PROJECTILES

    Field storage -- Group EDrawings:

    Complete assy - -9211744 (82-6-22Loading assy(head) - - - - - - - 82-16-36Loading assy(motor) - - - - - -9225502 (82-16-35)Packing (inner)- -7549038Packing (outer)- -7549040

    References:TM 9-1340-222-34

    DODAC - - - - - - - 1340-H600

    2 - 6

  • TM 43-0001-30

    ROCKET, PRACTICE, 3. 5-INCH M29A2

    Type Classification:

    STD (LLC-B) AMCTCM 36841 (M29A2)

    Use:

    For training personnel inhandling of service rockets.

    Description:

    use, care and

    a . The warhead is completely inert.The practice rockets can be fired at buttoned-up, modified target tanks without danger totank crews. The practice rockets have thesame flight characteristics as the HEATrocket.

    b. The dummy fuze rocket M405 whichseries as a coupling for the warhead andmotor, is cylindrical. It is threaded exter-nally at the forward end to fit into the

    warhead assembly, and internally at therear end to receive the motor assembly.A safety band fits around the seals andfuze. This fuze incorporates a double-locking, bore-riding, round ejection pinassembly simulating that used in basedetonating (BD) fuze M404A2. The body ofthe fuze and the safety band are paintedblue.

    c_. The motor assembly consists of atube which houses the propellant and ig-niter, The fin assembly is securelyattached to this tube. The front end of thetube is assembled to the base of the fuze.The rear end forms a nozzle. The cylin-drical motor cavity is divided into foursections by two spacer plates which sup-port the grains of propellant powder.

    d. Each grain of propellant is 5-in.long and approximately 3/8-in. in

    2 - 7

  • TM 43-0001-30

    diameter. Three grains are placed in eachof the four sections formed by the spacerplates. Each lot of propellant is adjusted atthe time of manufacture to give standardvelocity. The igniter ignites the propellant.

    e. The igniter consists of a short, cyl-indrical plastic case containing a smallblack powder charge and an electrical squib.It is assembled in the forward end of themotor on top of the propellant spacer plates.The leads of the electrical squib, runningparallel to the grains of propellant, passfrom the igniter through the nozzle into theexpansion cone. A green lead (ground) wireis connected to the aluminum support ring ofthe contact ring assembly. A red lead(positive) wire is attached to a pin which isinsulated from the support ring, but is incontact with the copper contact band. Theseconnections are positioned 180° apart. Bluelead is used for test purpose only.

    f. The fin assembly consists of sixaluminum alloy fins and a contact ringassembly. The contact ring assembly,which encircles the fins, consists of threerings. An aluminum support ring, which isinnermost, is separated from the coppercontact ring by a plastic insulating ring. Thefins are spot welded to the expansion cone;the expansion cone is press-fitted to therear of the motor tube.

    Differences between Models:

    a. The M29A1 and M29A2 rockets aresimilar in appearance to the M28A2. TheM29 series differ in that they have a crimp-ing groove at the juncture of the warheadbody and ogive. The rockets of an earlymanufacture are assembled with M28A2rocket warhead metal parts inert loaded withplaster of paris.

    b. The M29A1 warhead differs from theM29A2 warhead in the head and trap and

    spacer assembly. The ogive is attachedto the head body of four screws staked tothe ogive. Some rockets may have the casttrap and square spacer blades.

    The warhead being inert, no functionsoccur when the rocket is fired. The rocketis strictly for training purpose.

    Tabulated Data:

    Rocket:Model - - - - -

    T y p e - - - - - - -Diameter - - - -Length (max) --Weight(approx) - - - - -Performance:

    Operatingtemperaturel i m i t s - - - - - -

    Muzzle velo-city (at 70°F,approx) - - - - -Range (max,approx) - - - - -

    Warhead:T y p e - - - - - - -B o d y - - - - - - -C o l o r - - - - - - -

    Diameter - - - -L e n g t h - - - - - -W e i g h t - - - - - -

    Fuze:M o d e l - - - - - - -T y p e - - - - - - -Diameter - - - -

    Length:Overall - - - - -TO shoulder( m a x ) - - - - - - -

    W e i g h t - - - - - - - -

    M29A2Practice3.5 in.23.6 in.

    9.00 lb

    -20° to +120°F(-28. 6 to +48.4°C)

    334 fps (101.9 reps)

    945 yd (863.7 m)

    InertCast ironBlue w/whitemarkings3.5 in.10.5 in.4.47 lb

    M405A2Dummy2.0 in.

    3.42 in.

    2.94 in.1.01 lb

    2-8

  • TM 43-0001-30

    Motor:Diameter (atfins) - - - - - - - 3.5 in.Length - - - - - - 10.41 in.Weight - - - - - - 3.30 1bThrust - - - - - - 6,000 to 10,000 lbs

    Propellant initiatingtrain:

    Igniter:Model - - - - - -Charge (blackpowder) - - - -

    Electricalsquib - - - - - -

    Propelling charge:Propellant:

    Model, - - - - - -Type - - - - - -Configuration-

    Weight (newtype) - - - - - -Burning time:

    At -20°F - - -At +120°F - -

    Launchers:M29A2 - - - - - -

    M29A1 - - - - - -

    Packing - - - - - - -

    M20A1

    0.125 ± 0.007 OZ+ .2 g)3 . 5 4 ±

    M2

    M7SolventMonoperforated, cylin-drical extruded grains(12)

    0.44 lb (200 g)

    0.05 sec0.02 sec

    M20, M20A1,M20A1B1, M20B1M20, M20B1

    1 per metal/fibercontainer; 3 con-tainers per woodenbox

    Box:Weight (withcontents) - - - - 53.0 lbDimensions:

    W/metalcontainer - - - 29-9/16 in. x 14-1/16

    in. x 6-19/32 in.

    W/fibercontainer - - - 29-3/16 in. x 13-7/8

    in. x 6-19/32 in.

    Cube:W/metalcontainer - - - - 1.6 ft3

    W/fiber3container - - - - 1.5 ft

    Shipping and storage data:Storage class/S C G - - - - - - - 1.2C (12)DOT shippingclass - - - - - - - BDOTdesignation - - - ROCKET AMMUNI-

    TION WITH EMPTYPROJECTILES

    Field storage- - Group CDODAC - - - - - - - 1340-H601Drawings:

    Complete assy - 82-6-23Loading assy -- 82-6-23Fuze - - - - - - - Dummy 72-5-16Packing (inner)- 7549038Packing (outer)- 7549040

    References:TM 9-1340-222-20TM 9-1340-222-34

    2 - 9

  • TM 43-0001-30

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    2-10

  • TM 43-0001-30

    ROCKET, GROUND: 3.5-INCH SMOKE (WP) M30

    Type Classification:

    (obsolete) was AMCTCM STD (LCC-B)36841 Jul 58

    Use:

    The 3.5-in. whiteM30 smoke rocket isscreening purposes.

    Description:

    phosphorous (WP),intended for smoke

    a. Smoke rocket, 3.5-in. WP, M30 isfired in the same manner as rocket M28A2.On impact, the rocket bursts to produce aspray of phosphorous particles. Theseignite on contact with air, generating densewhite smoke. The smoke itself is harmless,but the burning particles produce painfulburns. In external contour, the rocket issimilar to the M28A2. Rocket M30 consists

    of the WP smoke warhead, base detonating(BD) fuze M404A1 or M404A2, and theservice motor assembly.

    b. Rocket fuze BD M404A2 consistsof a body which contains the functioningparts; a safety band, a detonator and abooster pellet. The fuze body and safetyband are olive drab. The fuze mechanismconsists of an activating plunger, a set-back spring, a setback sleeve, a firing pinassembly, a detent spring, an ejection pinand an ejection spring. The spring-loadedejection pin passes th-rough the fuze body.

    c. The motor assembly consists of atube which houses the propellant and ig-niter. The fin assembly is securelyattached to this tube. The front end of thetube is assembled to the base of the fuze,The rear end forms a nozzle. The cylin-drical motor cavity is divided into four

    2 - 1 1

  • TM 43-0001-30

    sections by two spacer plates which supportthe grains of propellant powder.

    d. Each grain of propellant is 5-in. longand approximately 3/8-in. in diameter.Three grains are placed in each of the foursections formed by the spacer plates. Eachlot of propellant is adjusted at the time ofmanufacture to give standard velocity. Theigniter ignites the propellant.

    e. The igniter consists of a short, cyl-indrical plastic case containing a smallblack powder charge and an electrical squib.It is assembled in the forward end of themotor on top of the propellant spacer plates.The leads of the electrical squib, runningparallel to the grains of propellant, passfrom the igniter through the nozzle into theexpansion cone. A green lead (ground) wireis connected to the aluminum support ring ofthe contact ring assembly. A red lead (posi-tive) wire is attached to a pin which is insul-ated from the support ring, but is in contactwith the copper contact band. These con-nections are positioned 180° apart. Bluelead is used for test purpose only.

    f. The fin assembly consists of sixaluminum alloy fins and a contact ringassembly. The contact ring assembly,which encircles the fins, consists of threerings. An aluminum support ring, which isinnermost, is separated from the coppercontact ring by a plastic insulating ring.The fins are spot welded to the expansioncone, and the expansion cone is press fittedto the rear of the motor tube.

    Differences between Models:

    a. This warhead is generally similar tothat of rocket M28A2, except that it has acharge of white phosphorous (WP). At therear, it has a union internally threaded toreceive the fuze. The burster casing (M8)

    is press-fitted into the union, and the steelbody is fitted over it. The steel ogive andthe internal steel dome, which closes theforward end of the filler cavity are at-tached to the body.

    b. This fuze is similar to BD rocketfuze M404A2. The M404A1 differs princi-pally in minor design changes of the func-tioning parts and the shape of the safetyband.

    Functioning:

    a. When the safety band is removed,the injection pin moves outward approxi-mately 3/8 of an inch but still prevents allparts of the fuze mechanism from moving.When the rocket is in the firing chamber,the ejection pin is partially depressed bythe chamber, thereby freeing the setbacksleeve so it can move to the rear when therocket is fired.

    b . The fuze is still safe, since theejection pin prevents movement of theactuating sleeve and firing pin.

    c. If it becomes necessary to removethe rocket from the launcher, the ejectionpin will move outward and re-engage thesetback sleeve. This returns the fuze toits original safe condition.

    d. When the rocket is fired, the forceof inertia causes the setback sleeve tomove rearward, It is held in its rearwardposition by the lockpin. When the rocketleaves the muzzle of the launcher, theejection pin is thrown clear of the fuze bythe ejection pin spring. The fuze is thenfully armed.

    e . During flight, the firing pin leverand firing pin spring prevent the firing pinfrom striking the detonator. The creep

    2 - 1 2

  • TM 43-0001-30

    spring retards the forward movement of theplunger and actuating sleeve. The action ofthe creep spring prevents the fuze fromfiring should the rocket strike light objectssuch as thin brush or undergrowth.

    f . Upon impact with a more resistantobject, the plunger and actuating sleevemove forward until the sleeve hits the firingpin lever. This causes the firing pin tostrike and detonate the burster.

    Tabulated Data:

    Rocket:Model - - - - - - M30DODAC - - - - - 1340-H602Assy drawing- - 82-6-26Type - - - - - - - SmokeDiameter - - - - 3.5 i n .Length (max) - - 23.55 in.Weight (approx)- 9.00 lbPerformance:

    Operatingtemperaturelimits - - - - - -20° to +120°F

    (-28.6° to +48.4°C)Muzzle velocity(at 70°F,approx) - - - - 317 fps (96.7 mps)Range (max,approx) - - - - 945 yd (863.7 m)

    Warhead:Type - - - - - - - ChemicalBody - - - - - - - SteelColor - - - - - - - Gray w/yellow

    markingsDiameter - - - - 3.45 in.Length - - - - - - 10.6 in.Weight - - - - - - 4.47 1b

    High-explosive train:Detonator - - - - M41Booster

    (tetryl) - - - - 0.1702 (4.81 g)Type - - - - - - - W PWeight (approx)- 2.23 lb (1.01 kg)

    Fuze:Model - - - M404A1 or M404A2Type - - - - BD

    Motor:Diameter(at fins) - - - 3.5 in.Length - - - - 10.41 in.Weight - - - - 3.30 lbThrust - - - - 6,000 to 10,000 lb

    Propelling initiating train:Igniter:

    Model - - - M20A1Charge(blackpowder) - - 0.125 ± 0.00702

    (3.54 ± .2 g)Electricsquib - - - - M2

    Propelling charge:Propellant:

    Model - - -Type - - - -Configura-tion - - - - -

    Weight (newtype) - - - -Burning time:

    At -20°F -At +120°F -

    Launchers - - - -

    Packing - - - - -

    Box:Weight (withcontents) - - -Dimensions:

    W/metalcontainer -

    M7Solvent

    Monoperforated, cyl-indrical, extrudedgrains (12)

    0.44 lb (200 g)

    0. 05 see0. 02 secM20, M20A1, M20A1B1,M20B11 per metal/fiber con-tainer; 3 containers perwooden box

    53.0 lb

    29-9/16 in. x 14-1/16tn. x 6-19/32 in.

    2 - 1 3

  • TM 43-0001-30

    W/fibercontainer - - - 29-3/16in. x 13-7/8

    in. x 6-19/32 in.

    Cube:W/metalcontainer - - - - 1.6 ft3W/fiber

    3container - - - - 1.5 ft

    Shipping and storage data:Storage Class/SCG - - - - - -- 1.2H (12)DOT shippingclass - - - - - - - AD O T ROCKET AMMUNITIONdesignation - - - W I T H S M O K E

    PROJECTILES

    Field storage - - Group H

    DODAC - - - - - - - 1340-H602

    Drawings:Completeassembly - - - - - 82-6-26Loadingassembly - - - - - 82-16-39Fuze (M404A2,type BD) - - - - - - 9209515Packing (inner) -7549038Packing (outer) -7549040

    References:TM 9-1340-222-20TM 9-1340-222-34

    2–14

  • TM 43-0001-30

    LIGHT ANTITANK WEAPON (LAW) SYSTEM M72 SERIES

    2-15

  • TM 43-0001-30

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    2-l6

  • TM 43-000

    ROCKET, HEAT, 66 MM, M72, M72A1, M72A2, AND M72A3

    Type Classification:

    M72 & M72A1 OBS-MSR-05806019.M72A2 - STD LCC-B-MSR-09806022.M72A3-STD LCC-A-MSR-09806021.

    Use:

    Primarily for penetration of armoredtargets. It may be used effectively againstbunkers and other light field of fortifications.

    a. Launcher.—

    b. Rocket.

    Description:

    a. The packaged compact portable wea-penis issued as a single shot shoulder-firedlauncher with a HEAT rocket and slingassembly. The rocket launcher is a tubu-lar, telescoping, smooth-bore, open-breech

    1-30

    type weapon. The outer (front) tube ismade of plastic, impregnated fiberglass;the inner (rear tube) is made of aluminum.The inner tube is oriented with respect tothe outer tube by the channel assembly,which rides in an alinement slot in thetrigger housing assembly. The tubes arelocked in the open position when the detentassembly drops into the rectangular holein the trigger housing assembly.

    b . The f in s tab i l i zed rocke t inthis system contains a shaped charge war-head with a point initiating base detonating(PIBD) fuze. The fuze contains a 2-wiresystem from the piezo electric element onthe warhead to the fuze detonator whichprovides electrical fuze initiation when thenose crystal is struck. In addition, thefuze has a mechanical inertial graze ele-ment as a secondary means of functioning.

    2 -17

  • TM 43-0001-30

    Differences between Models: Functioning:

    The M72A2 rocket is similar to the a. Extending the launcher into theM72A1 with the exception of the warhead extended or firing position automaticallywhich contains a precision shaped charge locks the weapon.liner cone. This provides greater targetpenetration than the M72A1. There isalso a minor change in the wiringbetween the piezo electric element andfuze, otherwise the two systems areidentical. The M72A3 is similar toM72A2.

    WARNING

    WEAR EAR PLUGS WHEN FIRING THEWEAPON . THE 100 AND 150 METERMARKINGS ON THE FRONT SIGHTARE COATED WITH RADIOACTIVEMATERIAL, THEN LAMINATEDBETWEEN TWO SHEETS OF PLASTIC.IF SIGHT IS BROKEN, REMOVE ANDPLACE IN A PLASTIC SEALED BAG.RETURN BAG TO AMMUNITIONDISPOSAL PERSONNEL.

    NOTE

    The front sight on theselaunchers, up to and includingthe M72A2 series weapon, isdesigned for use under condi-tions of limited visibility andis coated with a radioactivematerial (Promethium 147)at the 100 and 150 metermarks. On the weapons withthis limited light sight the100 and 150 meter marks arewhite, the remaining markingsare red. On weapons withoutthis feature, all markingson the sight are in red.The M72A3 series weapons donot have this radioactivesight feature.

    b. After the trigger safety handleis released, the trigger is depressed.This releases the channel assembly whichdrives the firing pin into the primerof the rocket motor igniter. Thisignites the black powder in the flashtube, which in turn, ignites the integraligniter of the rocket motor. The igniterinitiates the propellant. The burningpropellant propels the rocket from thelauncher.

    c. Upon target impact, the fuze traindetonates the charge which collapses thecopper liner into a finger shaped jet.The jet is preceded by extremely hot,high velocity gases which melt a hole inthe target. The copper jet thenpenetrates into the target. Almostsimultaneously the body and ogive areblasted into small fragments by thedetonated octol charge. These fragmentstravel adjacent to, and aft of the lineof fire.

    Tabulated Data:

    LAW systems (packaged):Models ----- M72A2Weight ----- 4.7 lbLength:

    Closedposition - 25.77 in.Extendedposition - 35.16 in.

    Launcher --- M72Weight --- 2.50 lb

    Rocket ----- M72Warhead -- M18A1Fuze ----- M412A1Motor ---- M54

    2-18 Change 4

  • TM 43-0001-30

    Warheads:Weight (loadedand fuzed) ---

    Explosive charge:Type ---------Weight -------Body material-

    Color --------

    Fuzes (integral):Type -- - - - -- --

    Weight -------Overall length(max) --------Diameter(max) --------Explosivebooster:

    Type -------

    Weight ----Armingdistance -----

    Motor:weight -------Propellant:

    Model -----Type ------Weight ----Configura-tion ------Number ----

    Velocity -----Thrust at70°F ---------Burning time -Temperaturelimits -------

    Packing ofrocket inlauncher -----

    Packing box:Weight

    2.3 lb w/contents ---- 117.7 lbDimensions ---- 33-1/2 in. x

    60/40 octol0.67 lb (304 g)Steel w/aluminum Cube ----ogiveBlack w/yellow Shipping andmarkings Storage cl

    31-1/813-3/4

    ----- 8.3 ft3

    storage data:ass/

    ----------- 1.1EPoint-initiating, base DOT shipping

    in. xin.

    detonating class ---------- A0.154 lb DOT

    designation --- ROCKET AMMUNITION1.89 in. WITH EXPLOSIVE

    PROJECTILE1.28 in. Field storage - Group E

    *DODAC -------- 1340-H553, 1340-H554,1340-H555, 1340-H557,

    Composition A5(tetryl)

    and 1340-H568

    0.200z (5.6g) Drawings:Complete

    25 - 45 ft (7.6-13.7m) assembly ------ 1OO485O3-M729210276-M72A19244054-M72A2

    0.67 lb Loading ------- 9235663Packing (inner)- 9227925

    M7 Packing (outer)- 9227926D o u b l e b a s e0.138 lb (62.7g) References:

    SC 1340/98-IL TM9-134O-214-1OStick TM 9-1340-222-20 FM 23-3319 TM 9-1340-222-34475 fps (145 reps)

    4250 lb7 to 15 milliseconds

    *See appropriate supply catalog for-40° to +140°F individual NSN’S pertaining to this(-39.6° to 59.4°C) (these) DODAC(s).

    5 per carton; 1 cartonper barrier bag; 3barrier bags per woodenbox

    Change 4 2-19

  • TM 43-0001-30

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    2-20

  • T M 1 3 - 0 0 0 1 - 3 0

    Type Classification:

    STD (LCC-A) AMCTCM 9018 March 72

    Use:

    The M74 incendiary thickenedtriethylaluminum (TPA) is used todefeat or neutralize hard, soft,or jungle targets.Description:

    The M74 consists of a rocket warheadcontaining approximately 1.3 pounds ofTPA, a base detonating (BD) fuze

    Functioning:

    When the projectile is fired, accelera-tion acts upon the fuze sequential leafarming mechanism. The fuze rotorassembly is then free to rotate to thearmed position. When the rotor is inthe armed position, the detonator isalined with the remainder of the explo-sive train. Rocket deceleration, dueto impact, causes the graze elementof the fuze to shift, thereby allowingthe firing pin of the fuze to be driveninto the primer. The primer flashesthrough the flash channel and initiates

    and an adapter which adapts the rocket motor the detonator, then the trademark into the warhead. The rockets are issued in the warhead; disseminating the warheadfour round clips. agent.

    Change 4 2 - 2 1

  • TM 43-0001-30

    Tabulated Data:

    Rocket:Model - - - - - - --Type - - - - - - - - -Length - - - - - - - -Weight (approx) - -

    Performance:Operating temper -ature limits - - - -

    Range (rnax) - - - -Range (rein) - - - -

    Muzzle velocity(approx) - - - - - - -

    Burst radius(approx) - - - - - - -

    Motor:Model - - - - - - --Length - - - - - - - -Weight - - - - - - - -Thrust - - - - - - - -

    Propellant initiatingtrain:

    Igniter:Model - - - - - - -Type - - - - - - - -

    Propelling charge:Propellant - - - - -Type - - - - - - - - -Configuration - - -

    Weight - - - - - - - -Burning time - - -

    Launcher - - - - - - - -

    M74Incendiary21.0 in.2.95 lb

    -40’ to +140°F(-39. 60 to 59. 4°C)825 yd (754 m)22 yd (2o m)(hard targets)

    375 ft/sec

    65. 5 ft (20 m)

    M549.2 in.0.67 lb4250 lb

    M56Integral

    M 7SolventMonoperforated cyl-indrical extrudedgrains (19)0.138 lb7 to 15 millisecondsM202A1

    Packing - - - - - - - --

    Warhead:Model - - - - - ---Type - - - - - - - - -Color - - - - - - - - -

    Length - - - - - - - -Filler (warhead):

    Type - - - - - - --

    Weight - - - - - - --

    Fuze:M o d e l- - - - - - --Type - - - - - - - - -

    DODAC - - - - - ----

    Shipping and storagedata:

    Storage class/SCG - - - - - - ---DOT shippingclass - - - - - - --DOTdesignation - - - - -

    Field storage - - -

    References:TM 3-1055-218-12TM 3-1055-456-12

    Four per clip

    M235IncendiaryRed w/yellow bandand black markings11.60 in.

    TriethylaluminumPyroPhoric (TPA)1.3 lb (0.59 kg)

    M 4 3 4Base detonating

    1340-H110

    1.2L (12)

    A

    ROCKETAMMUNITIONWITH INCENDIARYPROJECTILEGroup D

    Information on M196, four tube-CSclips used in the M1202Al launcher.

    2 - 2 2 Change 7

    *U.S. GOVERNMENT PRINTING OFFICE: 1990-743-049:20203

  • T M 4 3 - 0 0 0 1 - 3 0

    ROCKET, PRACTICE, 35 MM, SUBCALIBER, M73

    Type Classification:

    STD (LCC-A) AMCTCM 7617 April 70

    Use:

    To train personnel in the operation anduse of the 66-mm antitank rocket, M72series.

    Description:

    a. The M190 subcaliber launcher withM73 subcaliber rocket can be used againstall solid stationary or moving targets.

    Together they can be used in all trainingphases, from fixed firing live to simulatedsituations, such as a “trainfire” typeoperation.

    b_ . The M190 subcaliber launcher isa tubular, telescoping, smooth-bore, open-breech weapon.

    c_ . The M73 subcaliber rocket consistsof a spotting head, a motor closure, arocket motor and an igniter assembly. Thespotting head contains the same flash com-position used in the M80 explosive simula-

    tor (TM 9-1370-203-34&P) to assist in locating

    2 - 2 3

  • TM 43-0001-30

    the fired rocket. The forward end of themotor closure provides a cavity that con-tains a base detonating fuze and a primer.The motor case contains tubular grainsor propellant. The rocket is stabilized bysix molded, plastic fins.

    Differences between Models:

    The external appearance of the M190subcaliber is almost identical to theM72A1. The M190 differs from the tacti-cal launcher M72A1 by having a subcaliberrocket and a quick release primer housingdoor to simplify reloading. The usedM72A1 launcher is modified by use of aconversion kit to produce the M190 sub-caliber launcher.

    Functioning:

    Extending the launcher into the extendedor firing position automatically locks theweapon. After the trigger safety handle isreleased, the trigger can be depressed.This releases the channel assembly whichdrives the firing pin into the primer of therocket motor igniter. This ignites theblack powder in the flash tube, which, inturn, ignites the integral igniter of therocket motor. The igniter initiates thepropellant. The burning propellant propelsthe rocket from the launcher. When thespotting head of the rocket strikes a target,an inertia-driven firing pin sets off theprimer. The primer in turn sets off thespotting head which produces a flash, noiseand white smoke.

    Tabulated Data:

    Rocket:Model - - - - - - - - M73Type - - - - - - - - - PracticeWeight - - - - - - - - 0.321bLength - - - - - - - - 8.87 in.

    Diameter - - - - - -Head:

    Material - - - - - -Type - - - - - - - -Charge:

    Flashcomposition - -Color - - - - - - -

    Motor - - - - - - ----Type of propellant:

    Model - - - - - - - -Type - - - - - - - - -Weight - - - - - - - -Configuration - - -Number - - - - - - -

    Fuze - - - - - - - - - - -

    Primer - - - - - - -Velocity at 70°F-Burning time( m a x ) - - - - - - - - -Range - - - - - - --

    Temperature limits:Firing - - - - - - - -

    Storage - - - - - - -

    Launcher - - - - - - - -Packing - - - - - - - - -

    Packing box:Weight w/contents-Dimensions - - - - -

    Cube - - - - - - - - - - -

    Shipping and storagedata:

    Storage class/SCG - - - - - - - - --Dot shippingclass - - - - - - - - -

    1.37 in.

    PlasticSpotting

    0.05oz (1 .41g)BlackSteel

    M7Double base0.02 lb (9 g)Stick3Integral, basedetonatingStab, M26497 fps

    12 milliseconds(55-354 yd)(50-325 m)

    -10° to +135°F(-23. 1° to +56. 65°C)-40° to +140°F(-39. 6° to +59. 4°C)M19030 per fiber con-tainer; 3 containersper wooden box

    58.8 lb (26, 460 g)32-3/4 in. x 13-1/4in. x 15-7/8 in.

    4.0 ft3

    1.2E (04)

    A

    2–24

  • T M 4 3 - 0 0 0 1 - 3 0

    D O T d e s i g n a t i o n - - - - - - - - - R O C K E T A M M U -N I T I O N W I T HEXPLOSIVEPROJECTILE

    * D O D A C - - - - - - - - - - - - - - - - - - 1 3 4 0 - H 7 0 8D r a w i n g s :

    C o m p l e t e a s s y - - - - - - - - - 1 0 2 4 2 7 2 5L o a d i n g a s s y - - - - - - - - - - 1 0 2 4 2 7 2 5P a c k i n g ( i n n e r ) - - - - - - - 1 0 2 4 2 7 4 3P a c k i n g ( o u t e r ) - - - - - - - 1 0 2 4 2 6 9 7

    I n f o r m a t i o n o n S L U F A E m i n e n e u t r a l -i z i n g r o c k e t s , 115MM GB and VXr o c k e t s a n d t h e V I P E R H E A T R o c k e t ,

    R e f e r e n c e s :S C 1 3 4 0 / 9 8 - I LT M 9 - 1 3 4 0 - 2 0 3 - 2 0

    * S e e a p p r o p r i a t e s u p p l y c a t a l o g f o ri n d i v i d u a l N S N ’ S p e r t a i n i n g t o t h i s( t h e s e ) D O D A C ( S ) .

    C h a n g e 1 2 - 2 5

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    2-26

  • TM 43-0001-30

    CHAPTER 3

    AIRCRAFT ROCKETS2.75-Inch

    Complete Rounds: Aircraft Rocket Launchers.

    a. Complete rounds can be assem- b. The rockets can be issued unassem-bled in the combinations in table 3-1. bled. This chapter contains informationThey may be fired from the M157, M158, pertaining to the components of the un-M159C, M3 or M200 2.75-Inch assembled rockets.

    Table 3-1. 2.75-Inch Complete Round Rocket Combinations

    DODAC

    1340-H459

    1340-H4701340-H4711340-H4891340-H4901340-H1611340-H485

    1340-H4881340-H5331340-H5341340-H1601340-H469

    1340-H5191340-H4861340-H5931340-H826

    1340-H8281340-H1801340-H116

    Warhead

    Flechette (ANTIPERSONNEL)WDU/4A/A

    High Explosive M151

    High Explosive M229

    Smoke, WP, M156

    HE, DP

    Practice, WTU-1/BIlluminating M257

    Smoke, Screening WP, M259

    Motor

    Mk40, Mod 3

    Mk4, ModsMk40, Mod 3Mk40, Mod 3Mk40, Mod 3Mk40, Mod 3Mk4, Mod 10

    Mk40, Mod 3Mk40, Mod 3Mk40, Mod 3Mk40, Mod 3Mk40, Mod 3

    Mk40, Mod 3Mk 4, Mod 10Mk40, Mod 13Mk40, Mod 3

    Mk40, and ModsMk40Mk40, Mod 3

    Fuze

    Integral

    M427M433M429M423M423M427

    M429M427M423M423M433

    M423M427M427M438M247NoneM442M446

    3 -1

  • TM 43-0001-30

    TYPICAL 2. 75-INCH AIRCRAFT ROCKET (LSFFAR)

    3-2

  • TM 43-0001-30

    ROCKET, FLECHETTE, 2.75-INCH, WDU-4A/A

    Type Classification:

    STD (LCC-A) AMCTCM 47560 Nov 69

    Use:

    The warhead containsused against personnel.

    Description:

    flechettes and is

    a. The complete round consists of awarhead with an integral fuze and rocketmotor,

    b . The warhead consists of 3 mainparts: a nose section, a body, and an in-tegral fuze. The nose section, a plasticcone bonded to a metal plate, is attachedto the body by shear pins. The body is a

    hollow cylinder loaded with 20 grainflechettes. The most recently manufac-tured WDU-4A/A warheads contain threetracers for the purpose of assisting thepilot/gunner in identifing the beaten zoneof the flechette impact pattern. Twosemicylindrical sleeves retain theflechettes in place. A metal pusher plateis located just aft of the flechettes. Thethreaded end of the body is machined in-ternally to accommodate a base-detonating(BD) fuze.

    c. The low-spin folding-fin aircraftrocket (LSFFAR) is an air-to-groundrocket primarily deployed from rotary-wing and other low-speed aircraft. How-ever, it is also used on Air Force andNavy jet aircraftrestricted single

    in ripple fire and in afire mode.

    3 - 3

  • TM 43-0001-30

    d . The rocket motor is described inChapter 5.

    Differences between Models:

    The Mk 40 Mods 1 and 3 have integralbulkhead motor tubes whereas the Mk 40Mod 0 has nonintegral bulkhead tube. Theigniter of the Mod 3 motor differs fromthat of the Mods 0 and 1 motors in that theigniter has been modified to incorporate acarried, frangible case in lieu of the blow-out plug. Also, the squib is located on theperiphery instead of the center of the case.

    Functioning:

    a. The rocket motor functions whencurrent passes through the launcher firingcontact to the igniter in the rocket motor.This current generates the heat necessaryto initiate the igniter charge which ignitesthe propellant grain. Combustion gasesfrom the burning propellant pressurizes thechamber and exhaust through the nozzle,providing the unequal forces required forrocket thrust.

    b. Functioning of the fuze sets off anexpelling charge which forces the pusherplate, flechettes and semicylindricalsleeves forward. This shears the pinsattaching the nose cone to the body and ex-pels the flechettes into the slipstreamahead of the rocket.

    Tabulated Data:

    Type - - - - - - - - - AntipersonnelWeight (fuzed) - - - 9.3 lbLength - - - - - - - - 17.8 in.Filler:

    Type - - - - - - - - 20-grain flechettesNumber - - - - - - 2200Weight - - - - - - - 6.3 1b

    Body material - - - Extruded aluminum

    Fuze - - - - - ----Type - - - - - - - -Length - - - - - - -Diameter - - - - -Sensitivity - - - -Arming distance-

    Setback to arm- -Color - - - - - - - - -

    Temperature limits:Firing - - - - - - - -

    Storage - - - - ---

    Drawing number- - - -Packaging for com-plete round - - - - - - -

    Packing box:Weight (w/contents - - - - - - -Dimensions - - - - -

    IntegralBase detonating3.30 in.2.55 in.15 G's or less(47-100 yd)(43 -92 m)28 G's approxOlive drab w/whitemarkings

    -40° to +140°F(-39. 6° to +59. 4°C)-40° to +140°F(-39. 6° to +59. 4°C)D67D9700

    1 rocket consistingof warhead, WDLT-4A/A and rocketmotor Mk 40, 3 perfiber container; 4containers perwooden box

    162 lb62-13/16 in. x8-11/16 in. x 9-1/2in.

    cm)Cube - - - - - - - - - 3.5ft3

    Shipping and storage data:Storage class/SCG - - - - - - - - - - 1.2C (12)DOT shippingclass - - - - - - - - - BDOTdesignation - - - - - ROCKET AMMUNI-

    TION WITH INERTLOADED PROJEC-TILE

    Field storage - - - Group FDODAC for completeround - - - - - - - - - - 1340-H459

    3 - 4

  • TM 43-0001-30

    Rocket Motor:Model - - - - - - - - Mk 40, Mod3Length (overall) - - 39.9 in.

    3 - 5

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    3 - 6

  • TM 43-0001-30

    TYPE CLASSIFICATION:

    TBD

    USE:

    The M255A1 warhead contains approximately 1179 60-grain flechettes for use against light material targets and per-sonnel.

    DESCRIPTION:

    The complete round consists of a warhead with an integralfuze and a rocket motor. The warhead consists of a nosecone assembly, a warhead case, and integral fuze, approxi-mately 1179 60-grain flechettes, and an expulsion chargeassembly. The nose cone assembly, a plastic cone bonded toa metal cup-shaped base, is attached to the body by shearpins. The body is a hollow cylinder loaded with approxi-mately 1179 60-grain flechettes. A metal pusher plate islocated just aft of the flechette cargo stack and is forward ofthe expulsion charge assembly. The threaded end of thebody is machined internally to accommodate a base-detonat-ing, remote settable, variable range fuze.

    The primary warhead fuze, M439 RC, is a resistance-capaci-tance electronic variable time delay fuze. The time delay isremotely set for the desired functioning distance (time) bycharging the circuit from the fire control center. The fuzebegins timing at the first motion of the rocket and will func-tion at the prescribed time if the Safety and Arming Device(S&A) is armed. The S&A is a mechanical accelerationintegrator with an unbalanced rotor holding the M84 electricdetonator and a runaway escapement. An accelerationgreater the 27G is necessary to arm the fuze. The M439 RCfuze is a base mounted, forward firing fuze. The fuze con-nector cable extends from the fuze, through the warhead (ina lengthwise groove), and exits the ogive for connection tothe launcher by an unbilical cable.

    The flechette cargo contains approximately 1179 60-grainflechettes, which are deployed by initiation of a 5.5 gramexpulsion charge.

    The spin-stabilized wrap-around fin aircraft rocket is an air-to-ground rocket primarily deployed from rotary-wing andother low-speed aircraft. It can also be used on Air Forceand Navy jet aircraft, as well as in the Mobile GroundLauncher System.

    ROCKET, FLECHETTE, 2.75-INCH W/M255A1 WARHEAD

    Change 14 3-6.1

  • TM 43-0001-30

    FUNCTIONING:

    The rocket motor functions when current passes through thelauncher firing contact to the igniter in the rocket motor.The current generates the heat necessary to detonate theigniter charge which ignites the propellant grain. Combus-tion gases from the burning propellant pressurize the cham-ber and exhaust through the nozzle, providing the unequalforces required for rocket thrust.

    Upon receipt of the fire signal from the pilot, the remote fuzesetter processes the proper time constant (delay) to the M439RC electronic time fuze immediately prior to firing therocket. The intervalometer delivers a 160 millisecond pulseinterval. The pulse is divided into a 45 millisecond fuzecharging pulse, followed by a 45 millisecond rocket firingpulse. The remaining 70 milliseconds are used as dwellinterval to maintain spacing between pairs of rockets fired.

    After the rocket is fired and experiences sustained accelera-tion, the setback weight of the S&A device within the fuzemoves rearward sufficiently to allow the roller attached tothe unbalanced rotor to move out of the groove provided bythe setback weight. Once the roller is free, the unbalancedrotor rotates in response to the acceleration forces. The rota-tion of the rotor is delayed by a runaway escapement whichprovides an arming delay (a function of the acceleration)until the rocket is a safe distance from the aircraft. When thesetback weight experiences the necessary magnitude ofacceleration, the rotor will lock up with the propellant chargeand the fuze is armed. The detonator is now connected to thefiring circuit, the connection between the electronic moduleand the umbilical cable is broken, and electronic timing isstarted.

    From 1.2 to 25 or more seconds after firing, depending uponthe range setting, the detonator is initiated electrically andignites the expelling charge. Gases from the expellingcharge force the pusher plate and cargo stack forward, shear-ing the nose cone (ogive) retaining pins and ejecting theflechettes into the airstream. The actual ejection range issome distance from the target as determined by the fire con-trol computer along with the aircraft QE based on aircraftelevation, ground speed, and range to target.

    TABULATED DATA:

    PERFORMANCE:

    TEMPERATURE LIMITS:

    Warhead:Model .............................................. M255A1Type................................................. FlechetteBody ................................................ AluminumColor................................................ Olive drab w/white

    markingsDiameter .......................................... 2.75 in.Length ............................................. 26.86 in.Weight ............................................. 13.6 lbDODAC........................................... 1340-H462 w/

    MK66 Mod 2 motor; 1340-H411 w/MK66 Mod 4 motor

    Motor:Type................................................. MK66, Mod 2Diameter .......................................... 2.75 in.Length (max) ................................... 41.7 in.Weight ............................................. 24.4 lb (w/MK66,

    Mod 2 motor)Igniter .............................................. 2.2-3.5 ohms resis-

    tanceDODAC........................................... 1340-J147

    Fuze:Model .............................................. M439Type................................................. RC time fuzeDiameter .......................................... 1.5 in. (max)Length ............................................. 2.77 in. overallWeight ............................................. 0.6 lbArming distance .............................. 96-126 mSetback to arm................................. 27gDelay element.................................. ElectronicDelay time ....................................... VariableDetonator......................................... M84 electricalMaximum velocity .......................... 1950 fps (600 mps)

    Operating temperature limits .............. -50°F to +150°F(-46.56°C to +65.56°C)

    3-6.2 Change 14

  • TM 43-0001-30

    DRAWINGS:

    PACKING DATA:

    Assembly drawing (w/MK66Mod 2 motor).................................. 13058370-13

    Assembly drawing (w/MK66Mod 4 motor).................................. 13058370-25Packing and marking drawings....... 9230116

    Packaging (Box):Dimension....................................... 72-13/16 in. x 8-11/

    16 in. x 9-1/2 in. w/MK66, Mod 2 motor

    Cubic contents .................................... 3.5 cu ftTotal explosive weight........................ 7.13 lb (3.24 kg)Total weight (w/contents 4 warheads

    w/motors assembled in fibercontainers)....................................... 138 lb (62.6 kg) w/

    MK66, Mod 2 or 4 motor

    SHIPPING AND STORAGE DATA:

    NOTE

    Rocket, 2.75-Inch, Flechette: w/WarheadM255A1 and Motor MK66 Mod 2 (DODICH462) or Motor MK66 Mod 4 (DODIC H411)is airworthiness certified for the A/MH6 and U/MH60 aircraft only, and will not be issued tounits that do not use these aircraft.

    Packing................................................ 1 rocket consists of warhead M255E1 and Rocket motor MK66 Mod 2 or 4 per fiber container; 4 fiber containers per wooden box

    Complete (Round):DOD hazard class............................ (03) 2.3 C)DOT hazard class ............................ 1.2 CDOT shipping class ......................... ADOT designation ............................. Rocket, UN: 0436

    NSN: 1340-01-309-5799

    DOT label........................................ Explosive 1.2 C

    Change 14 3-6.3

  • TM 43-0001-30

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    3-6.4 Change 14

  • TM 43-0001-30

    TYPE CLASSIFICATION:

    STD (LCC) AMCTCM 3990, 3233, and 5178 Oct 65.

    USE:

    This is a general purpose high-explosive rocket that can bepresently assembled in five different combinations of motorsand fuzes.

    DESCRIPTION:

    This low-spin folding-fin aircraft rocket (LSFFAR) is an air-to-ground rocket primarily deployed from rotary-wing andother low-speed aircraft. It is also used on Air Force andNavy jet aircraft in ripple fire and in a restricted single firemode.

    The warhead consists of two main parts, a nose and a base,brazed together. The nose section is threaded to receive afuze. The base is made of steel and is threaded for attach-ment to rocket motor.

    Fuzes assembled with 2.75-inch rockets are classified aspoint detonating (PD), or proximity, according to the mannerin which they are initiated. Except for the Proximity FuzeM429, these fuzes are nondelay and super-quick. The pointdetonating fuzes and proximity fuzes are threaded into theforward end of the high explosive warhead.

    The M151 warhead is available with fuzes M423, M427,M429, and M433. These fuzes differ from each other func-tionally and have the following characteristics:

    M423 and M427 - Oblique impact sensitive, point-detonat-ing, super-quick type fuze.

    M429 - Transistorized doppler type proximity fuze with asuper-quick impact switch as a backup.

    M433 - A resistance-capacitance multi-option time delayfuze with selectable functioning modes for jungle canopypenetration, bunker penetration and super-quick for open ter-rain.

    The rocket motors are described in Chapter 5.

    FUNCTIONING:

    Fuze Functioning:

    A typical PD fuze (M423 and M427) arms under minimum,sustained acceleration. On impact with the target, the noseof the fuze is crushed and the firing pin strikes the primer.Primer detonation sets off, in sequence: the detonator, thebooster lead-in, the booster, and the explosive in the war-head.

    The M429 proximity fuze is a completely transistorized,continuous wave, doppler device to provide airburst charac-teristics. It was designed primarily for use with high-explo-sive (HE) warheads for improved antipersonnel lethalities.

    The M429 proximity fuze is equipped with a super-quickimpact switch which serves as a backup in the event of fail-ure of the airburst electronics. The arming mechanism issimilar to that contained in the M427 fuze except that it hasbeen modified to include an electric detonator as well as a

    ROCKET, HIGH-EXPLOSIVE, 2.75-INCH W/M151 WARHEAD

    Change 14 3-7

  • TM 43-0001-30

    battery starter assembly to initiate an electric battery. Anelectric detonator is assembled in the rotor. A plastic (lexan)sleeve houses the thermal battery which is located directlyabove the safing and arming (S&A) mechanism.

    The M433 fuze is an electronic multi-option delay timedelay fuze with selectable functioning modes for forest can-opy penetration, bunker structure penetration, and super-quick (SQ) for open terrain. The fuze body is steel. A forestcanopy switch extends from the nose of the fuze to signal tothe fuze electronic circuit when first contact is made with thetree tops. An umbilical assembly is positioned at the nose ofthe fuze for electrical connection to the M132 fuze safetyand timing device located in the helicopter. Internally, thefuze consists of a Resistance Capacitance (RC) electronictime circuit, a safing and arming mechanism with an electri-cal M84 detonator and a booster assembly.

    The M433 fuze has a selectable time delay range thatdepends on the height of the forest canopy (40 to 130 ft).After first contact with the tree tops, a delay timer is acti-vated which results in warhead functioning beneath the can-opy but above ground level. The bunker structurepenetration mode is incorporated into the fuze to defeat themedium hardness targets constructed of logs, earth, bricks,etc. The fuze can be set from the cockpit for penetrating upto 10 feet of protection and destroying the target fromwithin. The hard target penetration RC timer is activated byinertial switch sensing, setback in excess of 1000 G's. Also,an SQ point detonating feature is included to provide opera-tional flexibility in open terrain. This mode is achieved by

    setting delay to zero. First contact with any surface deto-nates the round.

    The M433 has no internal battery. Required voltage is sup-plied by the aircraft via the M132 safety and timing device160 milliseconds prior to the rocket being fired. During this160 millisecond period, fuze is charged to give time delayselected by pilots.

    The M433 fuze is to be used with M151 warheads.

    Testing the M433 fuze against 3 ft thick wood barriers indi-cates warhead detonations may occur 6 in. prior to exit fromthe barrier to as much as 4.5 ft into the bunker void.

    The M433 fuze nose cap is designed to provide fuze sensitiv-ity on oblique/graze impacts. With the cap removed and thefuze set in the delay mode, oblique/graze impact sensitivityis obtained through the inertial action of the firing pin.

    Because of the void sensing characteristics of the M433fuze, complete destruction may be anticipated when a targethit is achieved. It is recommended that rockets be fired inpairs at minimum ranges and steep dive angles to enhancetarget hits.

    DIFFERENCES BETWEEN MODELS:

    The table below identifies the differences between the high-explosive M151 warhead incorporated within the approvedconfigurations of motor and fuze.

    DODAC Warhead Motor Fuze1340-H470 High-Explosive M151 MK 40, Mods 1, 3 M4271340-H471 MK 40, Mod 3 M4331340-H489 MK 40, Mods 1, 3 M4291340-H490 MK 40, Mods 0, 1, 3 M4231340-H161 MK 40, Mod 3 M4231340-H485 MK 4, Mod 10 M4271340-H163 MK 66, Mod 1 or 2 M4231340-H164 MK 66, Mod 1 or 2 M4331340-H582 MK 66, Mod 3 M4331340-H583 MK 66, Mod 3 M4231340-HA12 MK 66, Mod 4 M423

    3-8 Change 14

  • TM 43-0001-30

    Rocket Functioning:

    When the rocket is launched with a PD fuze, it becomes arm-ed from inertial forces resulting from sustained acceleration.This frees the unbalanced rotor to turn and lock the explosivetrain in the armed position. Upon impact with a target, thedetonator functions and initiates the explosive train.

    Upon detonation, the warhead shatters into thousands ofsmall, high-velocity fragments.

    TABULATED DATA:

    TEMPERATURE LIMITS:

    DRAWINGS:

    PACKING DATA:

    Warhead model................................... M151Type .................................................... High explosiveWeight (fuzed) .................................... 8.7 lbLength (w/o fuze) ............................... 12.9 in.Filler:

    Type ................................................ Comp B4Weight............................................. 2.3 lb (1.04 kg)

    Body material ..................................... Pearlitic or ferritic malleable iron

    Color................................................... Olive drab, yellow markings

    Firing .................................................. -65° to +150°F(-53.35° to +64.9°C)

    Storage................................................ -65° to +150°F(-53.35° to +64.9°C)

    Drawing numbers ............................... 8882186, 9220807, 9204528, 9209570, 9235961, 8796521, 9230114, 8796522

    Packing for complete round ............... 1 rocket consisting of Warhead, HE, M151 with Rocket Fuze, M423 or M427 with MK 4, MK 40, or MK 66 motor; 1 or 3 per fiber container; 3, 4 or 25 containers per wooden box or 4 per metal container

    SHIPPING AND STORAGE DATA:

    REFERENCES:

    TM 9-1340-222-20TM 9-1340-222-34SC 1340/98-IL

    *See appropriate supply catalog for individual NSN’s per-taining to this (these) DODAC(s).

    WARNING

    Do not fire M151 warheads with M433 fuzeand MK66 motor from closer than 51 metersfrom other helicopters. There is a remote pos-sibility of airburst due to premature fuze func-tion. Affected lots are: LOP94D825-001through LOP94D825-006.

    Packing box:Weight w/contents:

    Wood............................................ 127 lbMetal ............................................ 147 lb

    Dimensions:Wood............................................ 62-13/16 in. x 8-11/

    16 in. x 9-1/2 in.Metal ............................................ 70.7 in. x 9.24 in. x

    9.24 in.Cube ................................................ 3.5 ft

    Storage class/SCG............................... 1.1EDOT shipping class............................. ADOT designation................................. ROCKET AMMU-

    NITION WITH EXPLOSIVE PRO-JECTILES

    Field storage........................................ Group F*DODAC ............................................ 1340-H470, 1340-

    H471, 1340-H489, 1340-H490, 1340-H161, 1340-H485, 1340-H163, 1340-H164, 1340-H582, 1340-H583, 1340-HA12

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    3-10 Change 14

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    TYPE CLASSIFICATION:

    STD AMCTCM or OTCM 8685

    USE:

    To provide improved aerial artillery capability for the 2.75-inch rocket.

    DESCRIPTION:

    This rocket is an air-to-ground rocket primarily deployedfrom rotary-wing and other low-speed aircraft. It is alsoused on Air Force and Navy jet aircraft in ripple fire mode.

    This rocket is used to enhance the lethality and destructive-ness of the 2.75-inch rocket in its aerial artillery role. It usesthe M229 warhead which is an elongated version of theM151 warhead and is commonly referred to as the 17-poundwarhead.

    It consists of three main parts consisting of the nose, body,and base. The three main parts are welded together. There is

    an alternate two-piece design consisting of a one-piece nosebody plus a base.

    Fuzes assembled with 2.75-inch rockets are classified aspoint detonating (PD) or proximity, according to the mannerin which they are initiated. Except for the Proximity FuzeM429, these fuzes are nondelay and super-quick (SQ). ThePD fuzes and proximity fuze are threaded into the forwardend of the high explosive warhead.

    The M229 warhead is available with fuzes M423, M427, andM429. These fuzes differ from each other functionally andhave the following characteristics:

    M423 and M427 - Oblique impact sensitive, point-detonat-ing, super-quick type fuze.

    .M429 - Transistorized doppler type proximity fuze with asuper-quick impact switch as a backup.

    The rocket motors are described in Chapter 5.

    ROCKET, HIGH-EXPLOSIVE, 2.75-INCH W/M229 WARHEAD

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    DIFFERENCES BETWEEN MODELS:

    The nose and base of the M229 warhead are essentially iden-tical to the M151 parts which are separated by the 10-inchlong cylindrical body.

    The table below identifies the differences between the high-explosive M229 warhead incorporated within the approvedconfigurations of motor and fuze.

    FUNCTIONING:

    Ignition: Functioning of the 2.75-inch rocket with an M229warhead begins when the firing circuit switch is closed.Current passes through the launcher firing contact to theigniter in the rocket motor. This current generates the heatnecessary to initiate the igniter charge, which ignites the pro-pellant grain. Combustion gases from the burning propellantpressurize the chamber and exhaust through the nozzle, pro-viding the unequal forces required for rocket thrust.

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    DODAC Warhead Motor Fuze1340-H469 High-Explosive M229 MK 40, Mod 3 M4331340-H488 MK 40, Mod 1, 3 M4291340-H533 MK 40, Mod 1, 3 M4271340-H534 MK 40, Mod 1, 3 M4231340-H160 MK 40, Mod 3 M4231340-H642 MK 66, Mod 2 M4231340-HA09 MK 66, Mod 4 M423

    Fuze Functioning: The M429 proximity fuze is a completelytransistorized, continuous wave with doppler device to pro-vide airburst characteristics. It is designed primarily for usewith HE warheads for improved antipersonnel lethalities.

    A super-quick impact switch on the M429 serves as a backupin the event of failure of the airburst electronics. The armingmechanism is similar to that contained in the M427 fuzeexcept that it has been modified to include an electric deto-nator as well as a battery starter assembly to initiate an elec-tric battery. An electric detonator is assembled in the rotor.A plastic (lexan) sleeve houses the thermal battery which islocated directly above the S&A mechanism.

    When the rocket is launched, the fuze becomes armed frominertial forces resulting from sustained acceleration. Thisfrees the unbalanced rotor to turn and lock the explosivetrain in the armed position. Upon sensing a target, the deto-nator is fired and initiates the explosive train.

    Upon detonation, the warhead shatters into thousands ofsmall high-velocity fragments.

    TABULATED DATA:

    TEMPERATURE LIMITS:

    Warhead model ................................... M229Type .................................................... High explosiveWeight (fazed)..................................... 18.1 lbLength (w/o fuze)................................ 2303 in.Filler:

    Type................................................. Comp B4Weight ............................................. 4.8 lb (2.18 kg)Color................................................ Olive drab w/yel-

    low markings

    Firing................................................... -65° to +150°F(-53.35° to +64.9°C)

    Storage ................................................ -65° to +150°F(-53.35° to +64.9°C)

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    DRAWINGS:

    PACKING DATA:

    SHIPPING AND STORAGE DATA:

    9220806.............................................. W/Motor, MK40, Mod 3

    13058371............................................ W/Motor, MK66, Mod 2

    9218698.............................................. Warhead, M2299230116 .............................................. Packing and mark-

    ing

    Packing ............................................... 1 per fiber con-tainer, 4 containers per wooden box

    Packaging for complete round............ 1 rocket consisting of warhead, HE, M229 w/rocket fuze and rocket motor per fiber container; 3, 4 or 25 containers per wooden box

    Packing box:Weight (w/contents)........................ 162 lbDimensions ..................................... 72-13/16 in. x 8-11/

    16 in. x 9-1/2 in.Cube................................................ 3.5 cu ft

    Storage class SAG.............................. 1.1EDOT shipping class ............................ ADOT designation ................................ ROCKET AMMU-

    NITION WITH EXPLOSIVE PRO-JECTILES UN 0181

    WARNING

    When firing rockets with the M229 warheadand MK66 Motor from the A/MH6 and U/MH60 Aircraft, limit engagement of targetsand ensure line of fire is clear of obstructions ata minimum distance of 450 feet if forward air-speed exceeds 10 knots or 350 feet if forwardairspeed is less than 10 knots.

    NOTE

    Rocket, HE, 2.75-Inch with warhead M229 andMotor MK66 is airworthiness certified for theA/MH6 and U/MH60 Aircraft only, and willnot be issued to units that do not use these air-craft.

    REFERENCES:

    TM 9-1340-222-20TM 9-1340-222-34SC 1340/98-IL

    *See appropriate supply catalog for individual NSN’s per-taining to this (these) DODAC(s).

    DOT labels.......................................... EXPLOSIVE 1.1EField storage........................................ Group F*DODAC ............................................ 1340-H469, 1340-

    H488, 1340-H533, 1340-H534, 1340-H160, 1340-H162, 1340-HA09

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    ROCKET, SMOKE, WP, 2.75 -INCH W/M156 WARHEAD

    Type Classification:

    STD AMCTCM 10756032

    Use:

    Primarily to provide smoke for targetmarking and incendiary purposes.

    .Description:

    a . This warhead is a ballistic matchfor high explosive (HE ) Warhead M151. TheM156 consists of a steel body, a base, andan adapter, brazed together. The body isshaped at the forward end to form the ogive.The base is an extruded steel cup threadedfor attachment to the rocket motor. Thesteel adapter, at the forward end of thewarhead, is threaded to receive the fuze.It also serves to retain the burster chargetube.

    b. The fuzes assembled in this 2.75-in. rocket are classified as point detonating(PD), or proximity, according to the man-ner in which they are initiated. Except forthe Proximity Fuze M429, these fuzes arenondelay and super-quick. The pointdetonating fuzes and proximity fuze arethreaded into the forward end of the warhead.

    c . The WP M156 warhead is availablewith fuzes M423, M427, and M429. Thesefuzes differ from each other functionallyand have the following characteristics:

    M423) Oblique impact sensitive,M427) point-detonating, super-quick

    type fuze.

    M429 Transistorized Doppler typeproximity fuze with a super-quick impact switch as abackup.

    3 - 1 5

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    d. The LSFFAR 2.75-in. rocket motorsare fin stabilized and have scarfed nozzles.The scarfed nozzles give low spin to therocket and provide the additional stabilityrequired for deployment from low speedaircraft.

    e. The rocket motor is described inChapter 5.

    Differences between Models:

    The table below describes the differencesbetween the WP smoke M156 warhead incor-porated within the approved configurationsof motor and fuze.

    Functioning:

    a . I g n i t i o n . Functioning of the 2.75-in.rocket with an M156 warhead begins whenthe firing circuit switch is closed. Currentpasses through the launcher firing contactto the igniter in the rocket motor. Thiscurrent generates the heat necessary toinitiate the igniter charge, which ignitesthe propellant grain. Combustion gasesfrom the burning propellant pressurize thechamber and exhaust through the nozzle,providing the unequal forces required forrocket thrust.

    b . Fin Operation. The thrust of thenozzle exhaust blows off the fin retainerand releases the fins. Upon clearing thelauncher, the fins are opened by the force

    DODAC Warhead

    Smoke WP M1561340-H4721340-H5191340-H4861340-H593

    of the fin actuating piston pushing onthe heels of the fins.

    c . Fuze Functioning.

    (1) A typical point detonating (PD)fuze (M423 and M427) arms under minimum,sustained acceleration. On impact with thetarget, the nose of the fuze is crushed andthe firing pin strikes the primer, initiatingthe explosive train.

    (2) The M429 proximity fuze is acompletely transistoriz