<p>Produced by Texas Instruments, the 400-lb class <hi format=bold>AGM-45 Shrike</hi> was the first anti-radiation missile (<hi format=bold>ARM</hi>). Developed by the Naval Weapons Center as the <hi format=bold>ASM-N-10</hi> during the Vietnam War, it became operational in 1965, with production of 16,000 ending in 1978. All missiles are 8 in (20 cm) in diameter, with a 36.3-in (92-cm) wing span and an 18.0-in (46-cm) tail span. Most Shrikes are 120 in (305 cm) long, with the -7 the longest at 122 in (310 cm). Weights of the $89,000 missile vary between 394 and 426 lb, depending on the components used. Except as noted otherwise. all exterior surfaces are FSN 17875 gloss white.
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<p>Both the <hi format=bold>AGM-45A</hi> and <hi format=bold>AGM-45B</hi> missiles use the same guidance sections, which determine the 'dash' number of the missiles. They operate in four modes: captive, powered, and free flight, followed by terminal guidance. During <hi format=underline>captive</hi> flight the missile provides the crew with target detection signals by using aircraft power. <hi format=underline>Powered</hi> flight defines the period of rocket motor burn and can be commanded either automatically or manually. There are three types of <hi format=underline>free</hi> flight functioning: most missiles simply glide until the gas generator in the control section is activated by the electronic attitude sensor (EAS). This component monitors flight path angle by sensing pressure changes and fires the gas generator after the missile descends through 18,000 ft (5,486 m) and the desired dive angle is reached. In missiles modified for <hi format=ital>dive delivery</hi> the EAS is bypassed and the gas generator fires three seconds after launch, just after motor burnout. In missiles prior to the -9, this function has to be selected before flight by installing a component called a dive plug. In the -9 and -10 missiles EAS bypass (EASB) allows this option to be selected in flight. During <hi format=underline>terminal</hi> guidance power from the gas generator allows the control fins to react to commands from the guidance section, directing the missile towards or, in the case of the <hi format=ital>gravity bias</hi> (G-Bias) missiles, just above the target.
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<p>Shrike guidance sections are designed to attack radars which emit in different frequencies. Unlike the later HARM, which can be programmed, Shrike seekers are 'hard wired' for a single function. The <hi format=underline>Mk 22</hi> (AGM-45-2) was withdrawn from service about 1985. The <hi format=underline>Mk 23</hi> is an inert section used with the ground loading trainer (ATM-45A-1) and separation test item (ATM-45-2). Although similar to the Mk 22, its single-piece shell lacks a radome. The <hi format=underline>Mk 24</hi> (AGM-45-3) and <hi format=underline>Mk 25</hi> (AGM-45-4) are used by both the Air Force and Navy. Use of the <hi format=underline>Mk 36</hi> (AGM-45-6) requires use of a special control section. The <hi format=underline>Mk 41</hi> (ATM-45-6) exercise guidance section contains no fuzing. The <hi format=underline>Mk 37</hi> (AGM-45-7) is used only by the Air Force. The <hi format=underline>Mk 77</hi> (ATM-45-8) is an unfuzed trainer converted from the Mk 36. The <hi format=underline>Mk 49</hi> (AGM-45-9 and -9A), and <hi format=underline>Mk 50</hi> (AGM-45-10) are only used by the Air Force. These sections have no color bands. The Mk 22's radome was FSN 17038 gloss black, and the Mk 23's is FSN 15080 gloss blue. All other radomes are FSN 17875 gloss white.
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<p>The AGM-45As and Bs each have three interchangeable warheads that detonate either when signaled by the guidance section or upon impact. The <hi format=underline>Mk 5</hi> (AGM-45A/B), <hi format=underline>WAU-8</hi> (AGM-45A), and <hi format=underline>WAU-9</hi> (AGM-45B) warheads have a 2-in (5-cm) wide bands of FSN 14187 gloss green, indicating the presence of a red phosphorus (RP) spotting charge, and FSN 23538 semi-gloss dark yellow. The <hi format=underline>Mk 86</hi> (AGM-45A/B) warhead has only a single 2-in (5-cm) wide yellow band. The <hi format=underline>Mk 83</hi> (ATM-45A/B) inert practice warheads are FSN 15080 gloss blue. The <hi format=underline>Mk 85</hi> (ATM-45A/B-4) is FSN 15080 gloss blue, with a yellow band like that on the Mk 86.
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<p>The full-deflection (bang-bang) <hi format=underline>Mk 1</hi> and <hi format=underline>Mk 5</hi> control sections have a 2-in (5-cm) wide band of FSN 30117 flat brown, while the inert <hi format=underline>Mk 2</hi> is overall FSN 15080 gloss blue. All are fitted with four, 14.0-in (36-cm) high <hi format=underline>Mk 2</hi> wings, which are sometimes left off of captive trainers.
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<p>The <hi format=bold>AGM-45A</hi> uses the single burn 22,000 lb-second total impulse <hi format=underline>Mk 39</hi> motor with a 2.8-second burn time. A second AGM-45A motor, the <hi format=underline>Mk 53</hi> was withdrawn from service in the mid-1980s. The <hi format=bold>AGM-45B</hi> introduced the dual burn 22,300 lb-second total impulse <hi format=underline>Mk 78</hi> motor, with an initial 1.0-second acceleration thrust supplemented by a 20-second period of lower sustained thrust. Motors have a 2 to 3-in (5 to 7.6-cm) wide band of FSN 30117 flat brown about 8 in (20 cm) from the front edge of the motor. The inert <hi format=underline>Mk 46</hi> is FSN 15080 gloss blue. All motors are fitted with four, 5.7-in (14.5-cm) high <hi format=underline>Mk 21</hi> tail fins. As with the wings, these are sometimes left off captive trainers.
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<p>The <hi format=bold>ATM-45A-1</hi> is a non-flight qualified ground handling trainer. The <hi format=bold>ATM-45A-2</hi> was used for safe separation testing of the AGM-45A. The <hi format=bold>ATM-45A-3</hi> can be fitted with any seeker and used either as a captive operational trainer or to train ground crew. The <hi format=bold>ATM-45A-4</hi> and <hi format=bold>ATM-45A-6</hi> are used for live-fire operational training. The <hi format=bold>ATM-45B-2</hi> was used for safe separation testing of the AGM-45B. The <hi format=bold>ATM-45B-4</hi> and <hi format=bold>ATM-45B-6</hi> are used for live-fire operational training.
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<p>Shrikes can be launched from the LAU-34 or the newer LAU-118, also used for the AGM-88. The Shrike in USAF service can be carried by F-4Gs and 'Wild Weasel' F-16Cs. It has also been used by the USN and exported to Britain during the Falklands War and to Israel during the 1973 Yom Kipper War. With little or no capability against modern SAMs, the Shrike has almost passed into history. However, they are kept in storage 'just in case'.
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<hi style=hdr1>AGM-65 Maverick</hi>
<display id=\weapons\photos\agm65001.bmp>
<p>Developed during the Vietnam War as a subsonic, launch-and-leave replacement for the AGM-12 Bullpup, the Hughes Maverick has continued to evolve and remained in production through FY91, with second-source supplier Raytheon receiving the final contract. While utilizing a variety of guidance and warhead sections, all AGM-65s are the same size (98 in/249 cm long, 12 in/30 cm in diameter, with a 29-in/74-cm fin span). The original 125-lb high-explosive, shaped-charge WDU-20 has been replaced in later Mavericks with the 300-lb WDU-24 blast-penetration warhead. All versions use the same rocket motor, with maximum launch range dependent on target size and seeker performance. While maximum aerodynamic range is about 12.5 nm (23 km), a more realistic range is nearer 8 nm (15 km). During the Gulf War, over 90 per cent of the AGM-65s fired were from A-10s. Maverick is a very workload-intensive weapon which pilots of faster, single-seat aircraft, such as the F-16, found very difficult to employ in combat.
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<display id=\weapons\photos\agm65b01.bmp>
<p><hi format=bold>AGM-65A</hi> has a 5 degree field of view (FOV) electro-optical (EO) television seeker that the pilot uses to acquire the target. After designating the target and ensuring that the missile is locked on, he fires it and can either select another target or commence escape maneuvering. The $22,000 missile was introduced in 1972, and all were FSN 17875 gloss white. During the Vietnam War, 99 were fired operationally with an 88 per cent success rate. Four hundred were transferred from US stocks to Israel during the 1973 Yom Kippur War.
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<p><hi format=bold>AGM-65B</hi> features an optional 2.5 degree FOV. Called 'scene-magnification', it can be locked onto the same target as an AGM-65A from twice the range. Both missiles can be identified by their clear seeker domes. Introduced in 1975, the $64,000 AGM-65Bs were initially painted white, with the words 'SCENE MAG' stenciled on the side of the seeker. However, many were later painted FSN 34087 olive drab. During Desert Storm, A-10s fired 1,682 AGM-65Bs.
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<p><hi format=bold>AGM-65C</hi> was a semi-active laser (SAL) version developed in the late 1970s. However, in 1979 both the USAF and USN decided to forgo this seeker in favor of IIR guidance and this missile was never produced.
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<p><hi format=bold>AGM-65D</hi> was the first Maverick with an imaging infra-red (IIR) seeker. Introduced in 1983, it first became operational during 1986 with 81st TFW A-10As. The advantage of the $110,000 IIR missile over earlier EO versions is its ability to be used at night and in conditions of smoke and haze. With the IIR seeker, the missile can be locked on to targets at greater ranges than it is capable of flying aerodynamically. These missiles are FSN 34087 olive drab with a silverish seeker, similar to some sunglasses. During Desert Storm, A-10s fired 3,128 AGM-65Ds.
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<p><hi format=bold>AGM-65E</hi> is the operational version of the earlier AGM-65C. The USMC is the only user of SAL guidance, and this version became the first to feature the larger warhead. SAL permits ground troops to designate targets for close air support. During the Gulf War, this capability was used fewer than 10 times. The AGM-65E was first delivered in 1985 and is FSN 36375 gray.
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<display id=\weapons\photos\agm65002.bmp>
<p><hi format=bold>AGM-65F</hi> entered production in 1987, combining the C's larger warhead with the D's IIR seeker. Built for the Navy, it has a modified tracking function optimized for attacking ships. It also introduced inflight selectable fuzing to allow warhead effects to be optimized for the target being attacked. Because of the heavier warhead, this missile has a slightly decreased maximum range
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<p><hi format=bold>AGM-65G</hi> combines the guidance features of both the 'D' and 'F' with the latter's warhead. They cost about $121,000 each in FY90. An Air Force missile, it is olive drab in color. It also differs from the AGM-65F in that its guidance and fuzing options must be selected prior to flight. It differs from the AGM-65D in that it is better capable of being locked onto larger targets. During Desert Storm, A-10s fired 203 AGM-65Gs.
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<p><hi format=bold>A/A37A</hi> series captive Maverick trainers are commonly called TGM-65s. They are ballasted to weigh as much as the live missiles, are usually fitted with a video recorder to aid in training, and can most easily be identified by their lack of tail fins. The A/A37A-T1 is used to simulate the AGM-65A and B, the A/A37A-T8 and -T10 simulate the AGM-65D, while captive AGM-65Fs are called CATM-65Fs. (Unlike the live missiles, IIR training missiles have yellowish seeker domes.) The A/A37A-T9 simulates the AGM-65E.
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<p>A turbine-engined variant, called '<hi format=bold>Longhorn</hi>', has been proposed. It would be equipped with either IIR or millimeter wave guidance sections and have triple the range of existing versions.
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<p>Maverick launchers include the three-rail <hi format=bold>LAU-88</hi> (for A, B and D versions), and single-rail <hi format=bold>LAU-117</hi> that can be used with any version. In addition to the USN and USMC, USAF Mavericks can be employed by the A-10A, F-111F, F-4G, F-15E, and F-16. It has been exported to Greece, Iran, Israel, Korea and Turkey (F-4E); Saudi Arabia (F-5E); Sweden (AJ37 as the <hi format=bold>Rb 75</hi>); and Switzerland (Hunter).
<row><c>AGM-65F<c>WGU-13/B IIR (anti-ship)<c>677 lb<c>300 lb<c>USN only
<row><c>AGM-65G<c>IIR<c>642 lb<c>675 lb<c>USAF only
</table>
<hi style=hdr1>AGM-130</hi>
<p>The Rockwell AGM-130 stand-off weapon system (SWS) is a GBU-15 equipped with a rocket motor to increase its stand-off range from 15 nm (28 km) to over 40 nm (74 km). One important upgrade from the GBU-15 is the incorporation of a charge coupled device (CCD) that will extend its usability for two additional hours per day. It also improves the missile's reliability, EO sensor clarity and sensitivity while reducing cost. Although tested with the F-4E and fit checked on the F-16 and Tornado, it is only operational with the F-111F and F-15E. Operational testing began in July 1994 at Cannon AFB, NM with F-111Fs of the 524th FS. After the completion of production verification flight testing, approval for full-rate production was approved late 1994. Initial testing with the B-52H is expected to begin in 1995, with plans to also qualify it with the B-1B and B-2A.
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<p>Launched from a prebriefed location, the AGM-130 flies a glide, rocket-powered, glide profile while receiving man-in-the-loop guidance inputs via datalink. The rocket motor separates after burn out, and a radar altimeter allows terrain clearance to be selected in 200-ft (60-m) increments. Once the target is sighted, the missile can either be manually guided or locked on for automatic terminal guidance.
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<p>Further proposed upgrades included the incorporation of an INS/GPS navigation package to increase the weapon's operational utility by delaying man-in-the loop guidance to the final 15-20 seconds of weapon's flight. This would reduce the amount of datalink transmissions, increase launching position and weather flexibility, and allow the WSO to be more involved in target area egress (rather than being totally involved in weapon guidance from launch to impact).
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<p>Procurement of the $400,000 missile was originally intended to reach 4,048, but was reduced to only 2,300 in 1993 because of a combination of budget pressures and the anticipated procurement of newer weapons, such as JSOW. By mid-1993 the first three production lots were under contract; with Lots 4 and 5 planned to be equipped with CCD seekers and improved, anti-jam datalinks, while Lot 6 would have improved IIR seekers. The initial contract award for weapons using the BLU-109 was made in August 1992. A further 102 were authorized in the FY95 budget.
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<p>A turbojet-powered version of the AGM-130 has been proposed for the British Conventionally Armed Stand-Off Missile (<hi format=bold>CASOM</hi>) requirement. This version was initially unveiled in 1992 and would use the same engine (and have nearly the same 180-nm/332-km range) as the canceled AGM-137, which it could replace. Another proposal to increase the AGM-130's range is to revive the planar-wing concept originated with the GBU-15 in the 1970s to increase its range to about 100-nm (184 km). However, the new wing is being developed by Brunswick, which also makes the ADM-141 TALD.
<p>The McDonnell Douglas Harpoon anti-ship missile entered production for the US Navy in 1975. It can be launched from ships (RGM-84) and submarines (UGM-84), as well as aircraft (AGM-84). The ship-launched versions have 30.9-in (78-cm), 367-lb rocket boosters that create 12,000 lb (53.4 kN) of thrust for 2.9 seconds before burning out and separating from the missile. The AGM-84A through D are externally identical. All versions of this subsonic missile are powered by a 600-lb (2.7-kN) thrust turbojet that is fed by a NACA inlet located on the bottom of the missile between its 36-in (91-cm) span wings. The inlet cover is jettisoned after the missile separates from the aircraft and just prior to starting the turbojet. The Harpoon warhead weighs about 500 lb, with two hits required to disable a destroyer, or five for a 'Kiev'-class helicopter carrier.
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<p>Introduced in 1976, the 1,150-lb initial production (IP) <hi format=bold>AGM-84A</hi> Harpoons are 152 in (386 cm) long. It uses a radar altimeter to fly at sea-skimming heights and has an inertial guidance section programmed prior to launch to direct it to the target area, where a frequency-agile radar seeker controls terminal guidance. As it attacks its target, the missile performs a pop-up maneuver to enhance warhead penetration. The warhead has a delay fuze, allowing it to penetrate into the target before exploding. The IPs were followed in 1978 by Block 1 missiles, which feature improved ECCM.
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<p>The Block 1A <hi format=bold>AGM-84B</hi> 'Sub-Harpoon' is used by the British Royal Navy. It incorporates an indigenous guidance program that decreases cruise altitude and dispenses with the terminal pop-up maneuver. The Block 1B <hi format=bold>AGM-84C</hi>, first delivered in June 1982, incorporates the British features into US missiles.
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<p>Deliveries of the 1,170-lb Block 1C <hi format=bold>AGM-84D</hi> began in 1984. Its range has been increased over previous versions from 57 to 75 nm (106 to 139 km). It also features a refined pop-up maneuver, the ability to navigate to several turn points en route to the target area, a selectable search priority, and several optional terminal attack maneuvers. The warhead is also fitted with crush sensors to increase warhead survivability as it penetrates the target.
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<p>The development contract for the 1,400-lb Block 1D <hi format=bold>AGM-84F </hi>was awarded in September 1989. Its major guidance improvement was the ability to execute a cloverleaf reattack pattern to search for a target if it was not detected during the initial attack. It also featured a 22.3-in (57-cm) fuselage extension behind the wing but in front of the inlet, containing additional fuel for increased range. However, this Block 1D option was only exercised for the sea-launched RGM-84 version, with production approval being given during 1992 for upgrades to existing missiles. The AGM-84F was tested and, although production did not materialize, the Block 1D guidance improvements are being made to AGM-84D airframes as the Block 1CR, resulting in the <hi format=bold>AGM-84G</hi> designation.
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<p>As of July 1992, more than 6,500 Harpoons had been produced, used by the USN, USAF, USCG and 20 foreign customers. Beginning in July 1984, 30 B-52Gs were equipped with AGM-84A/D Harpoons. As these aircraft were earmarked for retirement, Harpoon capability has been added to 19 B-52Hs. On B-52s, Harpoons are mounted on the HSAB's MAU-9A/A bomb rack. The missile has also been fit-checked on the Block 50 F-16.
</p>
<p>Harpoons are normally referred to by their 'Block', rather than AGM designation. They are painted either FSN 17858 gloss white or FSN 36440 flat gray. The 'White' missile's diameter is 13.5 in (34.29 cm), while the 'Gray' missiles have a 13.59-in (34.52-cm) diameter (with a weight increase of 50 lb). Some missiles were fueled at the factory with JP 5 fuel while others received JP 10 (which increases their weight by about 20 lb). All color bands are 2-in (5-cm) wide. The sustainer motor section's flat brown band is either FSN 30117 or 30140, while the warhead's yellow band is either FSN 13538 gloss or 33538 flat.
</p>
<p>The ATM-84A/C/D/G-<hi format=underline>1</hi> <hi format=ital>exercise</hi> air launch missiles replace the warhead with a telemetry section marked with a FSN 35109 flat blue band. The ATM-84A/C/D/G-<hi format=underline>1A</hi> <hi format=ital>inert warhead</hi> air launch missiles have a FSN 35109 flat blue warhead band. The ATM-84A-<hi format=underline>1B</hi> <hi format=ital>inert training</hi> missiles are not flight worthy and used as only as ground crew trainers. The similar captive carry ATM-84A-<hi format=underline>1C</hi> ballistic air test vehicle is also completely inert and has a FSN 35109 flat blue band around the guidance section.
<p>The Northrop AGM-137 TSSAM was a stealthy missile developed by the USAF for itself, as well as the Army and Navy. The Army's ground-launched version was to be designated <hi format=bold>MGM-137</hi>. The 14-ft (4-m) long missile had an 8.3-ft (2.5-m) wing span and a range of slightly more than 180 nm (332 km). Originally, four versions were to be developed, employing the BLU-97 CEM, brilliant anti-tank (BAT) sub-munitions, and two types of terminally guided unitary warheads. By 1994, only two versions remained: a 1,000-lb class unitary warhead version which was to go into production, and a sub-munition version that would be developed but not produced to keep program costs down.
</p>
<p>The original TSSAM mission was to attack well protected Warsaw Pact and Soviet targets during the first few days of a conflict. Its range would allow hardened air defense sites, command and control complexes and communication centers to be struck with minimum warning while allowing the launching aircraft to remain well beyond enemy air defenses. Its wide airfoil body was designed to impart extreme maneuverability to evade air defense concentrations, avoid other obstacles, and perform high- and low-level pop-up attacks, while its all-aspect stealth design would make it difficult to locate and attack.
</p>
<p>The original program plan was to procure 9,050 missiles over five years at a unit cost of $1.06 million ($9.6 billion for the program). By late 1994, the total buy had shrunk to 4,156 (3,631 USAF and 525 USN) at a unit cost of $3.2 million ($13.3 billion for the program).
</p>
<p>The Air Force planned to employ AGM-137 with the B-52H (12 external), B-1B (eight internal), B-2A (eight internal), F-16 (two external), and F-22, while the Navy originally hoped to use it with the A-6E and F/A-18 (two external). However, by the FY94 budget cycle, Navy participation was reduced to $75.4 million, and the Army withdrew from the program entirely.
</p>
<p>Initial test launches were performed by the B-52 and A-6E. With the program about halfway through EMD, results of two 1994 test launches (5 August from an F/A-18C and 13 August by an F-16C) were quickly made public by the USAF to help preserve the troubled TSSAM development effort during Congressional budget deliberations. Film of the tests showed the missiles striking targets less than 9-ft (2.7-m) wide after flying to maximum range. The schedule by that time called for a long-lead production decision in January 1996, completion of flight test in 1997, initial USAF delivery in FY99, and first USN delivery in FY02.
</p>
<p>The TSSAM program was canceled "for the convenience of the government," on 10 February 1995. The Air Force will embark on what is commonly called 'Son of TSSAM', that will be stealthy from only the front aspect in hopes of reducing unit costs to about $750,000. To fill the stand-off void left by the AGM-137's cancellation, the Air Force is exploring options to procure an additional AGM-86C, AGM-130, or AGM-142. The Navy plans to acquire additional AGM-84E and SLAM(ER) missiles.
</p>
<hi style=hdr1>AGM-142 Popeye</hi>
<p>Popeye is a 3,300-lb conventional stand-off missile armed with either 750-lb high-explosive/fragmentation or 800-lb hard structure munition (HSM) warhead (using the FMU-124 C/B fuze). It was developed by Israel's Rafael Armament Development Authority in the early 1980s and procured by the US Air Force under the '<hi format=bold>Have Nap</hi>' program.
</p>
<p>Co-produced in the US by Martin Marietta, the 190-in (483-cm) long weapon features inertial guidance coupled with EO and IIR terminal homing. Popeye differs from the USAF's GBU-15 and AGM-130 in two major respects: its inertial platform allows greater flexibility in guidance and navigation and its sustainer rocket motor allows it to be powered all the way to target impact. These advantages are offset by its larger size, higher cost ($726,000 for each of the 86 missiles bought), and much smaller warhead.
</p>
<p>The 63-nm (116-km) plus range Popeye became operational with conventionally dedicated B-52Gs in the early 1990s and was also evaluated with the F-111F and F-15E. It was not used during the Gulf War, reportedly because of concerns about the effects using an Israeli-developed weapon would have had on the coalition. It is also operational with Israeli air force F-4Es.
</p>
<p>Testing of the 2,500-lb <hi format=bold>AGM-142D</hi>, dubbed Have Lite or Popeye 2, began in the fall of 1994. Improvements to the 168-in (427-cm) long missile include use of a IIR seeker, penetration warhead, a new inertial measurement unit (IMU), laminated wings and fins, and a lighter rocket motor casing. The $650,000 missile is designed for use by Israeli F-16s and other tactical aircraft. It is also small enough to be carried internally by the B-1B and B-2A. Thirty of these missiles were bought for B-52Hs using FY93 funds. An additional $31 million was provided in 1994 to fund 36 more missiles. Total inventory of Have Nap is expected to reach 130. Testing of the AGM-142D is expected to begin as early as 1996, with production to follow in 1997. Consideration is being given to a turbojet-powered version with a range in excess of 200 nm (370 km).
</p>
<hi style=hdr1>AGM-154 JSOW</hi>
<p>Formerly known as the advanced interdiction weapon system (<hi format=bold>AIWS</hi>), the Texas Instruments AGM-154 joint stand-off weapon (<hi format=bold>JSOW</hi>) was a $400-million Navy-led research and development program to develop a gliding PGM with a stand-off range of about 40 nm (74 km). Program costs through the first 21,600 JSOWs will be $6 billion. Flight testing began on 19 November 1993 at Patuxent River (on F/A-18C 163985, s/n 100), with the initial separation/jettison test on 8 March 1994 (on NF/A-18A 161925, s/n 106). The first guided launch occurred on 13 December 1994 (from F/A-18C 163476 s/n 101) at China Lake.
</p>
<p><hi format=bold>AGM-154A</hi> will be equipped with 145 BLU-97 <hi format=bold>CEM</hi> cluster munitions (see SUU-64). This 1,000-lb class weapon will use GPS-aided inertial guidance to navigate to the target area with a terminal accuracy of less than 33 ft (10 m). About 8,800 of this version will be procured at a cost of $100,000 each. The Navy plans to replace its Rockeye II and CBU-59 APAM cluster bombs with the AGM-154A. Low-rate production is planned for 1996, leading to an initial operational capability (IOC) in 1999.
</p>
<p>The primary Navy JSOW delivery vehicle will be the F/A-18C/D (and later the new F/A-18E/F). The integration process for the AV-8B will begin in 1998. The Harrier II has an additional requirement to take off with two weapons and land vertically with just one. (Initial plans called for Navy versions to be delivered from the A-6E, AV-8B, F/A-18, F-14, and any future attack capable aircraft. However, the early retirement of the A-6E led to it being dropped from the program.)
</p>
<p>The primary Air Force JSOW delivery vehicle will be the F-16C, with two weapons being loaded to the center wing pylons, with consideration being given to doubling this by use of the F/A-18's BRU-33A/A CVER, thus still allowing two wing fuel tanks to be carried. Other likely candidates include the F-15E and B-1B. The F-15E fit check evaluated six weapons mounted to the wing pylons and front and rear-bottom CFT stations (although the rear stations may not have be usable because of acoustic loads). The B-1B can carry four per weapon bay on CSRLs. Fit checks were also conducted with the B-52H and F-111F.
</p>
<p>JSOW is also designed to be compatible with all NATO tactical combat aircraft. The Tornado was fit checked with the weapon in late 1993. There is the possibility that foreign participation in the program will be allowed before the full-scale production decision is made in 1998.
</p>
<p><hi format=bold>AGM-154B</hi> will deliver the BLU-108 <hi format=bold>SFW</hi> (see SUU-64) for anti-armor applications. The Air Force plans to acquire 5,000, beginning in 2000. Use of JSOW as a SEAD weapon to counter SA-4 and SA-11 SAMs is also considered likely.
</p>
<p><hi format=bold>AGM-154C</hi> is scheduled to become operational with the Navy in 2001. It will be fitted with a 500-lb <hi format=bold>BLU-111</hi> GP bomb warhead and a IIR terminal guidance seeker developed by Phase III of the JDAM program. The addition of the seeker will provide this $400,000 weapon with a 10-ft (3-m) accuracy, allowing it to attack point targets such as bridges. About 7,800 are expected to be acquired, with the Navy using them to replace the AGM-62 Walleye, AGM-65 Maverick, AGM-123 Skipper II, and 'some LGBs'. The Air Force originally did not plan to buy any of this version, but is reconsidering this position in the wake of the AGM-137 TSSAM's cancellation.
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<p>One possible follow-on effort would equip JSOW with a more powerful penetration warhead. Other payloads being considered include the <hi format=bold>Gator</hi> and <hi format=bold>BAT</hi> sub-munitions, and the <hi format=bold>'Kit 2'</hi> carbon fiber warhead (like those used by BGM-109s during the 1991 Gulf War). In addition, proposals to use it to deliver <hi format=bold>Gen-X</hi> disposable radar jammers, and even as a resupply container carrying food and ammunition for long range patrols are being evaluated.
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<hi style=hdr1>SHarK</hi>
<p>A USAF program to develop a <hi format=bold>Silent Hard Kill</hi> (SHarK) capability was announced in mid-1993. Unlike previous suppression of enemy air defense (SEAD) programs, SHarK was tasked with preemptively striking silent, non-emitting surface-to-air and theater ballistic missile sites, and doing enough damage to take them out of the battle for several days.
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<p>Expected to eventually become a joint program with the USN, SHarK went unfunded in FY93, but was redirected to study the overall process of destroying non-emitting air defense radars. Renamed <hi format=bold>Preemptive Destruction</hi>, it was managed by the Conventional Munition Systems SPO at Eglin AFB, FL. As a study program, its research team identified and evaluated 124 SEAD tasks through mid-1995, to find the most cost-effective way to accomplish the SHarK task.
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<p>The preemptive destruction mission differed from reactive suppression by being less time sensitive. By September 1994, it was thought that the mission would be broken into two parts, a non-lethal decoy and a lethal bomb or missile. First, the threat would be generally located, probably by a stand-off system, such as JSTARS. Then its position would be refined by using a short-range, air-launched decoy, launched from a fighter aircraft. The miniature decoy would perform a ferret function, using an RF package to emit aircraft-like radar signals. (In a joint development effort, ARPA contracted Sundstrand to develop a very small engine for the decoy. By late FY96 or early FY97, the engine program would be transferred to the USAF for production of 24 complete systems in FY98.) The decoy would also identify and prioritize the threat for later attack by the lethal system. The study narrowed the list of potential non-lethal sensor technologies to millimeter-wave radar (MMWR), imaging infra-red (IIR), synthetic aperture radar (SAR), global positioning system (GPS), and laser radar (LADAR).
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<p>Because of the inherent mobility of modern SAM systems, lethal attack would need to be within a few minutes of threat identification and location. (A Russian-exported SA-8 could move 24 miles/39 km in two hours.) It was expected that the actual kill mechanism would be based on an existing delivery system such as TMD, AMRAAM, HARM, JDAM, JSOW, AGM-65, or AGM-130. The warhead was anticipated to be some sort of area munition, such as an SFW modified to expel up to 54 fragments rather than a single, focused warhead. This would be necessary to counter modern systems, such as the SA-11, which could have up to 0.5 mile (0.8 km) between various system elements, using datalink instead of hard wired communication links.
