?_ÔÿÿÿÿY-Ä»l»d©4Hellfire Missileþ è( @€€€€{€€€€€{€€€{ÀÀÀÿÿÿÿÿÿÿÿÿ.ÿÿÿîîîîîîîîîîîîîîîîîîîîîîîîîîîîîîîîîîîîîîîîîàîîîîîîîîîîîîîîîîîîîîîîîîîî`îîîîîîîîîîîà`îîîîîîîîîîf`îîîîîîîîîîf`îîîîîîîîîàf`fîîîîîîîîîàf`îîîîîîîîàf`fîîîîîîîîîffîîîîîîîîàf`f`îîîîîîîîfffîîîîîîîîàfff`îîîîîîîîîfffîîîîîîîîîàfff`îîîîîîîîîàfffîîîîîîîîîfff`îîîîîîîîîàfffîîîîîîîîîàff`îîîîîîîîîîîf`f`îîîîîîîîîîàfffîîîîîîîîîîf`f`îîîîîîîîîàfffîîîîîîîîîàfff`îîîîîîîîîàff`îîîîîîîîîîàÀffîîîîîîîîîîî Àf`îîîîîîîîîîîî Ìîîîîîîîîîîîîàîîîîîîîîîîîîîîîîîîîîîîîîîîîîî'PositionWindow(0,0,1024,1024,1,"MAIN")BrowseButtons()MCreateButton("Firemode-id","&Modes","JumpId(`HELLFIRE.HLP',`Firing_Modes')")LCreateButton("Specs-id","&Specs","JumpId(`HELLFIRE.HLP',`Specifications')")ICreateButton("TYPE-id","&Type","JumpId(`HELLFIRE.HLP',`Missile_Types')")Zƒmain?mainR;:Ÿ‚Oz0WGä ô”OŸm##ÊO,‡lGŒŸŸŸ&/&;)z4þAþÿÿ)U)ÿÿÿÿ|CONTEXTC¹|CTXOMAP§|FONTž|KWBTREEåš|KWDATA§|KWMAPÔš|SYSTEM|TOPIC |TTLBTREE±|bm0rÁ|bm1ú…|bm10ÎÞ|bm11jL|bm12ö|bm13R|bm14ìÿ|bm15͚|bm16š |bm17… |bm18Æp |bm19eÐ |bm27Ò|bm20e |bm21çä |bm22ÅÕ |bm232|bm24>©|bm25Â/|bm26ŽÅ|bm27y|bm28Oà|bm29C|bm3ø5|bm30[|bm31ž|bm4o|bm5(|bm6ǹ|bm7jï|bm8"'|bm9܈Ä_^DROP_REJ.WMFKõÿÿ_^Íd$d$ƒ=ˆÆúu!èÂûÿÿ ÀtžÍd$d$LjÆú‹D$f8CKtóÀ€WÀè’ÅŸíúÀ íúÀóÀ€WÀè’Å”îúÀ‹ÍÀžîúÀ¡íúÀóÀ€WÀè’ÅC:\ROBOHELP\HELLFIRE\WMF\DROP_REJ.WMF*.XL?-# Rÿÿ*ñŸÐÿÿÿÿìëŸ €óÀ€WÀè’ÅÈïúÀ2ÀDîúÀóÀ€WÀè’ŹîúÀDROP_REJ.WMFGþÿÿƒÄ Àu ‹D$PèæþóÀ€WÀè’Å%ïúÀ÷ÃÀ¬* ÁóÀóÀ€WÀè’Å4ïúÀ4À÷ÃÁóÀ€WÀè’Å(Í* ÁTïúÀÑ À¬* ÁýÃÁ• •ÿÿÿÿ AÿÿÿÿM1ê  €ÿÿÿÿMö Hellfire Missile8 …% €&€Œ˜€‚ÿHellfire Missile©^M.K d€ñ€€†"€4‚‚‚ãÇp°€‰€‚‚‚âï߀‰€‚ÿSYSTEM OBJECTIVESThe HELLFIRE Missile system was designed to fill the need for a high-velocity, low visibility standoff weapon. Hellfire exceeds the requisites of this need with a supersonic missile possessing extreme accuracy and a high probability of target destruction. GENERAL MISSILE DESCRIPTIONThe Army's AH-64, Navy's AH-60 and Marine AH-1W attack helicopters serve as the current airborne launch platforms for the Hellfire missile. The laser seeker is a semi-active laser terminal homing device that provides accurate fire on targets. Target designation is accomplished by ground-based designators and from the air by scout helicopters as well as the attack helicopter itself. The AH-64 can carry 16 Hellfire while the Navy's AG-60 and AH-1W can carry a maximum of 8. A Swedish antiship variant exist that is launched from a tripod.{J…©1 0€•€€‚ãòÚ"€‰€‚ÿHELLFIRE missiles can be launched in an indirect firing mode allowing the helicopter to remain concealed from the target and air defense weapons. Designators using different laser codes can illuminate separate targets to guide the missiles before or after launch from behind a terrain mask even if one target has not been visually detected by the helicopter. This tactic improves the helicopter's survivability and offers the element of surprise. Indirect fire requires remote designation from any one of the family of air and ground-based front line laser designation systems.Mº.ö “ ô€u€€‚ãÂXPs€‰€‚‚ãÑ»7€‰€ã²3€‰€ãPÆ€‰€ã k*ò€‰€ãÇp°€‰€ãI (d€‰€ã™NÙŀ‰€ãŒ×?€‰€‚ÿThe HELLFIRE missile's long range, high velocity, and pinpoint accuracy enable the AH-1W to destroy enemy armor and other point targets from beyond the range of air defense systems. The missile's built-in trajectory shaping features and ballistic/glide mode options increase the impact angle of the missile to the target, thereby increasing penetration of heavy armor by placing the missile over the thinner top plate armor.The HELLFIRE missile is composed of four (4) major sections or assemblies. It is packaged in two separable units: the laser seeker section which houses the seeker head and electronics assemblies; and the missile bus which includes the warhead, guidance, propulsion, and control sections. It's design features four (4) fixed strakes at the aft end of the seeker section to provide aerodynamic instability. Three (3) launch shoes are located along the top of the body for missile carriage.A©7 1Xÿÿÿÿÿÿÿÿ7 ZAAuthor / Version8ö o % €&€Œ˜€‚ÿAuthor / Version Ê7 x ? L€•€€‚‚‚ƒƒ‚ƒ‚ƒƒ‚ƒƒ‚‚ƒƒ‚ƒƒ‚ƒƒ‚‚ƒƒ‚ÿ***************************************************************************************** UNCLASSIFIED*****************************************************************************************Author:Lee Standley, Fleet Weapons Support Team (FWST) rep.Address:MALS 39 OrdBox 55761Camp Pendleton, CA 92055-5761Phone:DSN 365-3509Comm (760)725-3509FAX (760)725-3509Email:LeeStandley@msn.com4üo ¬8 >€ù€€‚ƒ‚ƒƒ‚ƒ‚‚‚‚‚‚‚ƒ‚ƒ‚ƒƒ‚ÿVersion: 1.6Date 30 Dec 97First issued:26 Sept 97All NavAir manual information has authority when it conflicts with this training aid.This help file is a hypertext document containing 36 graphics and 13,000 words.Some text pirated from another Hellfire help file by Klaus Tomczyk, an Army rep.Pulications:Army unit / intermediate maintenance captive/dummy:TM 9-6920-475-23PNavy AGM-114B/K & Captive/Dummy I/O maint:AW-820YB-MIB-000Navy AGM-114B/K & Captive/Dummy Depot:AW-820YB-MIB-100¢mx ZA5 8€Û€€ƒƒƒƒƒ‚ƒƒƒ‚ƒƒƒƒ‚‚‚‚ÿAH-1W tactics manual:NWP ¬ZAö 3-22.5-AH1AH-1W O-level maintenance:NAVAIR 01-H1AAC-2-12AH-1W Loading:NAVAIR 01-H1AAC-75***************************************************************************************** UNCLASSIFIED*****************************************************************************************?¬™A1X RŠÿÿÿÿ™A²NSpecifications6ZAÏA% €"€Œ˜€‚ÿSpecificationsµ™AáC] ˆ€k€€‚€€‚ƒƒƒ‚ƒƒƒ‚ƒƒ‚ƒƒ‚ƒƒƒ‚ƒƒ‚ƒ‚ƒ‚ƒƒ‚ƒƒƒ‚ƒ‚ƒ‚ƒƒƒƒ‚ƒƒƒƒ‚ƒƒƒ‚ÿAll Up Round (AUR)Weight:100 lb. (A,B,C,K), 107 lb.(F)Length:64 inchesDiameter7 inchesWing span13 inchesRange:8000 mt.Guidance:Semi-active homing laserCenter of gravity34.5 in form noseNet explosive weight:34.13 lbMission:AntiarmorCost:$43,000Launch platforms:AH-64, AH-1, AH-60Launch azimuth:LOBL +/- 20 deg >=1000 mt.LOAL 400 mt wide @ 2000 mt.3200 mt. wide @ 8000 mtMTBF286 (K)¹ÏAçEM h€s€€ƒƒ‚ƒƒ‚ƒƒƒ‚ƒƒƒ‚€€‚ƒƒ‚ƒƒ‚ƒƒ‚ƒƒƒ‚ƒƒƒ‚ƒƒƒ‚ÿAir launcherM272 (Marines), M299 (Navy/Army)Manufacturer:Developer/1st contract - Rockwell Int.2nd contract - Martin Marietta3rd contract - Martin Marietta + Rockwell Int. became Boeing AircraftStorageTemperature:-49 deg F to +160 deg FTemp/altitude:up to 40,00 ftHumidity:5% - 100% @ 70 deg. F to 160 deg. FSand:Up to 1.0 mm particles at 50 ft/sDust:6 x 10 (-6) kg/m (3) at 60 ft/sRain:up to 27 in/hrváC÷Gš í€€ƒ‚ƒƒƒ‚‚‚ƒƒ‚ƒƒ‚‚ãâ‚Ñ€‰€‚ãïâI€‰€ƒƒƒ‚ãÜ0L"€‰€‚⌜Ž÷€‰€‚âÖB܀‰€‚ãì•[€‰€‚‚ãÑ»7€‰€‚ƒƒ‚ƒƒ‚ƒƒ‚ÿTemperature shock-49 deg F to +160 deg FShock100 g - 10 msOperatingTemperature-45 deg F to +149 deg FLaunch shock40 gLaunch rangeDrop Rejection CriteriaCookoff Safe SeperationTime lineDelay designation timeDesignator zones footprintSeekerSpin rate:4200 rpmCode type:PRF (A,B,C,F,K), PIM (K)PRF rate:10 - 20 HzµçEJY €€k€€ƒ‚ƒƒ‚‚ãPÆ€‰€‚ƒ‚ƒ‚ƒƒ‚ƒƒ‚ƒƒ‚ƒƒ‚ƒƒ‚ƒƒ‚ƒƒ‚ƒƒƒ‚ƒƒ‚ƒƒ‚ÿDetector wavelength:1.064 micrometerGimbal limits:30 deg.WarheadTotal main charge weight24 lb.Explosive weight A,B,C & F13.6 lb.Explosive weight K12.5 lb.Explosive materialLX-14Fast cookoff time:1 minuteSlow cookoff temp.:358 degrees FCookoff withdrawal1,200 ftBooster materialPBXN-5Cone liner materialsilver bearing copperCone weight1 lb.Arming distance150-300 mtArming acceleration10 g's÷GL‚ Ҁ€€ƒƒ‚€‚ã+fy€‰€‚ƒƒ‚ƒƒƒ‚ƒƒ‚ƒƒ‚‚‚ã k*ò€‰€ã¥[…É€‰€‚ƒƒ‚ƒƒƒ‚ƒƒ‚ƒƒƒ‚ƒƒƒ‚‚ãÇp°€‰€‚ƒƒ‚ÿFocused pressure5 million psiPre-cursor Explosive weight:2.25 lb.Explosive type:LX-14Fast cookoff time:1 minuteSlow cookoff temp.:358 degrees FGuidance / ControlAccumulator pressure:8000 psiRegulated to:600 psiGyro accumulator pres.3000 psiGyro spin rate:40,000 - 20,000 rpmRoll stabilized:+/- 10 degPropulsionPropellant weight:20.5 lb.3ÖJIN] ˆ€­€€ƒƒƒ‚ƒƒƒ‚ƒƒƒ‚ƒƒƒ‚ƒ‚ƒƒƒƒ‚ƒƒƒãSV6€‰€‚ƒƒ‚ƒƒ‚ƒƒƒ‚ƒƒ‚ƒƒ‚ƒƒ‚ÿMax. velocity:475 m/sec (mach 1.4)Min. velocity:400 ft/secSquib qty.2Burn time:2 - 3 secondsTime of flight @ 70 deg F13 sec @ 3000 mt; 20 sec @ 5000 mt.; 38 sec @ 8000 mtStages:SingleMax. altitude17,000 ftReduced smoke:AGM-114A (visible)Minimum smoke:AGM-114B, C, F, K, IIR, MMWS&A used in:AGM-114B & KFast cookoff time:1 minuteCookoff withdrawal1,200 ftTemp @ nozzle centerline:2000 deg K @ 3.7mt1000 deg K @ 6.6 mtiCL²N& €†€€ƒƒ‚‚ÿPressure @ nozzle centerline:1000K.Pa @ 1 mt150 K.Pa @ 3.6 mt9INëN1h€‡ÿÿÿÿëN&Failures0 ²NO% €€Œ˜€‚ÿFailures}ëN+€‡ ހú€âwR¬i€‰€‚â*E@#€‰€‚â^Á“.€‰€‚âXý3Š€‰€‚âXþ0€‰€‚â“ L€Ž€€‚‚ãóÁↀ‰€‚ãÑ»7€‰€‚ÿRelated topics:RIPPLE modeLast significant pulse tracking@冪‡1¶‡ÿÿÿÿª‡ ‰Beam divergence7j‡á‡% €$€Œ˜€‚ÿBeam divergence?ª‡ ‰0 .€€€âXý3Š€‰€‚ÿThe farther the laser designator is from the target, the wider the spot will be upon the target. The amount of beam divergence will vary between types of designators. A .2 -.25 mr beam divergence is common. A large spot will increase over/underspill conditions.< á‡\‰1!ážÿÿÿÿ\‰A‹Attenuation3 ‰‰% €€Œ˜€‚ÿAttenuation²Ž\‰A‹$ €€€‚ÿAttenuation is a portion of the laser beam energy that is "scattered" by obscurants along the laser-to-target LOS and missile-to-target LOS resulting in a reduced target signature to the seeker. If the attenuation is severe, the seeker will not detect the laser energy from the target. One source of attenuation is the missiles own smoke. The launch aircraft should slide out of launch smoke.A‰‚‹1Ëß ÿÿÿÿ‚‹ Boresight errors8A‹º‹% €&€Œ˜€‚ÿBoresight errorsR.‚‹ $ €]€€‚ÿDesignator sight to laser alignment could be incorrect but undetectable. If a laser range finder is integrated into the laser designator a rough alignment check can be accomplished by ranging a small target with distant surroundings and ensure the range increases as the sight moves off the object.: º‹F1"ž€ÿÿÿÿF:ÀOverspill1 w% €€Œ˜€‚ÿOverspill·‘F:À& €#€€‚‚‚ÿCaused by placing the laser spot too high on the target so that beam divergence and jitter cause the spot or a portion of the spot to spill over onto the object of the terrain behind the target. This can cause intermittent background false targets, becoming more severe at longer designation ranges. If given a choice of underspill or overspill, underspill is preferred since Hellfire tracks the last significant pulse. Spot jitter is one sourse of overspill.Even a small number of over/underspilled laser pulses can cause the missile to follow false signals. If this occures just before missile impact, w:À the probability of hit is seriously degrade.; wuÀ1Ðß J‚ ÿÿÿÿuÀ ÃUnderspill2 :À§À% €€Œ˜€‚ÿUnderspillc=uÀ Ã& €{€€‚‚‚ÿCaused by placing the laser spot too low on the target so that the spot or a portion of the spot spills onto the foreground. This can cause foreground false targets, becoming more severe at long designation ranges. If given a choice of underspill or overspill, underspill is preferred since Hellfire tracks the last significant pulse. Spot jitter is one sourse of underspill.Even a small number of over/underspilled laser pulses can cause the msisile to follwofaulse signals. If this occures just before missile impact, the probability of hit is seriously degrade.9§ÀCÃ1€€H„ ÿÿÿÿCÊÅHangfire0 ÃsÃ% €€Œ˜€‚ÿHangfireóCÊÅ$ €ç€€‚ÿHangfire is traditionally a condition where the missile propulsion or cad fired but was mechanically restrained to the aircraft. a slightly different definition is given to a hangfire by Hellfire. After issuing the launch command to the missile the missile present signal should go away at missile separation. If the missile present signal remains a Hangfire will be signaled. A down range loiter time of one hour is required after a hangfire. EOD should be advise of the hangfire condition.?sÃÉÅ1ÄJ‚|„ ÿÿÿÿÉÅNÆDrop Rejection6ŠÅÿÅ% €"€Œ˜€‚ÿDrop RejectionO"ÉÅNÆ- *€F€€†"€‚‚ÿIn Hellfire container CNU-448HÿŖÆ1<H„… ÿÿÿÿ–ÆŠÇCookoff Safe Separation?NÆÕÆ% €4€Œ˜€‚ÿCookoff Safe Separationµ…–ÆŠÇ0 .€ €€†"€‚‚‚‚ÿFast cookoff time for both warheads and the propulsion section is 60 secondsSlow cookoff temp. for both warheads is 358 deg. FBÕÆÌÇ1ý|„Ž† ÿÿÿÿÌLJÉMissile Fail (MF)9ŠÇÈ% €(€Œ˜€‚ÿMissile Fail (MF)‚^ÌLJÉ$ €œ€€‚ÿIf the missile does not return a valid code signal to the aircraft or the seeker fails to spin up within 30 seconds an MF indication will be displayed on the Hellfire control panel. Spin up time is nomally well within the 30 seconds but extreme cold weather can cause a sluggish spin rate. The AGM-114K and newer seekers have improved cold spin.: ÈÁÉ1¹ …ÿÿÿÿÁÉûTime Line1 ‡ÉòÉ% €€Œ˜€‚ÿTime Line)ØÁÉÌQ p€±€€‚‚ƒƒƒ‚ƒƒƒƒ‚ƒƒƒƒ‚ƒƒƒƒƒ‚ƒƒƒƒƒ‚ƒƒƒƒƒ‚ƒƒƒƒƒ‚ƒƒƒƒƒ‚ÿTime 0 = triggerSignal/EventTime onTime offPrimary power@coding1.04Main power input from A/CStare cmd@LOAL select0.96Indicates LOAL selected, skr @ 0,0Indirect low00.96If LOBL selectedIndirect low 0.160.96Indirect lo @ .16 + Stare = LOAL DirectIndirect low00.96Indirect lo @ t0 + Stare = LOAL LowIndirect low0.160.96Indirect lo @.16 + hi @ 0 + Stare = LOAL HighIndirect high00.16Indirect lo @.16 + hi @ 0 + Stare = LOAL High4ØòÉOÎ\ †€±€€€ƒƒƒƒƒƒ‚ƒƒƒƒƒ‚ƒƒƒƒƒ‚ƒƒƒƒƒ‚ƒƒƒƒƒ‚ƒƒƒƒƒ‚ƒƒƒƒ€€‚ƒƒƒƒƒ‚ÿ+18vdc01.00Power from launcherSquib arm0.121.24Enables squib ignitionMsl Squib 1&20.160.22Lights off thermal battery, gyro & accumulator Pitch slave0.161.00Transfers A/C pitch attitude while in LOALDeice squib fire0.240.30Signals to blow dome covers in LOALLaunch cmd0.68>1.24Seeker launch preparationExt pwr removed1.001.00+28vdc 7 +18vdc from launcher removedBattery check1.001.04Check for thermal battery power or MF2Î̍d –€€€ƒƒƒƒƒ‚€€ƒƒƒƒ‚ƒƒƒƒ‚ƒƒƒ‚‚€€‚ƒƒƒƒ‚ƒƒƒƒ‚ƒƒƒƒƒ‚‚€€ƒ‚ƒƒƒƒƒ‚ÿMotor squib1.041.10Propulsion ignitionFirst launch motion1.061.07Umbilical separationMissile present@load-up1.07If not separated by 1.24 hangfire declaredMissile clear rail1.181.2LOAL DirDir 1.25 deg climb1.197lockLOAL DirHangfire declared1.240If missile separation has not occurredDir scan1.57O΍‡É2lockLOAL Dir box scan at 4.25 deg below horizonLOAL LoLo 6 deg climb1.1971.572LOAL Lo laser unlock climb begins2ÚOοX ~€µ€€ƒƒƒƒ‚ƒƒƒƒ‚ƒƒƒƒ‚ƒƒƒƒƒƒ‚ƒƒƒƒ‚ƒƒƒƒƒƒ‚‚€€‚ƒƒƒƒƒ‚ƒƒƒƒ‚ÿHangfire declared1.240If missile separation has not occurredLo 15 deg climb1.5723.065LOAL LoLo Seeker slaved2.0653.315LOAL Lo skr set to -20 pitch, +10 yawLo scan2.7lockLOAL Lo box scan at -9.75 deg AGM-114KLo 1.25 deg climb3.065lockLOAL LoLo scan3.315lockLOAL Lo box scan at 9.75 deg AGM-114B/C/FLOAL HiHi 6 deg climb1.1971.572LOAL Hi laser unlock climb beginsHangfire declared1.240If missile separation has not occurred ¹ÈP n€s€€ƒƒƒƒƒ‚ƒƒƒƒ‚ƒƒƒƒƒƒ‚ƒƒƒƒ‚ƒƒƒƒƒƒ‚‚ƒƒƒƒ‚ƒƒƒƒƒ‚ƒƒ‚ÿHi 15 deg climb1.5725.225LOAL Hi Hi Seeker slaved2.0655.465LOAL Hi skr set to -20 pitch, +10 yawHi scan4.6lockLOAL Hi box scan at 11.75 deg AGM-114KHi 1.25 deg climb5.225lockLOAL HiHi scan5.465lockLOAL Hi box scan at -11.75 deg AGM-114B/C/FSkr acquires targetTrigger+impactCan occur anytime seeker locks onStarts trackingTrigger+impact starting at trigger pull.Pitch program stopsTrigger+impact3ú¿û9 @€õ€€ƒƒ‚‚ƒƒƒƒƒ‚ƒƒƒƒƒƒ‚‚‚‚‚‚ÿSlaving/scanning stopTrigger+impactGuidance loop closed+.6impactThese events start .6 seconds afterG-bias & body previous event.attitude regulatoroutputs applied.Missile starts track to target A/P slaving and scanning cmd off.= È81) Ž†€ÿÿÿÿ80@Firing Modes4ûl% €€Œ˜€‚ÿFiring Modesr48Þ> J€q€€†"€‚‚‚ãÏ} €‚‚‚ÿFire ModesThe HELLFIRE missile possesses the ability to be launched using a variety of firing techniques. It can utilize both remote (air or ground) and autonomous designation systems.For example, the missile has the capability of being launched in the direct (Lock-On After Launch-LOAL) fire mode, where the initial target heading is established by an auxiliary pointing unit or by momentarily designating the target. The missile is then launched without seeker lock-on. Lock-On occurs automatically in flight whenever the target is designated again.>ÿl ? L€ÿ€€‚‚‚ãòÚ"€‰€ãâ‚Ñ€‰€‚ÿThe above figure gives maximum altitude for LOAL trajectories prior to lock-on. The missile altitude will increase after lock-on if there is sufficient range to target. LOBL altitude increases with longer range.Lock On After Launch (LOAL) - HIGH enables the missile to be launch from behind masking terrain. This mode has the longest minimum and maximum range. This mode is known as in indirect fire mode because the launch platform does not have to have a direct line of sight to the target.ö€ÞR r€I€ãòÚ"€‰€ãâ‚Ñ€‰€‚ãòÚ"€‰€ãâ‚Ñ€‰€‚ÿLock On After Launch (LOAL) - LOW enables the missile to be launch from behind shorter masking terrain. This mode has the same maximum range as LOAL HIGH. This mode is known as indirect fire mode because the launch platform does not have to have a direct line of sight to the target.Lock On After Launch (LOAL) - DIRECT permits use of delayed designation and allows employment of the weapon under a cloud ceiling. Direct puts the missile into a 5 degree climb until laser lock at which time it lofts if sufficient range exist. This mode is known as a direct fire mode because the launch platform must have to have a direct line of sight to the target.Ÿ 0@T v€}€ãu_6€‰€ãâ‚Ñ€‰€‚‚ãŸiM±€‰€‚ãóÁↀ‰€‚ÿLock On Before Launch (LOBL) This mode is known as a direct fire mode because the launch platform must have to have a direct line of sight to the target in order for the missile to see the reflected laser energy. The missile will not launch without a lock-on. This mode permits the shortest range to target engagement.Rapid fire used when only one designator is availableRipple fire used 0@ûwhen two designators are availableL|@1^/‡ÿÿÿÿ|@ŽHLock On After Launch (LOAL)C0@¿@% €<€Œ˜€‚ÿLock On After Launch (LOAL)Õ£|@”C2 2€I€€‡"€‚‚‚‚‚‚ÿAGM-114 Instantaneous FOVWhile loaded on the aircraft, Lock On After Launch (LOAL) doesn't scan for targets but passively stares straight ahead and will lock onto a properly coded target reflection if it falls within it's 8 degree field of view unless it is an AGM-114K. The AGM-114K inhibits laser lock until after launch for LOAL-Lo/Hi. The three altitude based trajectories allow for various range to target and cloud ceilings.Since the instantaneous FOV is closer to a square that a circle if is misleading to flatly state that the FOV is 8 degrees. Actually it is closer to 7 degrees at it's narrowest point and 13 degree diagonally or 8 deg by 8 deg square.T¿@èF? L€/€€‚‡"€‚‚‚‚‚‡"€‚‚‚‚ÿLOAL Post-launch Search Area (top view)After launch hellfire begins to scan for reflected laser energy. This capability allows target designation to be delayed until the missile is close to the target, or to operate in low visibility conditions which shorten the seeker's lock-on range.LOAL Effective Look Down Angles (side view)After the initial pull-up maneuver the missile pitches down to 1.25 degree nose-up attitude. The actual missile look down angles are -5.5 degree, Dir; -11 degree, Lo; -13 degree, Hi. Since the missile is nosed up 1.25 degree the effective look down angle is shallower as the figure indicates. The AGM-114K scan depression angle gradually increases with time in flight. AGM-114A maintains a 4 degree nose-up attitude instead of 1.25 degree.ŠV”CŽHP n€­€€‚‚‚‚‚‚ãâ‚Ñ€‰€‚ãì•[€‰€‚ãu_6€‰€‚ÿA LOAL-Lo mask may not be higher than 260 feet. To clear the 260 foot mask, the minimum standoff distance from the mask is 600 meters.A LOAL-Hi mask may not be higher than 1000 feet. To clear the 1000 foot mask, the minimum standoff distance from the mask is 1500 meters.Related topics:Missile RangeLOAL FootprintLOBLMèFÛH1×€،ÿÿÿÿÛHeOLock On Before Launch (LOBL)DŽHI% €>€Œ˜€‚ÿLock On Before Launch (LOBL)ÐÛH-K> J€¥€€‡"€‚‚‚‚‚‡"€‚‚‚‚ÿLOBL Prelaunch Search AreaWhile in a LOBL mode, a coded missile will scan the area and lock-on to properly coded laser reflections prior to launch. The scan angles are 12 degrees high by 6 degrees wide. Aircraft pitch attitude is monitored in order to maintain optimum Hellfire's scan angles.Instantaneous FOVWhen the 8 degree instantaneous seeker field of view (FOV) is added to the scan pattern the total coverage area is 20 degrees by 14 degrees.ΛIûM3 4€9€€‚‡"€‚‚‚‚‚‚ÿLOBL Multiple Missile Search AreasWith multiple missiles loaded, LOBL scan patterns are divided up to cover a wider area in less time. If one of the missiles locks onto a target the other like coded missiles will begin to scan the same sector that the tracking missile was scanning.If LOAL-Dir/Lo/Hi is selected and properly coded laser energy is received prior to launch then the AGM-114A/B/C/F missile will default to LOBL and the launcher display will change to a LOBL constraints. The AGM-114K will only default to LOBL from the LOAL-Dir autonomous mode. In all other modes the laser energy is locked out until approximately 1.5 seconds after launch.j-KeON j€9€€‚‚‚‚ãâ‚Ñ€‰€‚ãòÚ"€‰€‚ãŸÍˆ“€‰€‚ÿA LOBL scan time limit of 30 minutes exist for continuous search operations at temperatures above 90 degrees F. After 30 minutes the missile must be deselected or placed in the LOAL mode to allow the seekers to cool.Related topics:Missile RangeLOALLOBL Footprint> ûM£O1†/‡Gÿÿÿÿ£OςMissile Range5eOØO% € €Œ˜€‚ÿMissile Range€P£Od‚0 .€§€€†"€ØOd‚eO ‚‚‚‚ÿRanges are based on a 0 degree azimuth off-set. A 20 degree off-set is allowed in LOBL and 7.5 degree in LOAL but maximum ranges are shortened and minimum ranges are longer. The maximum range of a particular launch may be limited by the distance the designator is from the target. Engaging a target at 8000 meters would require a remote designator to be placed much closer. The missiles electronics have enough in flight longevity to permit engagement of targets beyond 8000 meters but the slow terminal velocity of the missile makes the missile body difficult to guide accurately.kGØOς$ €Ž€€‚‚ÿThe AGM-114K maximizes range by minimizing flight path transients.; d‚ ƒ1ù،…ÿÿÿÿ ƒȆRapid fire2 ς<ƒ% €€Œ˜€‚ÿRapid fireŽ ƒð…5 8€€€†"€ ‚‚‚‚‚‚‚‚‚ÿRapid fire is a firing mode selected on the TOW / Hellfire Control Panel (THCDP) that launches a missile with the same laser code at each push of the fire button. Missiles fired in rapid must have an 8 second interval between them in order to allow the designator adequate time to change targets without loosing the missile.Potential problems:Ensure that both targets are in the same FOV to ensure sufficient time to move spot.Walk laser from target to target without turning laser off. Hellfire doesn't reenter the scan mode after lose of laser spot but stares at last LOS. Second target could be outside first targets FOV.ر<ƒȆ' €c€€‚‚‚‚ÿEnsure second target isn't down wind from first target to prevent explosion dust obscuring second target.Engage closer target first to prevent overflight of second target.< ð…‡1rG`ÿÿÿÿ‡:‰Ripple Fire3Ȇ7‡% €€Œ˜€‚ÿRipple Firė:‰7 <€›€€†"€ ‚‚‚‚‚ƒ‚ƒ‚ƒ‚ÿRIPPLE toggles the code automatically each time the trigger is pressed. The is the same as pressing the PRI / ALT button after each missile firing in the RAPID mode. Potential problems:-Missiles fire in ripple must have a minimum of 2 seconds between them to prevent laser obscurant and backscatter from the first missiles smoke trail.-Ripple must not be used in conjunction with the AUTO mode on the Laser Code Panel (LCP). -Verify both codes> 7‡x‰1£…}ÿÿÿÿx‰݉Missile Types5:‰­‰% € €Œ˜€‚ÿMissile Types0x‰݉, (€€€†"€ ‚ÿ9­‰Š1ž`›ÿÿÿÿŠ•ŒAGM-114A0 ݉FŠ% €€Œ˜€‚ÿAGM-114AOŠ•Œ< F€'€€ƒ‚ƒƒ‚ƒƒ‚ƒ‚ƒ‚ƒ‚ƒ‚ƒ‚ƒ‚ƒƒ‚‚‚ÿHoming:Semi-active laserWeight:100 lb.Length:64"Diameter:7"Wing span:13"Propulsion:Low smoke motorWarhead qty.1Circuitry:AnalogService date:1985DODIC:PA79First in the family of Hellfiie missiles the A model is almost completely expended. Remaining quantities have been sold to foreign governments. The A's trajectories were slightly higher than following versions, but is still compatible with all launch platforms. The -114A low smoke motor (a.k.a. reduced smoke motor) leaves a visible smoke trail.9FŠΌ1o}€ÿÿÿÿΌÀAGM-114B0 •ŒþŒ% €€Œ˜€‚ÿAGM-114BÅΌÀA P€‹€€ƒ‚ƒƒ‚ƒƒ‚ƒ‚ƒ‚ƒ‚ƒ‚ƒ‚ƒ‚ƒƒ‚ƒƒ‚ƒ‚‚‚ÿHoming:Semi-active laserWeight:100 lb.Length:64"Diameter:7"Wing span:13"Propulsion:Minimum smoke motorWarhead qty.1Circuitry:AnalogService date:1986P/N:13007357NALCPC91UN Serial #:0181This missile has an improved low visibility propulsion section and flies lower trajectories than the AGM-114A. AGM-114B is the same as the AGM-114C except it has an safe arming device (SAD) in the propulsion firing chain. This SAD is a mechanical interrupt in the rocket motor firing chain which requires thermal battery power before arming. The minimum smoke motor leaves no visible smoke trail and has a shorter burn time. Maintenance due date of depot has been extended to indefinitelþŒÀ•Œy.9þŒIÀ1æ›NÿÿÿÿIÀöÁAGM-114C0 ÀyÀ% €€Œ˜€‚ÿAGM-114C}CIÀöÁ: B€‡€€ƒ‚ƒƒ‚ƒƒ‚ƒ‚ƒ‚ƒ‚ƒ‚ƒ‚ƒƒ‚‚‚ÿHoming:Semi-active laserWeight:100 lbLength:64"Diameter:7"Wing span:13"Propulsion:Minimum smoke motorWarhead qty.1Circuitry:AnalogDODIC:PD68This missile is the same as the AGM-114B but does not have the S&A in the propulsion squib circuit. The minimum smoke motor leaves no visible smoke trail...9yÀ/Â1—€Kƒÿÿÿÿ/ÄAGM-114F0 öÁ_Â% €€Œ˜€‚ÿAGM-114F.ò/Ä< F€å€€ƒ‚ƒƒ‚ƒƒ‚ƒ‚ƒ‚ƒ‚ƒ‚ƒ‚ƒ‚ƒƒ‚‚‚ÿHoming:Semi-active laserWeight:107 lbLength:71"Diameter:7"Wing span:13"Propulsion:Minimum smoke motorWarhead qty.1Circuitry:AnalogService date:1991DODIC:PV29The F is a stretched AGM-114C with a pre-cursor warhead installed between the seeker and main warhead. The extra warhead improves performance against reactive armor. This additional warhead makes the -114F seven inches longer that all other laser seeker models. It requires an extra long container for shipping.9_ÂÆÄ1œ NŒÿÿÿÿÆÄJÎAGM-114K0 ÄöÄ% €€Œ˜€‚ÿAGM-114K”GÆÄŠÈM h€€€ƒ‚ƒƒ‚ƒƒ‚ƒ‚ƒ‚ƒ‚ƒ‚ƒ‚ƒ‚ƒƒ‚ƒƒ‚ƒ‚‚ã+fy€‰€‚ÿHoming:Semi-active laserWeight:100 lbLength:64"Diameter:7"Wing span:13"Propulsion:Minimum smoke motorWarhead qty.2Circuitry:DigitalService date:1996P/N:13415100NALC:PV30UN Serial #:0181AGM-114K is the latest laser guided Hellfire. It's length is the same as the original Hellfire. This missile features dual warheads with an electronic-safe-arm-fuze (ESAF) for defeating reactive armor, electro-optical coutermeasures hardening, and an externally programmable guidance section for trajectory shaping-seeker logic changes. This missile has lower altitude trajectories than any of the previous models. The missile contains both Pulse Rate Frequency (PRF) and Alternate A-Code capability. Previous model's analog circuits were compressed and digitized in order to make room for the pre-cursor warhead.À|öÄJÎD V€û €€‚ãâ‚Ñ€‰€‚‚€€‚†"€ ‚‚ÿK has improved short range capibility.Cloud ceiling algorithmA significant characteristic change of the K is in how it reacts when it loses laser lock while in flight. If a missile flies into a cloud, it will lose lock and may not reacquire the target. The AGM-114K missile has the highest probability of reacquireing the target if the missile flies into the clouds because of guidance algorithms designed for this condition. The performance of the AGM-114K is improved over the other Hellfire missiles if target acquisition is lost after launch, When the missile flies into a low cloud ceiling. In the earlier missiles, if target acquisition is lost after launch, the seeker will be inertially pointed at the target, but the missile will continue to climb at a preset gravity bias (g-bias) rate. Although the seeker is still pointing at the target, the missile climb rate does not bring the missile and its seeker below the cloud layer in time to reacquire the target. This problem was solved with improved guidance algorithms in the K missile. After target loss the K seeker will continue to point at the target; however, the missile (instead of climbing) is commanded to turn so as to point in the same direction as the seeker, which results in the missile flying out of the clouds and toward the target. This maximizes the probability of target reacquisition for the K missile.: ŠÈ„Î1[Kƒuÿÿÿÿ„ÎCM36 / M341 JεÎ% €€Œ˜€‚ÿM36 / M34骄Ϊ? L€U€€ƒƒ‚ƒƒ‚ƒ‚ƒƒ‚ƒƒ‚ƒ‚ƒ‚ƒ‚ƒ‚ƒ‚ƒ‚‚‚ÿWeight:100 lb.Length:64"Wingspan13"M36:CaptiveM34:DummyM36 NALC:5W98M34 NALC:2W59M36 NSN:6920-01-133-4438M34 NSN6920-01-131-6667M36 P/N13007355M34 P/N13007376The M36 is a captive carry missile that uses a tactical seeker attached to a holloµÎªJÎw body. The captive seeker's identification is accomplished through a wiring change in the missile umbilical. A/C launcher displays place a "T" beside the missile rail number to distinguish it from a tactical missile. Tactical missiles can not be coded while an M36 is loaded on the aircraft. The M36 captive seeker is a tactical seeker with a modified umbilical harness to identify it as a captive hellfire.™uµÎC$ €ê€€‚‚ÿThe M34 is a dummy intended for ordnance load training exercises. There are no electrical components in the M34.Fª‰1ëŒÁÿÿÿÿ‰.Millimeter Wave (mmW)=CÆ% €0€Œ˜€‚ÿMillimeter Wave (mmW)h4‰.4 6€i€€ƒƒ‚ƒƒ‚ƒ‚ƒ‚ƒƒ‚ƒ‚‚‚ÿLength:68"Weight105 lb.Wingspan:13"Homing:Semi-active homing radarFreq:94 GHzService date:1994MMW (a.k.a. Longbow) uses a millimeter wave semi-active homing seeker. It requires an AH-64D to paint the target with RF. Longbow has a greater stand off range and isn't affected by smoke/dust.OÆ}1ñuxÿÿÿÿ}Imaging Infrared System (IIRS)F!.Ã% €B€Œ˜€‚ÿImaging Infrared System (IIRS)\)}3 4€S€€ƒƒ‚ƒƒ‚ƒ‚ƒ‚ƒ‚‚‚‚‚ÿLength:70"Weight:105 lb.Wingspan:13"Homing:Passive infrared imageService date:1999Infrared Imaging System Hellfire uses a FLIR equipped seeker to lock on heat outlines. It was developed by Rockwell and is now undergoing testing by the Marines and other services.The laser Hellfire autopilot electronics currently possesses the ability to identify seekers and provide an appropriate "G" bias command for each seeker type. These experimental seekers would allow operation of Hellfire in widely varying weather and obscurant conditions.6ÃU1ùÿÿÿÿÿÿÿÿÿÿÿÿU RB-17-‚% €€Œ˜€‚ÿRB-17–eU 1 0€Ë€€ƒƒ‚ƒƒ‚ƒ‚ƒ‚ƒ‚‚‚ÿWeight:106 lb.Length:64 in.Wing span:13 inGuidance:Semiactive homing laserService date:1987The RB-17 is known as the Hellfire Swedish shore defense system. It replaces the shape charged warhead with an anitship warhead. It is identical to the AGM-114C otherwise. It loads into a tripod which can hold and fire only one missile at a time.7‚O 1 ÁÆÿÿÿÿO ùƒSeeker.  } % €€Œ˜€‚ÿSeekerá~O ^c ”€ €€‡"€‚‚‚€€‚ƒƒ‚ƒ‚ƒƒ‚ƒƒ‚ƒ‚ƒƒ‚ƒƒ‚ƒ‚ƒƒ‚ƒƒ‚ƒƒƒ‚‚ã k*ò€‰€‚ÿAGM-114A/B/C/F SeekerSpecs:Homing:Semi-active laser seekerLaser type A,B,C,Fpulsed repetion frequency (PRF)Laser type KPRF/Pulse Interval Modulation (PIM) aka Atrenate A-codePRF rate10-20 HzLaser wavelength:1.064 micrometerSpin rate:4200 rpmMax. track rate:12 deg/secOptical bandwidth300 angstromsCode type:PRF (A,B,C,F,K), PIM (K)Pulse rate:10 - 20 HzGyro:2 axis, spin stabilizedThe HELLFIRE Laser Seeker detects the coded laser energy pulses which are deflected from the target. The laser code determines the laser pulse frequency. If the designator's code and the code programmed into the missile are not the same, the missile will not acquire or track the target. It then tracks the centroid of the reflected radiation. As it tracks the target, the seeker produces up-down and left-right signals it sends to the seeker electronics before being passed on to the missile guidance section. The signals are proportional to the rate-of-change of the line-of-sight from the missile to the target, which permits implementation of proportional navigation for precision accuracy. In the AGM-114K the laser sensor processing and seeker positioning and spin controls are incorporated into the guidance group which has been moved into what used to be the aft seeker section. Pseudo range to target estimations are derived from the seeker track rates and angles.Cà} ­Ac ”€ó€€‚‡"€2‚‚‚⬠Öǀ‰€â¯–äû€‰€â“€Œ˜€‚ÿDetector / preamplifier assyÄ’èËðÎ2 2€'€€‚‚‡"€‚‚‚‚ÿThe function of the detector/preamplifier assembly is to convert laser energy, as relayed by the optics to the detector face, into four-quadrant electrical information. The assembly is located in the gyro portion of the seeker and forms part of the non-spinning gimbaled mass.Instantaneous Field of ViewThe detector is a four-quadrant, silicon PIN diode -200v with a guard ring. The detector shape approximates a square and is designed to provide maximum sensitivity over the required field of view(FOV). The average instantaneous FOV is 8 degrees. The detector is biased with -200 volts, which is carried by shielded cable from the power supply.Y4,ÌU% €i€€‚‚ÿThe detector/preamplifier package contains a heater and a sense thermistor which are connected to temperature-control circuitry on the spin and torque assembly. The heater is controlled to maintain the assembly at or above 35 degreðÎU›Ëes centigrade. This maintains high quantum efficiency in the detector.Oð΀1D7‰¬'ÿÿÿÿ€™Sensor / gimbal pickoff wiringF!Uê% €B€Œ˜€‚ÿSensor / gimbal pickoff wiring¯‹€™$ €€€‚ÿWires from the detector/preamplifier assembly are routed through the hollow inner gimbal shaft along grooves in the surface of the lens.BêÛ1w Z (ÿÿÿÿÛ Potted coil assy.9™% €(€Œ˜€‚ÿPotted coil assy."úÛ6( €õ€€‚‚‚‚‚ÿThe potted coil assembly provides the mechanical and electrical interface with the electronics assembly. This consists of a precession coil assembly, spin coils, and an impact switch assembly.The precession coil assembly consists of approximately 200 bifilar turns of 27 gauge, self-bounding, magnet wire wrapped around the gyro support. The wire is bonded to the gyro support using thin films of epoxy.The gyro support, which is a part of the potted coil assembly, is the major structural element on the entire head assembly. It is made of 40 percent glass-filled polycarbonate material and formed through an injection molding process. Not only does the gyro support supply structural support, but also angular alignment of the gyro-optics assembly.Ú  : B€A €€‚‚‚€€‚âU(H€‰€‚ÿThere are four spin coils using the same 27 gauge, self-bonding, magnet wire as the precession coil. Each coil is wound and formed separately from the assembly using a thermal process, then bonded into place.Misfire problemsThe coil assembly is essentially a DC motor field winding. A problem identified with all laser seekers has been the characteristic of a DC motor is that it can easily become a DC generator by spinning the magnetized rotor to induce a current in the field windings, i.e. coil assembly. The problem with this is that when the missile is fired the 28vdc aircraft power is removed from the missile just prior to launch. If the thermal battery is working it picks up the load and continues to spin the seeker rotor. After removing the aircraft 28vdc from the missile the launcher checks the formally powered line to see if 28vdc is coming back out the missile from the thermal battery. If the thermal battery fails, the launcher is designed to halt the missile launch sequence and signal the gunner of a Misfire (MF). What actually happens when a thermal battery fails is that the seeker rotor continues to momentarily spin which generates a voltage adequate enough to trick the launcher into thinking the thermal battery is working. The missile will launch but not guide. Assuming that the pneumatic accumulator squibs ignited, the control section has pressure but no electrical control. The control fins will be forced into two directions putting them in a maximum drag configuration. The missile will fly a ballistic arching trajectory and impact about 2000 meters in front of the launch point. No failure indication will be displayed in the cockpit.> 6N 1ÿ¬€)ÿÿÿÿN @Impact switch5 ƒ % € €Œ˜€‚ÿImpact switchŒhN @$ €Ñ€€‚ÿThe detonation of the missile warhead is initiated by the crushing of the nose of the seeker head. This is accomplished through the impact switch which is located at the interface of the optical dome and the seeker head. The impact switch consists of two (2) concentric, silver-plated copper plates, separated by a 40 percent glass-filled polycarbonate housing. The impact sensor housing is formed by the same injection molding process used to fabricate the gyro support. Redundant wiring is used in connecting the impact switch. Six stainless steel inserts carry the structural load of the seeker head. All of the wires are routed out the back of the gyro support. The entire assembly is potted to give the desired aerodynamic shape. It provides a detonation signal to the fuze upon impact and is located in a manner as to provide signals for various iƒ @ mpact angles.= ƒ X@1íZ g*ÿÿÿÿX@BSeeker purge4@Œ@% €€Œ˜€‚ÿSeeker purge|XX@B$ €±€€‚ÿA purging operation is performed to remove any moisture within the seeker by replacing the air that is present with dry nitrogen under positive pressure. A soft copper tube attached to the aft of the gyro support provides the necessary inlet into the seeker head. After the purging operation is complete, the tube is pinched off and sealed. EŒ@MB1€—„+ÿÿÿÿMBFGuidance electronics<B‰B% €.€Œ˜€‚ÿGuidance electronicsMBFw Œ€3€€‡"€"‚‚ã²3€‰€ãy€‰€âTT%€‰€â U€‰€â¹Ê÷€‰€â{ր‰€‚ÿThe AGM-114K electronics are a digitized and slightly modified functional equivalent of the analog circuits in the AGM-114B/C/F. Fifteen of the seventeen AGM-114A/B/C/F analog circuit card assemblies (CCA) of the seeker electronics and the guidance section autopilot have been compressed into seven digital and analoge circuit cards located in the K seeker and one in the Control Interface assy. The SAMPLE AND HOLD CCA, (green in fig.) CONTROLLER CCA (brown in fig.) and Gyro/Spin torquer assy. comprize the Guidance electronics group. AGM-114K guidance electronics group is functionally equivalent to the Longbow missile. Software is written with ADA and is using a 80960 microprocessor. Software is reprogrammable through the umbilical.?‰BGF1+g•‰,ÿÿÿÿGF3LController CCA6F}F% €"€Œ˜€‚ÿController CCA œGF‰HO l€{€€ƒƒ‚ƒ‚ƒƒ‚‚â Ž‡€‰€â§•5€‰€‚‚€€‚‚‚ÿDim.:9 in X 5 inDensity factor:2.19Layers:about 10The AGM-114K's CONTROLLER CCA replaces the analog DECODER and SCAN & MODE CCAs of previous models. Controller components include an 80960 CPU, 32K SRAM, 32K EEPROM, 12 BIT ADC, 12 BIT DAC and the Martin ADA Magic (MADAM) which is a single package Application Specific Integrated Circuit (ASIC). CCA Functions:*Decoder/pulse rpocessing logic / EOCM hardening*AutopilotÍ}FšJD V€›€€‚‚‚‚‚‚‚‚€€‚‚‚‚‚‚‚‚‚‚‚‚‚‚‚‚‚‚‚ÿ*Spin/precessing/agc commands*Mode control/status*Code laod/serial communications*Seeker gimbal pot buffer/led drive*Displacement gyro buffer*Warhead fuzing delyMADAM Functions:SEQUENCER:Clock generatorPower-on reset/enableSystem tmerWatchdog timerBoot ROMINTERFACE:Address & BYTE enable latchesWait state generatorBurst mode logicChip select logicExternal memory controlI/O PORTS:Parallel input & outputFast serial input & output™c‰H3L6 :€Ç€€‚‚‚‚‚‚‚‚‚‚‚‚‚‚‚‚‚‚‚ÿSlow serial input & outputSUCCESSIVE APPROXIMATIONcompetition sensitiveSPECIAL I/O:Code input (slow & fast)Commutator logicPulse counterPulse filtersPulse Input (DMA)AFC snapshotGate generatorTest pulse generatorInterrupt controlPulse width modulatorsAccelerometer inputIt is the bottom CCA in the two card guidance electronics stack.: šJmL1Å —„)-ÿÿÿÿmLr†Autopilot1 3LžL% €€Œ˜€‚ÿAutopilot$ômL΀0 .€é€€â\Žâ€‰€‚ÿThe autopilot includes electronics, two gyros (except in the K which has only one), and the internal missile power supply. It receives signals from the seeker which are proportional to line-of-sight rates to the target. These signals are then combined with signals from a gyroscopic reference package for implementation of a proportional navigation guidance law. The combined signals are used to operate actuators which effect steering and stabilization of the missile through the aerodynamic surfaces of the control section. Displacement gyros are used for pitch attitude, yaw attitude, and roll attitude references. The autopilot electronics perform the necessary signal conditioning from seeker inputs to provide steering commands to the control actuation system. Signals to the actuators are limited in the pžL΀3Litch and yaw planes in order to reserve travel for execution of roll corrections. The autopilot provides all required pitch program commands for the indirect launches prior to seeker lock-on.`;žL.ƒ% €w€€‚‚ÿThere is also a provision for gravity bias which cause the missile to climb until it obtains the predefined height about the launch platform or until the seeker angular rate input indicates that the missile is nearing the target. As the missile is looking down on target it's seeker starts looking down in pitch faster and faster as it nears the target. When the rate reaches 1.1-1.5 deg/sec the gravity bias signal is overridden. This induces a smooth arching path to the target. A proportional navigation function allows the missile to intercept moving targets.\7΀Š…% €o€€‚‚ÿThe autopilot provides timing and logic for switching and mode control of missile functions. It also is responsible for all flight control functions. Four (4) circuit card assemblies plus an interconnecting motherboard (A,B,C,F) are directly connected to the forward wire harness assembly for communication with the seeker. The autopilot electronics assembly also houses the actuator electronics and the on-board Built-in Test Equipment (BITE). The GSG also provides missile trajectory control prior to seeker lock-on during the direct and indirect (LOAL) modes.è·.ƒr†1 0€o€€‚ã²3€‰€‚ÿIn the AGM-114K, the seeker electronics have been digitized and incorporated into the same circuit card assemblies as the autopilot. Functionally they are basically the same.AŠ…³†1¬•‰/ .ÿÿÿÿ³†Electronics assy8r†ë†% €&€Œ˜€‚ÿElectronics assy­p³†˜Š= H€ç€€‡"€‚‚‚‚ãy€‰€‚ÿThe Hellfire laser seeker contains 11 electronics subassemblies which are either plug-in printed circuit (PC) boards, hard-mounted PC boards, or in the case of the detector/preamplifier assembly, a captive mounted hybrid circuit. The function of the electronics assembly is to provide LOS steering commands based on laser energy received from the outside world onto the detector. The electronics must accept command mode information from the missile autopilot and provide various status signals to the missile autopilot and the aircraft cockpit before launch. The electronics perform the conversion of laser energy to steering commands using an all-linear processor. The following is a list of circuit card assemblies in the AGM-114A,B,C and F model missiles but their electronic functions have been digitized and compressed onto two circuit cards in the AGM-114K.C놭ŒÒ r‡€€‚â¹Ê÷€‰€ƒƒ‚â7JRn€‰€ƒƒƒ‚âš8“€‰€ƒƒƒ‚âTT%€‰€ƒƒƒƒ‚â Ž‡€‰€ƒƒƒ‚⧕5€‰€ƒƒ‚⧕5€‰€ƒƒ‚â¹Ê÷€‰€ƒƒ‚‚âš(fµ€‰€ƒƒƒ‚âǗÊ€‰€ƒƒƒƒ‚âǗÊ€‰€ƒƒ‚ÿSpin/Torquer No. 1\Video Amplifier |Pulse Logic \Sample and Hold }Plug-in PC boardsDecoder /Scan and Mode No. 1 |Scan and Mode No. 2 |Spin / Torquer No . 2/Interface board\Power Supply No. I }Hard-mounted PC boardsPower Supply No. 2/q=˜Š4 8€z€€‚â e'€‰€ƒƒƒƒ‚ÿDetector/PreamplifierHard-Mounted hybrid assembly@­Œ^1)€/ÿÿÿÿ^œÁInterface board7•% €$€Œ˜€‚ÿInterface boardø^œÁ$ €ñ€€‚ÿAll wires from the gyro and coils are soldered to appropriate connections on the interconnection board. The interface board provides the electrical interface with the electronics assembly. The power supply voltages, bias for the preamplifier, gimbal angle pickoff signals, commutator signals, and the various other voltages/signals to and from the seeker head assembly are wired to the interface board, the interface board then connects to the electronics assembly via a connector and flex harness, exceptions to this electrical interface are the impact sensor signals which r•œÁoute directly to the seeker missile interface and the detector/preamplifier video outputs which route directly to the video amplifier board. In addition, the circuitry on the interface board processes the gimbal angle signals and guidance signals and provides for compensation of unit-to-unit seeker head variations. Detector heater circuit controls detector temperature at or above 95 degrees F for maximum pulse responsivity.A•þÁ1>/ uƒ0ÿÿÿÿþÁûÅSPIN TORQUER CCA8œÁ6Â% €&€Œ˜€‚ÿSPIN TORQUER CCA:þÁpÄ6 :€ €€€€‚‚‚‚‚‚€€‚ÿProvides spin drive currents to spin coils in seeker head and has the following characteristics:-Bipolar drive to two sets of coils provides quadrature drive-Timing derived from optical commutator inside seeker head which provides magnet position information-Spins up seeker head to "up to speed" (torquer enable speed" in approximately 11 seconds at ambient, <26 seconds at -45 degrees F-Regulates final spin speed to approximately 69.5 HzProvides torquer drive currents to torquer coils in seeker head‹^6ÂûÅ- (€œ€€‚‚‚‚‚‚‚‚‚‚ÿ-Bifilar windings driven by separate amplifiers-Optical commutator timing used to provide drive switchingDifferences of AGM-114K from AGM-114A/B/C/F:No Custom microcircuitsMoved from forward bulkehead to power supplyPrecession coil solenoid instead of bifilarSpin drive 180 degreees instead of 90 degrees50% more spin torqueNo dead spots.DpÄ?Æ1€Ӆ1ÿÿÿÿ?ÆÉVIDEO AMPLIFIER CCA;ûÅzÆ% €,€Œ˜€‚ÿVIDEO AMPLIFIER CCAä?Æ‹È- (€É€€‚‚‚‚‚‚‚‚‚‚ÿThe Video amplifier:-Receives the four channels of pulse video from the preamplifier-Performs amplitude limiting, logarithmic amplification and sums adjacent channels-Provides a part of the noise AGC loop (which controls the number of allowed threshold detections per second)-Provides approximately 25 DBP of dynamic range-Channels are balanced +/- approximately 5%Differences of AGM-114K from AGM-114A/B/C/F:Custom microcircuitsCloser to source of millivolt input signals‰dzÆÉ% €È€€‚‚‚ÿAGC input voltage range (=/- 10vdc)-200 volt detector bias filteringNo adjustment potentiometer@‹ÈTÉ1CuƒW‰2ÿÿÿÿTÉWÍSAMPLE AND HOLD7É‹É% €$€Œ˜€‚ÿSAMPLE AND HOLDÚTÉ“Ë. *€µ€€‚‚‚‚‚ƒ‚ƒ‚‚‚ÿThe sample and hold circuit card:Performs generation of guidance commands-Receives four log-summed adjacent channel pulse outputs from video amplifier-Samples and holds adjacent channel amplitudes-Performs difference function and generates output guidance commandsPitch command = Log (A+D) - Log(B+C)Yaw command = Log (A+B) - Log(C+D)Performs pulse discrimination-Inputs are delayed by 200 nanoseconds to allow discrimination circuitry to accept or reject pulseĘ‹ÉWÍ, &€1€€‚‚‚‚‚‚‚‚‚ÿ-Performs pulse discrimination by comparing pulse amplitude to threshold comparators utilizing a dynamic threshold-Performs a pulse width test-Generates a "valid" pulse presence output to decoderDifferences from AGM-114A/B/C/F:No custom microcircuitsCombined functions of sample and hold plus pulse discriminatorIncludes NDC (smoke rejection) circuit from HHLS seekerPhysical location, form factor@“Ë—Í1§Ӆ3ÿÿÿÿ—Í£PULSE LOGIC CCA7WÍÎÍ% €$€Œ˜€‚ÿPULSE LOGIC CCAØ—ÍÐÏ* "€±€€‚‚‚‚‚‚‚ÿGenerates automatic gain control (AGC) for preamplifier- Receives sample and hold pulse amplitude from sample and hold board- Controls preamplifier gain to maintain 4 volt pulse peak set point on pulse amplitude (approximately in center of video amp dynamic range)- With preamplifier attenuators provides approximately 37 DBP of dynamic rangeGenerates dynamic threshold voltage-Provides an amplitude versus time threshold voltage utilized on sample and hold boardǟÎÍ£( €?€€‚‚‚‚‚ÿGeneraÐÏ£WÍtes noise AGC voltage- Provides noise control by holding the noise pulse presence to a fixed rateIncooperated into the AGM-114K Sample & Hold CCA.< ÐÏß1¶W‰ÿ4ÿÿÿÿßYDECODER CCA3£% €€Œ˜€‚ÿDECODER CCAíß+, &€Û€€‚‚‚‚‚‚‚‚‚ÿAccepts code load information- Receives a 16 BIT code load command from helicopter- Decodes command to a valid pulse repetition frequency- Transmits a code accept pulse if received code was validPerforms target acquisition function- Receives pulse presence signals from sample and hold- Places each received pulse into a "bin" corresponding to its time of arrival- Examines "bin's" corresponding to anticipated pulse repetition frequency for satisfaction of acquisition requirements.Y* "€ €€‚‚‚‚‚‚‚ÿGenerates master lockout (MLO) gate after acquisition- Generates and MLO gate in anticipation of the next pulse, at the anticipated PRF, after acquisition (when acquisition is true, pulse not in this gate are ignored)- maintains a count of missing pulses (no pulse occurred in MLO gate) and declares loss of acquisition if criteria is reached.Generates automatic frequency control- At acquisition, modifies master clock frequency to match exact received PRF (prevent continuous "walking" of received pulses)A+š1³õ5ÿÿÿÿš MODE CONTROL CCA8YÒ% €&€Œ˜€‚ÿMODE CONTROL CCA)úšû/ ,€õ€€‚‚‚‚‚‚‚‚‚‚‚‚ÿReceives input command from autopilot- Receives cage, stare, scan, CCM and launch commands- Provides necessary internal signals to other seeker CCAs- Controls spin torquer by providing rate commands as requiredProvides track mode logic- Performs "angle gate" check before setting track true- Controls "high gain" mode on spin torquer- Switches guidance commands to missile and spin torquer when track trueGenerates box scan pattern- Provides maximum rate pitch or yaw commands to spin torqueréÒ ( €Ó€€‚‚‚‚‚ÿ- Determines pitch and yaw excursions by comparing gimbal angle outputs to zener diode thresholdsProvides status outputs to missile- Correlation, track, cage and seeker ID- Latches track output for loss-of-lock on after launch= ûI 12ÿL 6ÿÿÿÿI >POWER SUPPLY4 } % €€Œ˜€‚ÿPOWER SUPPLYÞI „ ) €œ€€‚‚‚‚‚‚ÿThe power supply is a switching regulator type. It receives +28 vdc +4/-6 from the missile and draws a 12 amp peak, 4 amp average load. Nominal switching regulator frequency is 20 KHz. Regulated by a separate sense winding on the single output transformer (provides tight control for input voltage variations but does not regulate output voltages changes due to loads). Generates all required voltages for seeker operation which are:+5.1 vdc+15.0 vdc-15.0 vdc-28 vdc@} Ä , &€)€€‚‚‚‚‚‚‚‚‚ÿ-200 vdcThe power supply consist of a Converter CCA, Interface CCA, Filter CCA and aluminum housing.The warhead precursor jet must penetrate the seeker, therefore a void which is one-quarter of body diameter and 1.5 to 2.0 charge diameters long must also be provided through the seeker electronics to prevent any interference with the warhead jet formation.Differences between AGM-114K and AGM-114A/B/C/F:Two circuit cards instead of three.No warhead void through assembly (void exists only in rear cover and first board)zV„ >$ €¬€€‚‚ÿ-200 volt inverter instead of converted bias supply+5 volt current drain increased8Ä v1Fõ 7ÿÿÿÿv„Strakes/ >¥% €€Œ˜€‚ÿStrakesß°v„/ ,€c€€†"€‚‚‚ÿStrakes destabilize the missile to reduce slipping during a turn. They cause the forward end to dip into the airstream as the aft control surface kicks the back end out.: ¥Ÿ1âL µ 8ÿÿÿÿŸì‚Umbilical1 „ @% €€Œ˜€‚ÿUmbilicalŸ @„ÌŸ%BM h€™€€‚‚€€‚ƒƒƒƒƒƒƒ‚ƒ‚ƒƒƒƒƒƒ‚ƒƒƒƒƒƒƒ‚ƒƒƒƒƒƒƒ‚ÿInterface for all electrical functions between missile and aircraft except the deice squibs. The umbilical, a.k.a. shotgun connector, houses two 37 pin connectors that automatically connect when the missile is loaded.J1PinSignal NameVoltageOriginComments1RF Frequency cmd2Yaw guidance cmd+-10vdcMissilemonitor Yaw guide cmd3-114K ident+5vdcMissilehigh out from K model4Seeker Ident.+5vdcMissileDefines skr type as laserÀ @?DZ ‚€€€ƒƒƒƒƒ‚ƒ‚ƒƒƒƒƒƒ‚ƒ‚ƒƒƒƒƒ‚ƒƒƒƒƒƒƒ‚ƒ‚ƒƒƒƒƒ‚ƒƒƒƒƒƒƒ‚ƒƒƒƒƒƒƒ‚ÿ5Slave command+5vdcLauncherFollow LOS cmd if lock-on6Target polarity7Pitch guidance cmd+-10vdcMissilemonitor pitch guide cmd8Gimbal limit attained9Counter measures+5vdcLauncherTurns on CM10Yaw gimbal+-9vdcMissileDrives skr position ind. lt/rt11PRF command12Scan/search cmd+5vdcLauncherBox scan active13Missile presentGroundMissileGround until launch14Analog shield0MissileGimbal angle shield#¿%BbFd –€€€ƒ‚ƒƒƒƒƒƒƒ‚ƒƒƒƒƒ‚ƒƒƒƒƒƒ‚ƒƒƒƒƒƒ‚ƒƒƒƒƒƒ‚ƒƒƒƒƒƒƒ‚ƒ‚ƒƒƒƒƒƒƒ‚ƒ‚ƒƒƒƒƒƒƒ‚ÿ1516Signal ground0Noncurrent carrying ref.17Nuclear event trigger+5vdc299 launcherProtects MSL from EMP18Stare/track cmd+5vdcLauncherlook ahead /direct mode19Correlation status+5vdcMissileInfo lau that skr is correlate20Primary pwr+28vdcLauncherOn when msl selected21Aux 28vdc+28vdcEnvironmental pwr for TM2223Deice power2425Pitch gimbal+-9vdcMissileDrives skr position ind. up/dn Ž?DmHW |€i€€ƒƒƒƒƒƒ‚ƒƒƒƒƒƒƒ‚ƒƒƒƒƒƒ‚ƒƒƒƒƒƒ‚ƒ‚ƒƒƒƒƒƒ‚ƒƒƒƒƒƒ‚ƒƒƒƒƒƒ‚ÿ26TM POC14vdcLauncherTelemetry power change over27Logic return0Digital (+5vdc) return2828vdc msl squib rtn0Missilebatt,gyro,accumulator squib rtn.29Missile squib fire+28vdcMissileBatt,gyro,accumulator squib fire30Squib shields3128vdc msl squib rtn0Missilebatt,gyro,accumulator squib rtn.32Missile squib fire+28vdcMissileBatt,gyro,accumulator squib fire33DC ground0Launcher11amps maxºbFŠJc ”€u€€ƒƒƒƒƒƒ‚ƒƒƒƒƒ‚ƒƒƒƒƒƒ‚ƒƒƒƒƒƒ‚€‚€‚ƒƒƒƒƒƒƒƒ‚ƒƒƒƒƒ‚ƒƒƒƒƒ‚ƒƒƒƒƒƒƒ‚ÿ34DC ground0Launcher<6.5 amps average35Environmental Pwr+28vdcLauncherConstantly on36Primary pwr+28vdcLauncherOn when msl selected37Primary pwr+28vdcLauncherOn when msl selectedJ2PinSignalVoltageOriginComments1Msl BIT control, BIT 114vdcLauncher1/4 of msl BIT interface2Serial data in (-)0 to +5vdcSupport equp.Test / program line /pin 73Track status+5vdcMissileLaser is locked onÀmH¢LX ~€€€ƒƒƒƒƒƒ‚ƒƒƒƒƒƒƒ‚ƒƒƒƒƒƒ‚ƒƒƒƒƒ‚ƒƒƒƒƒƒƒ‚ƒ‚ƒƒƒƒƒƒƒ‚ƒƒƒƒƒƒ‚ÿ4Pitch slave cmd+-9vdcLauncher1 deg / vdc5Cage status+5vdcMissileSpin-up achieved6Missile BIT response+-10vdcMissileAnalog response from BIT7Serial data in (-)0 to +5vdcSupport equp.Test / program line /pin 28+18vdc+18vdcLauncherOn w/ selected msl / off @ fire9Deice return10Actuator test+-10vdcMissileEmulate actuator test to equip.11Cage command +5vdcLauncherSeeker spin up signal-no trk/slv®ŠJŠNV z€]€€ƒƒƒƒƒƒ‚ƒƒƒƒƒƒƒ‚ƒƒƒƒƒƒ‚ƒƒƒƒƒ‚ƒ‚ƒƒƒƒƒ‚ƒƒƒƒƒƒ‚ƒƒƒƒƒƒƒ‚ÿ12Yaw slave cmd+-9vdcLauncher1 deg / vdc13Code select +5vdcMissileBi-directional serial code/confm14Code clock0-5vdcLauncher1KHz, On for 16 bit count15Motor squib fire return0LauncherPropulsion section ignition1617TM ON/OFF control14vdcLauncherControl telemetry power18Program enable +5vdcTest setPermits msl to be reprogram19-18vdc-18vdcLauncherOn w/ selected msl / off @ fire2á¢Lä€Q p€Ã€€ƒ‚ƒ‚ƒ‚ƒƒƒƒƒ‚ƒƒƒƒƒ‚ƒ‚ƒƒƒƒƒƒ‚ƒƒƒƒƒ‚ƒƒƒƒƒƒ‚ƒƒƒƒƒ‚ÿ20Video shield21PRF & pulse width22PRF & pulse width shield23Serial out clock0 to 5vdcTest set synch data transfer on serial out24Serial data out (+)0 to +5vdcMissileTo test set / programmer /pin 3525Separation26LOAL-HIGH14vdcLauncherSetsŠN䀄 msl mode to THCDP mode27Msl BIT control, BIT 314vdcLauncher1/4 of msl BIT interface28LOAL-LOW14vdcLauncherSets msl mode to THCDP mode29Msl BIT control, BIT 214vdcLauncher1/4 of msl BIT interfaceµŠNì‚S t€k€€ƒƒƒƒƒ‚ƒƒƒƒƒƒƒ‚ƒƒƒƒƒ‚ƒƒƒƒƒƒƒ‚ƒƒƒƒ‚ƒƒƒƒƒ‚ƒƒƒƒƒƒ‚ƒ‚ÿ30Msl BIT control, BIT 414vdcLauncher1/4 of msl BIT interface31Logic shield0Shield for code select/clock line32Motor squib fire+20vdc+-8.5LauncherPropulsion section ignition33Test return0Missilereference ground34Launch command5-0vdc pulseLauncherNormal hi - lo @ fire, ignites TB35Serial data out (-)0 to +5vdcMissileTo test set / programmer /pin 2436Squib armLauncherNot used M3637VideoCä€/ƒ1Ê Þ 9ÿÿÿÿ/ƒ¶…Pre-cursor warhead:ì‚iƒ% €*€Œ˜€‚ÿPre-cursor warheadM/ƒ¶…J b€)€€†"€"‚‚ƒ‚ƒƒƒ‚ƒƒ‚ƒƒ‚‚‚‚âüÂן€‰€‚ÿPre-cursor explosive weight:2.25 lb.Explosive:LX-14Fast cookoff time:1 minuteSlow cookoff temp.:358 degrees FReactive armor defeats standard small shape charge warheads by breaking up the uniformity of the shape charge by using a counter explosion. The pre-cursor warhead counters the reactive armor and clears the way for the main charge. The AGM-114F adds a 7 inch long pre-cursor warhead section between the seeker and main warhead. Otherwise the AGM-114F is identical to an AGM-114C.= iƒó…1kµ ù„ :ÿÿÿÿó…eÆMain Warhead4¶…'†% €€Œ˜€‚ÿMain Warhead€ó…,ˆa €S€€†"€ ‚‚€€‚ƒ‚ƒ‚ƒƒ‚ƒƒ‚ƒƒƒ‚ƒƒ‚ƒƒ‚ƒƒƒ‚ƒƒƒƒ‚ƒƒ‚ƒƒ‚ƒƒ‚ƒƒ‚ƒƒ‚ÿSpecs:Total main charge weight24 lb.Explosive weight A,B,C & F13.6 lb.Explosive weight, K12.5 lb.Explosive materialLX-14Penetration:>36" of steelBooster materialPBXN-5Cone liner materialsilver bearing copperCone weight1 lb.FuzeM820Slow cookoff temp.:358 degrees FFast cookoff time:1 minuteArming distance150-300 mtArming acceleration10 g'sFocused pressure5 million psiV%'†‚‹1 0€K€ãÜ0L"€‰€‚‚‚‚‚ÿCookoff distancesThe M265 (K is modified M265) warhead itself is a conical shaped-charge explosive device designed specifically for penetrating armor, and is capable of defeating all known armor. The Fuze is located at the aft end of the warhead and contains the safing and arming device (S&A) which prevents inadvertent triggering of the fuze. The Fuzing action is initiated through the crushing of the impact switch located at the optical dome interface.The body of the warhead section is an integral part of the missile's airframe. The warhead body section extends aft past the fuze and houses the guidance components It provides the structural interface between the seeker section (which is forward of the warhead section) and the propulsion section (which is aft of the warhead section).Ù,ˆ‚Ž' €³€€‚‚‚‚ÿ:The HELLFIRE warhead is a High Explosive Anti-Tank (HEAT) type. The major components of the warhead are the warhead body (including a center support ring), a liner-explosive subassembly, a retainer ring, a main charge booster, a precision initiation coupler, a wave shaper, and a cover plate.In operation, the warhead explosive charge is detonated at the rear end. A detonation wave proceeds forward through the explosive at extremely high velocity (8,837 meters/sec for LX-14). The shock wave emanates from the fuze lead charge in a spherical shape, but gradually flattens. A lead alloy wave shaper further flattens and inverts the shock wave so that the conical liner is attacked by a more nearly side-on pressure wave.‡b‚‹Á% €Å€€‚‚ÿThe initial acute angle of the warhead results in a high speed precursor that supplies the first punch to the tank hull. The shallower angle of the warhead results in a slower and more elongated jet. The production of the jet is the essential characteristic of the shaped charge. The jet is actually a rod of material with a velocity gradient‚ŽÁ¶… from the tip to the tail. The precursor portion of the liner produces a jet with an initial velocity on the order of 10 KM/sec (mach 30). This clears out the seeker before the main liner jet arrives, having an initial velocity on the order of 9 KM/sec (mach 20).Ÿl‚ŽŽÃ3 4€Û€€‚‚‚†"€‚‚‚‚ÿThe jet velocity of the shaped charge warhead gradually decreases as the detonation process proceeds, because of decreasing C/H (Charge/Metal) ratio. As a result, the jet elongates, reduces in diameter, and finally breaks up into short rods at long standoffs.Warhead Pre-cursor and Jet DevelopmentThe ductile silver bearing copper acts as a fluid upon target impact, inducing pressures on the order of 300-400,000 atmospheres (approximately 5 million PSI). At such high pressures, the tensile strength of even hard armor is vastly exceeded, and the jet and target materials flow, forming a volcano-like void. ±ŒÁeÆ% €€€‚‚ÿWhen the armor is thin enough to be completely penetrated, a compressive shock traveling through the armor breaks out a large spall on the backside, producing a shower of extremely small, high-velocity fragmentation. 15 lb. of tank material are shot into the tank cabin with an equivalent power of 200 shotgun shells. Both the main jet and secondary fragmentation spall contribute to target damage. Penetration capabilities of the shaped charge warhead scales in direct proportion to jet length (the product of jet velocity and break-up time) and/or charge diameter. The main charge alone is capable of penetrating over 36 inches of solid steel.: ŽÃŸÆ1‚Þ ë† ;ÿÿÿÿŸÆçÈExplosive1 eÆÐÆ% €€Œ˜€‚ÿExplosiveæŸÆçÈ1 0€Í€€ƒ‚ƒƒƒ‚ƒƒ‚ƒƒ‚‚‚ÿExplosive weight:13.6 lb. (A,B,C,F)12.5 lb. (K)Total weight:24 lb.Explosive:LX-14The main charge and main charge pellets, utilize LX-14 explosive, while the booster pellet and precision initiation coupler contain PBXN-5. The mass of the loaded warhead is approximately 24 lb. The conical shaped charge consists of a pressed explosive (under extreme pressure) contained in a cylindrical case. The AGM-114K warhead was shortened to make room for the pre-cursor warhead.> ÐÆ%É1¶ù„ ˆ <ÿÿÿÿ%ɝÊConical Liner5çÈZÉ% € €Œ˜€‚ÿConical LinerC%ɝÊ$ €?€€‚ÿThe conical liner is composed of a dense, ductile metal (silver bearing copper). The liner is manufactured with extreme precision to assure good penetration, with thickness and concentricity controlled to 0.0001 inches, while explosives alignment is controlled to about 0.001 inches= ZÉÚÊ1(ë† # =ÿÿÿÿÚÊ4Warhead Fuze4ÊË% €€Œ˜€‚ÿWarhead Fuzeo?ÚÊ}Î0 .€€€ƒƒƒ‚ƒƒ‚ƒ‚‚‚‚‚ÿFuse:M820Fuse explosive:.3 gramsExplosive class:CThe Fuzing system for the HELLFIRE warhead consists of an impact switch (located in the seeker section) and a safing and arming device (S&A) (M820) which is attached to the aft end of the warhead .The major components of the fuze include an arming rotor and escapement delay mechanism; a printed wiring board assembly (which includes the fuze timing; circuit); a solenoid-operated latch for primary fuze enable and rotor position-lock; the fuze electric detonator and explosive lead assembly; and structural components, including a plastic support, a mounting plate, a warhead attachment flange, and a fuze case assembly. The case assembly includes the safe-arm indicator window and the fuze electrical connector. The fuze meets design requirements of MIL-STD-1316.a<Ëê% €y€€‚‚ÿThe fuze itself is a base detonating electro-mechanical device which provides the safing, arming, and detonation functions for the conical shaped-charge warhead. In order for the fuze to arm after missile launch, it requires that missile power at 28 DC volts nominal throughout the arming cycle coincide with a prescribed launch acceleration profil}ÎêÊe. Upon completion of mechanical arming, the detonator is unshorted and internal switching action applies missile power to the firing capacitor. If a power loss occurs after charging the capacitor to 28 DC volts, the charge will stay above the designated "all-fire" level of the detonator for at least 60 seconds, but will dissipate in 10 minutes or less. If a pre-closed trigger switch exists, the firing capacitor will not charge up. This prevents an airburst at arming. J#}Î4' €G €€‚‚‚‚ÿWhen the arming rotor is out-of-line, it is locked in place by a setback weight, and both the rotor and the setback weight are locked safe by a solenoid-operated latch. When mechanical arming is complete, internal switching action releases the solenoid latch and allows it to re-engage the rotor and lock it armed. The returning setback weight then traps the latch in place as the rocket motor g-force falls off due to the rise in drag.At the onset of launch acceleration, the fuze setback weight will not move below 7g but will move back completely at 10g and above, to allow the fuze to arm. The arming rotor is an eccentric mass which rotates aft from the safe to the armed position at an angular rate proportional to missile acceleration. The rate of rotation is controlled by a runaway escapement mechanism. The escapement is a "double integrator", which allows the fuze to arm at an essentially constant separation distance provided the applied acceleration remains above the setback weight threshold for a sufficient period of time. The specification requirement for this separation distance is not less than 150 meters and not more than 300 meters. It is important to note that the arming mechanism responds to the incremental force available to accelerate the missile. The fuze cannot sense total distance traveled by the missile, but with minor allowances, mainly for the non-linearity of the mechanism itself, the device does sense actual separation from a launch vehicle flying at any constant velocity up to the design limits of the mechanism.6êj1Fˆ » >ÿÿÿÿjz Shoes-4—% €€Œ˜€‚ÿShoesíj³ / ,€Ý€€†"€‚‚‚ÿThere are three shoes atop the Hellfire missile. The forward shoe is part of the umbilical assembly. The forward and middle shoe are wider than the aft shoe. This configuration allows the middle and aft shoes to engage/disengage the launch rail at the same time. The design of the shoes and the launcher rail permit simultaneous release during launch to minimize "tip-off" dynamics. This makes it easier to load the missile but primarily is used to counteract rail torque that could act solely on the aft shoe if the ordnanceman didn't keep the missile in line with the rail as it was being loaded. The missile is locked into the rail by means of the detent and missile shoe. It takes 700 LB of launch pressure to override the detent. Ç¢—z % €E€€‚‚ÿA known problem of hellfire is centered around the middle launch shoe and rail flex. Launch shock can cause the rail to flex which is most evident at it's tip. This rail flex can induce a roll in the missile just as the middle shoe is clearing the forward end of the rail. If this roll is excessive the roll gyro will exceed its roll limit and crash. This causes the missile to spin immediately out of control.9³ ³ 1Ò# ‚ ?ÿÿÿÿ³ ëBGuidance0 z ã % €€Œ˜€‚ÿGuidanceºL³ ©@n ª€­€€†"€‚‚ƒ‚ƒƒ‚ƒ‚ƒƒ‚ƒƒƒ‚‚ãy€‰€â\Žâ€‰€âU(H€‰€âqQSR€‰€‚ÿAccumulator pressure:8000 psiRegulated to:600 psiGyro accumulator pres.3000 psiGyro spin rate:40,000 - 20,000 rpmRoll stabilized:+/- 10 degThe Guidance Section Group of the A,B,C and F models consists of an autopilot electronics assembly, two (2) displacement gyros, thermal battery, and a pneumatic accumulator. The harness on the autopilot electronics assembly is soldered to the battery, the gã ©@z yros, and the pneumatic accumulator. A flexible gas line is attached to the pneumatic accumulator and the above items are mounted in an aluminum enclosure.Bã ëB= H€ €€‚ã²3€‰€ãI (d€‰€‚ÿThe Guidance Section Group receives target tracking commands from the laser seeker and provides stabilization and steering commands to the missile control section, which responds by positioning aerodynamic flaps. It provides missile trajectory control prior to seeker lock-on during the indirect firing-mode. It also provides discrete commands to the seeker, electric and pneumatic power requirements, and timing and logic for switching and control of missile functions within the autopilot electronics.B©@-C1™» ¿„ @ÿÿÿÿ-C„FControl Interface9ëBfC% €(€Œ˜€‚ÿControl Interface!É-C‡EX ~€§€€†"€‚‚âU(H€‰€âqQSR€‰€ãI (d€‰€‚‚‚‚‚‚ÿThe control interface group contains the thermal battery, and a pneumatic accumulator and regulator. A flexible gas line is attached to the pneumatic accumulator and the above items are mounted in an aluminum enclosure. The accumulator supplies pressurized gas to the control solenoids.Functions:Contains safing relays for squib firingProvides regulated tracking switched +/-12vdc regulatorsGenerates CAS fin solenoid drive commandsýÓfC„F* "€§€€‚‚‚‚‚‚‚ÿProvides arming/ESAF/motor power controlGenerates solensid BIT response from fin drivesDifferences of AGM-114K from AGM-114A/B/C/F:ESAF connections/arming+/-12vdc switching regulatorsAutopilot functionsF‡EÊF1å‚ ™‰ AÿÿÿÿÊFiLPneumatic Accumulator=„FG% €0€Œ˜€‚ÿPneumatic Accumulator ÁÊFIL f€ƒ€€‚ƒƒ‚ƒ‚ƒ‚ƒƒ‚ƒ‚ƒ‚‚‚ƒƒƒ‚ƒ‚ƒ‚ƒ‚ƒƒ‚‚‚ƒƒ‚ƒƒ‚ƒƒ‚ÿReservoirGas:Nitrogen per BB-N-411Pressure:8,000 psiVolume:50 cu in (spherical bottle)Metal:Carpenter custom 455 corrosion resistant steelProof pressure13,600 psiBurst pressure22,500 psiInitiator (A/B/C/F)Type:Dual bridgewireBridgewire resistance:1 ohm +/-0.1Sure fire current:5 amp100% no-fire current:1 ampQualification:MIS-29265RegulatorInlet pressure:8,000 psiInlet proof12,000 psiInlet burst20,000 psißG$L1 0€¿€€ƒƒ‚ƒƒ‚ƒƒ‚ƒƒ‚‚‚ÿOutlet pressure600 psiOutlet proof1,200 psiOutlet burst2,000 psiFlow rate:280 std liters N2 @ 600 psiThe accumulator assembly consists of a high pressure gas storage tank filled with gaseous nitrogen at 8,000 PSI, a squib activated cutter valve, and a pressure regulator. Upon squib activation of the cutter valve, the regulator becomes pressurized with the high pressure gaseous nitrogen. This in turn pressurizes the two (2) dual actuator assemblies, thus allowing the aerodynamic control surfaces to be utilized. This is accomplished through a tubing system which connects the regulator to the actuator assemblies. The regulator routes the nitrogen gas at 600 PSI to each of the two (2) dual actuator assemblies.E"IiL# €D€€‚ÿAssembly P/N 13008160 (A,B,C,F)B$L«L1í¿„  Bÿÿÿÿ«Lb…Thermal batteries9iLäL% €(€Œ˜€‚ÿThermal batteriesK«L;€J b€€€‡"€‚‚ƒƒ‚ƒƒƒ‚ƒƒ‚ƒ‚ƒƒ‚ƒƒƒ‚ƒƒ‚ƒƒƒ‚‚‚ÿVoltages:25-32 vdc @ 6.5 amps15-19.5 vdc @ 0.25 ampsActivation time0.8 sec. maxMax. operation time:45 secondsElectrolyte:Fused saltPlates:Lithium-silicon/iron disulfideDiameter:2.5 in (K batt)Length:3.7 in (K batt)The missile's thermal battery provides all the electrical power to the on-board systems subsequent to separation from the launcher. The battery is activated by a squib fire signal. Heat pellets are ignited by the squib initiator to start the electro-chemical system. It is composed of fused salt electrolyte of disk-type cell elements, and operates at an extremely high temperature (>600K). Upon launching, the missile's thermal battery supplies the seeker, autopilot controäL;€iLl section, and fuze with nominal 28 Volts DC.èäLL‚) €Ñ€€‚‚‚‚‚‚ÿIt actually serves as a dual-section battery. Section I supplies 25-32 Volts DC at an average drain of 6.5 Amps, while section II supplies + - 15 Volts DC at an average drain of 0.25 Amps. The two sections are necessary to supply specific components of the missile with the proper voltages and currents for operation.The AGM-114K / Longbow thermal battery is redesigned and has only one output voltage. Sized for an 18 amp load for 55 secondsK pinout:1- negative of 28v outputÚ;€b…< F€µ€€‚‚‚‚€‚€‚â“ X DÿÿÿÿŠ‹Wings-ى<Š% €€Œ˜€‚ÿWingsÛ·Š‹$ €o€€‚ÿThe four wings are riveted to the propulsion section outer surface. Assists the missile in maintaining altitude by increasing it's glide slope and stabilizes the missile attitude.; <ŠR‹1î™ cˆ EÿÿÿÿR‹2ÍPropulsion2 ‹„‹% €€Œ˜€‚ÿPropulsion šR‹c ”€S€€†"€‚‚‚ƒƒƒ‚ƒƒ‚ƒƒƒ‚ƒƒƒ‚ƒƒƒ‚ƒƒ‚ƒƒƒ‚ƒƒƒ‚ƒƒƒ‚ƒ‚ƒƒƒ‚ƒƒƒ‚ƒƒƒ‚ƒƒƒ‚ÿSpecs:Propellant:SolidPropellant weight:20.5 lb.Propellant type:TP-Q7030Thrust A:1700 lb. peakThrust B,C,F,K:1900 lb. peakThrust alignment0.125 deg. ax errorTotal impulse20,000 nt-s minimumMax. velocity:475 m/sec (mach 1.4)Min. velocity:400 ft/secLaunch delay from trigger:1 secondSquib qty.2Squib current1 amp / 1 wattIgniter pellets15 GM BKNO3Burn time:5.8 secondsœ„‹Q p€{€€ƒƒƒ‚ƒ‚ƒƒƒƒ‚ƒƒ‚ƒƒƒãSV6€‰€‚ƒƒ‚ƒƒ‚ƒƒƒ‚ƒƒ‚ƒƒ‚ÿBurn time:2 - 3 secondsTime of flight @ 70 deg F13 sec @ 3000 mt; 20 sec @ 5000 mt.; 38 sec @ 8000 mtStages:SinglePropellant points:5Max. altitude17,000 ftReduced smoke:Model # M120 used on AGM-114A (visible smoke)Minimum smoke:AGM-114B, C, F, K, IIR, MMWSAD used in:AGM-114B & KTemp @ nozzle centerline:2000 deg K @ 3.7mt1000 deg K @ 6.6 mtPressure @ nozzle centerline:1000K.Pa @ 1 mt150 K.Pa @ 3.6 mtrKÄ' €—€€‚‚‚‚ÿThe Propulsion Section consists of the rocket motor, the mÄ‹otor squib, and the four (4) cruciform wings. The HELLFIRE's boost-coast type solid-propellant motor generates sufficient thrust to separate the missile from the launch rail, provide the acceleration profile necessary to arm the warhead fuze at a safe separation distance from the launch vehicle, and allow missile launches beyond the target's gun defense range with a minimum flight time to the target.Along with providing the thrust for missile acceleration, the propulsion section also supports the wings, warhead, and control section attachment points. It houses the motor's molded cellulose phenolic nozzle, which has a Styrofoam closure plug bonded inside the exit cone. The propulsion section's 7-inch diameter is an integral part of the airframe with machined end skirts for warhead and control section attachments. The four (4) wing rails are attaches to an extruded aluminum casing which is extruded 7075-T73. The section is lined with a 0.45 inch layer of hydroxyl-Terminated Polybutadiene (HTPB) for insulating purposes.Ž[©Ç3 4€¹€€‚†"€‚‚‚‚‚‚ÿPropulsion crossectionalThe HELLFIRE rocket motor is 7-inches (177.3 mm) in diameter and 23.4 inches (593.8 mm) in length. it's weight is approximately 33 pounds (15 kg). The motor has an integral head-end mounted pyrotechnic igniter and a nozzle/blast tube at it's aft end. It is a five-point, double web, internal burning, solid propellant motor. Electric squibs are used to activate the pyrotechnic igniter.The motor provides adequate thrust to separate the missile from the launch rail and the acceleration profile necessary to arm the warhead fuze at a safe separation distance. It also provides the impulse witch enables the missile to be launched outside the target's gun defense range with a minimum flight time to the target. Motor burn time is 2-3 seconds but the motor liner may burn and be visible for the duration of missile flight.ñÄÁÉ' €ã€€‚‚‚‚ÿThere are two versions of the HELLFIRE rocket motor. The current production motor contains propellant which leaves a "reduced smoke" exhaust signature, while the propellant of the improved motor displays a minimum smoke" exhaust signature.The improved version of the HELLFIRE motor incorporates an igniter that will accept a safe-and-arm device for the Marine version. It also eliminates the possibility that the enemy could locate the launch vehicle due to the missile's exhaust signature.mF©Ç.Ì' €€€‚‚‚‚ÿThe igniter of the "reduced smoke" motor contains 15 grams of boron potassium nitrate (BKNO3) pellets as the main pyrotechnic charge. The combustion of these pellets is initiated by the firing of two (2) electric actuated squibs.The igniter of the "minimum smoke" motor contains 0.5 grams of BKNO3 powder and 1.5 grams of BKNO3 pellets as an initiator charge. Its main charge consist of 20.5 grams of HEN-12 propellant and 16.4 grams of N-14 propellant. Combustion of the pellets ( and subsequently the igniter propellants) is initiated by two (2) electric-actuated squibs.ÐÁÉ2Í4 6€¡€€‚‚‚‚⧜ø€‰€‚ÿA waiver was issued to circumvent failed propulsion insensitive munitions tests. The propulsion section failed slow cookoff, multiple bullet impact and fragment impact test.Related topics:Hangfire= .ÌoÍ1dX A‰ FÿÿÿÿoÍ–ÎMax Altitude42Í£Í% €€Œ˜€‚ÿMax AltitudeóÏoÍ–Î$ €Ÿ€€‚ÿAGM-114 will climb to 17,000 ft before stalling. This data derived form a computed flight simulation of an AGM-114 at an 89 degree climb until it stalls. Simulation performed by Martin Merietta, Jan 91.@£ÍÖÎ1< cˆ i GÿÿÿÿÖÎíControl section7–Î Ï% €$€Œ˜€‚ÿControl sectionÝÖÎ-7 <€Ë€€‡"€‚‚‚‚‚‚‚‚‚‚‚ÿThe control section consists of a structural shell housing for four (4) actuators, a pneumatic manifold together with pneumatic distribution tubing, a wire harness, four (4) aerodynami Ï-–Îc control surfaces, an aft shroud, and an aft launch shoe. Design summary:- Cold gas pneumatic system- Ball poppet-solenoid operation valving- Unbalanced piston- Two (2) axis modules- Sandwich type manifold with integral filter and pressure relief- Blow-out plug - safety releaseº Ïç+ $€€€‚‚‚‚‚‚‚‚ÿ- 600 psi operation pressure- Fin slew rate loaded 150 deg/sec min- Fin slew rate unloaded 400 deg/sec min.- No load stability; 3 deg peak to peak sustained oscillation- Cross coupling; 20% dynamic, 5% static- Hysterisis; .02 degThe control section accepts commands from the guidance section group and positions the four (4) aerodynamic control surfaces as required for missile sterilization and steering control. This is accomplished through the use of the high-pressure nitrogen gas stored in the pneumatic accumulator. The control section has two (2) dual-actuator modules and a sandwich-type manifold with integral filter and pressure relief. The regulator routes the gas at 600 PSI to each of the two (2) dual actuator modules. This high-pressure gas is utilized by the unbalanced piston to effect control of the aerodynamic control surfaces through the movement of ball poppet-solenoid valves.Ú-í, &€µ€€‚‚‚‚‚‚‚‚‚ÿFin 1 is starboard upperFin 2 is starboard lowerFin 3 is port lowerFin 4 is port upperAn interconnecting wire harness assembly transfers electrical signals and power throughout the missile. This harness runs outside the body along the bottom of the missile. The harness is protected by an external cover.The rocket motor's phenolic nozzle runs through the center of the control section. The aft end of the nozzle is flush with the aft end of the control section.< ç)1ªA‰ - Hÿÿÿÿ)— Designators3í\% €€Œ˜€‚ÿDesignatorsk?)Ç , &€€€‚‚‚‚‚‚‚‚‚ÿAlthough designed for use on advanced attack helicopter's the HELLFIRE Missile System is compatible with a variety of laser designators of various services. These include:Target Acquisition and Designation System (TADS) - an AH-64 helicopter on-board systemNight Targeting System (NTS) - an AH-1W helicopter on-board systemGround Laser Locator Designator (GLLD) - a self-contained man portable laser designation system developed for the Army.Modular Universal Laser Equipment (MULE) - a self-contained man portable laser designator developed for the Marine Corps.Ðw\— Y ‚€î€€‚‚‚âÖB܀‰€‚ãì•[€‰€‚ãŸÍˆ“€‰€‚ã`–:€‰€‚ÿRelated topics:Delay Designation TimeLOAL Designator zonesLOBL Designator zonesFailure factorsGÇ Þ 14i Y IÿÿÿÿÞ Ë Delay designation time>—  % €2€Œ˜€‚ÿDelay designation timeXíÞ t k €€Û€€ƒƒƒƒ‚ƒƒƒƒƒƒƒƒ‚ƒƒƒƒƒƒƒƒ‚ƒƒƒƒƒƒƒƒ‚ƒƒƒƒƒƒƒƒ‚ƒƒƒƒƒƒƒƒ‚ƒƒƒƒƒƒƒƒ‚ƒƒƒƒƒƒƒƒ‚‚‚‚‚ÿRange (KM)Flight time (sec)Delay Designate time26243102841459518711623101372912178371522Flight time at 70 deg. FIf missile comes across LOS on delay designation gunner didn't delay enough.A minimum of 6 to 8 seconds (8 sec @ max. range) of laser on target time in needed to ensure missile is able to lock and maneuver to target. If adiquate range exist to target, missile will climb beyond the LOAL level off altitude.W& Ë 1 2€L€€‚‚ãBéW€‰€‚ÿRelated topics:Time of Flight?t  1‘- € Jÿÿÿÿ R@Time of Flight6Ë @% €"€Œ˜€‚ÿTime of FlightÇ R@? L€‘€€†"€‚‚‚‚‚‚âÖB܀‰€‚ÿTo use, follow appropriate red temperature line until it intersects with the desired blue range line. At that intersection go straight left too determine time of flight in seconds.When engaging targets beyond the maximum recommend engagement range of 8km the missile's decaying airspeed causes the missile guidance to become sluggish. Only larger than normal targets should be a@R@Ë ttacked at these ranges.Related topics:Delay designation time?@‘@1@Y „ Kÿÿÿÿ‘@’BLOAL Footprint6R@Ç@% €"€Œ˜€‚ÿLOAL FootprintËr‘@’BY €€ç€€‡"€‚‚‚‚‚‚ãŸÍˆ“€‰€‚ãu_6€‰€‚ãâ‚Ñ€‰€‚ÿIndirect (LOAL-LO/HI) Launch Surface Danger ZonesThe term "protected zone" infers a MULE or GLLD will be designating. The soldier controlling the designator must be "protected" by wearing a helmet, body armor and use terrain or sandbags to shield his position. It is a prohibited zone for aircraft.Related topics:LOBL FootprintLOBLMissile Range?Ç@ÑB1H€ ÿÿÿÿLÿÿÿÿÑBÚDLOBL Footprint6’BC% €"€Œ˜€‚ÿLOBL FootprintÓwÑBÚD\ †€ñ€€‡"€‚‚‚‚‚‚ãì•[€‰€‚ãu_6€‰€‚ãâ‚Ñ€‰€‚€ÿDirect (LOBL / LOAL-Dir) Launch Surface Danger ZonesThe term "protected zone" infers a MULE or GLLD will be designating. The soldier controlling the designator must be "protected" by wearing a helmet, body armor and use terrain or sandbags to shield his position. It is a prohibited zone for aircraft.Related topics:LOAL FootprintLOBLMissile Range 1Cÿÿÿÿ1ÿÿÿÿÿÿÿÿMÿÿÿÿÿÿÿÿÿÿÿÿíämŒHelvTms RmnSymbolCourierTimes New RomanArialMS SerifMS Sans SerifTimesHelveticaSystemCourier NewCourier 10 PitchCourier 20 PitchCourier 5 PitchLetter Gothic 12 PiLetter Gothic 24 PiLetter Gothic 6 PitCourier 16.67 PitchCG TimesUnivers€WÀè’ÅMarlettùíúÀóÀWingdings~HC8IREComic Sans MSAnimals 1CommonBulletsGeographicSymbolsÀKidnapÀ—íúÀóÀMusicalSymbolsÀžîúÀFencesÀ€WÀè’ÅMT ExtraS\TEMP\~hc8AvantGarde Md BTAvantGarde Bk BTDomCasual BTHumanst521 BTNews701 BT*.XL?TechnicalSouvenir Lt BTGoudyHvyface Cn BTGoudyHvyface BTGoudyOlSt BTGoudyOlSt XBd BTLcdDShotgun BTÅÈïúÀ2ÀHandelGothic BT¹îúÀHandelGotDBolRRHarpoonóÀHobo BTïúÀ÷ÃÀMachine BTÀ€WÀè’ÅMurrayHill Bd BTóÀImpuls BT4KidsTïúÀÑ À”Ê ÁShelleyVolante BT ÁStencil BTÀóÀ€WÀStopDóÀpþÀè’Å(‹ÀBlippo Blk BTþÀ€WÀDauphinpþÀè’Å(‹ÀVictorianDÀpþÀ€WÀWindsor BTÀ\' ÁðÊÀSquare 721 BlkÀ\' ÁSquare721 BTóÀH6ÀSquare721 Cn BTu4ÿuRibbon131 Bd BTuÿuWP Greek Centuryu4ÿWP MultinationalA CWP MultinationalB CWP BoxDrawingEüPMWP Greek Courier €éWP Hebrew Davidì‰MüWP MultinationalA HWP MultinationalB HWP Phoneticÿu0ÿuðÿuWP TypographicSymboWP IconicSymbolsAðÿWP IconicSymbolsBÿuWP MathAè÷ùÿÿ‹å]Â0WP MathBSVWjÿuWP MathExtendedA €éWP MathExtendedBøtWP Greek HelveìWP JapaneseuÇEðWP MultinationalA RWP MultinationalB RWP CyrillicA ÇEü WP CyrillicB j‰EWP Arabic SihafaUè‹WP ArabicScript SihElectronicsì$ÇEüMilitaryè¿‹Ø…Ûu MilitaryID‹E …ÀtƒMusictmÇEü €é‡BibleScrT 0€ÇEðArial BlackC tÇEôImpactë3À‰Eô‰EVerdanaèß‹M…À‰Architectureë&jMS Reference 1‰UàèÆMS Reference 2¥…ÛtBookshelf Symbol 1WBookshelf Symbol 2 Bookshelf Symbol 3öArial Special G1_^ÂArial Special G2 Arial Narrow SpeciaTimes New Roman SpeArial Narrow„ƒTahoma!€„3À‹t$MS DialogV;Ðt‹NƒCG Times (WN)óë‰D$€€€ ÅŒ}›€NKƒ x•‰L  µ Þ # » ‚ ™ X A‰ |„Ƈážß €i - € „ H„RŠ‡ážß €J‚Kƒ¬# …€/‡G…|„cˆ € „ » ¿„ ™‰  Á€،/‡،uŒ`،žJ‚H„|„X cˆ € „ xÆŸu 9G‚΄7‰¬Z €g—„)/ €uƒӅW‰ÿõ€H„|„Ž†cˆ - Ž†Y µ Þ ù„ ë† ˆ /&;)i24 8000 FÿÿoÿÿÿÿAGM-114AntishipComponents CookoffHDeice kitLDesignator PDrop RejectionxFailures |Failures (MF)šFiring Modes¬FootprintsÀGuidanceÐIIRSàLOALäLOBLðLongbowüM36 / M34Missile TypesRangeSafety Seeker,SpecificationsˆTime Line Time of Flight€Warheadš 40578 Seeker 40578 Seeker 501C6 Deice kit 501C6 Seeker 506BE Seeker 50A75 Seeker 58139 Seeker 58247 Seeker 584CE Seeker 58937 Seeker 60000 Seeker 600AC Failures 600AC Seeker 60A5A Seeker 68000 Seeker 68167 Seeker 68497 Components 68995 Seeker 70529 Seeker 70A2F Seeker 78000 Seeker 78375 Seeker 785D3 Seeker 78957 Seeker 80000 Seeker 803FF Seeker 806F5 Components 80B4C Components 80C07 Components 901B5 Warhead 901B5 Components 903DE Warhead 903DE Warhead 984F9 Warhead 986EB Warhead 9881A Components A0623 Failures A0623 Guidance A0ABB Components A0ABB Components A8205 Guidance A84BF Guidance A8999 Guidance B04C2 Components B0899 Components B0958 Safety B0958 Specifications B8863 Footprints B8863 Safety B8863 Components B8941 Designator C0569 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